CONSTELLATION SPACE SUIT SYSTEM ISS …sbir.gsfc.nasa.gov/SBIR/solicitations/2016/CSSS-T-002_LSS_CEI_ISS... · Document No.: D-0582682 Release Date: 7/02/2015 Revision: X-2 Date:

Document No. D-0582682 Release Date: 7/02/2015 Revision: X-2 Date:

Export Control Notice This document contains information on pages 1 – 105 that falls under the purview of the U.S. Munitions List (USML), as defined in the International Traffic in Arms Regulations (ITAR), 22 CFR §§ 120-130, and/or the Export Administration Act of 1979, as amended, 50 U.S.C., App. 2401, et seq., and is export controlled. It shall not be transferred to “foreign persons”, including foreign business entities and governments (22 C.F.R. § 120.16), in the U.S. or abroad, without the specific approval of a duly-authorized NASA export control official, and an export license obtained from the United States Department of State, or a documented determination that an ITAR exemption applies. Violations of these regulations are punishable by fine, imprisonment, or both.

CONSTELLATION SPACE SUIT SYSTEM

ISS UMBILICAL ASSEMBLY CONTRACT NUMBER: NNJ09TA40C

DRD CSSS-T-002 Prepared by: Anna Ronalds CSSS Systems Engineer Approved by: e-Signature John Fricker CSSS Life Support Subsystem (LSS) Lead e-Signature Cory Logan CSSS Systems Engineering and Integration (SE&I) Manager e-Signature Brian Krolczyk CSSS Safety, Reliability and Quality Assurance (SR&QA) Manager e-Signature Judson Hedgecock CSSS Suit Element Manager

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Table of Contents Acronyms ...................................................................................................................................... vi 1.0 Introduction ....................................................................................................................... 1

1.1 Purpose ............................................................................................................................ 1

1.2 Scope ............................................................................................................................... 1

1.3 Reserved .......................................................................................................................... 1

1.4 Conventions and Notations ............................................................................................. 1 1.4.1 "Shall", "Should", and "Will" ..................................................................................... 1 1.4.2 "TBX", "TBD" and "TBR" ......................................................................................... 1 1.4.3 Requirement Identification and Ownership ................................................................ 1 1.4.4 Naming Conventions .................................................................................................. 2 1.4.5 Use of Measurement Units.......................................................................................... 2 1.4.6 Requirement Traceability............................................................................................ 2 1.4.7 Rationale ..................................................................................................................... 2

1.5 Change Authority / Responsibility.................................................................................. 3 1.5.1 Order of Precedence .................................................................................................... 3

2.0 Documents ......................................................................................................................... 3

2.1 Applicable Documents .................................................................................................... 3

2.2 Reference Documents ..................................................................................................... 4

3.0 Requirements..................................................................................................................... 5

3.1 Description of the ISS Umbilical Assembly ................................................................... 5

3.2 Performance .................................................................................................................... 5 3.2.1 Reserved ...................................................................................................................... 6 3.2.2 Maintenance ................................................................................................................ 6 3.2.3 Reserved ...................................................................................................................... 7 3.2.4 Product Life ................................................................................................................ 7 3.2.5 Reserved ...................................................................................................................... 8 3.2.6 Reserved ...................................................................................................................... 8

3.3 Physical Characteristics .................................................................................................. 8 3.3.1 Mass ............................................................................................................................ 8 3.3.2 Product Marking ......................................................................................................... 9 3.3.3 Cleanliness .................................................................................................................. 9

3.4 Interfaces ....................................................................................................................... 11 3.4.1 Vehicle Umbilical Fluid Interfaces ........................................................................... 14 3.4.2 Vehicle Umbilical Electrical Interfaces .................................................................... 17 3.4.3 Umbilical PLSS Electrical Interfaces ....................................................................... 21 3.4.4 Umbilical PLSS Fluid Interfaces .............................................................................. 22 3.4.5 Reserved .................................................................................................................... 22

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3.4.6 Reserved .................................................................................................................... 22 3.4.7 Reserved .................................................................................................................... 22 3.4.8 Reserved .................................................................................................................... 22

3.5 Design and Construction ............................................................................................... 22 3.5.1 Materials ................................................................................................................... 25 3.5.2 Electrical Design ....................................................................................................... 26 3.5.3 Fluid Design .............................................................................................................. 31 3.5.4 Maintainability .......................................................................................................... 33

3.6 Environments ................................................................................................................ 34 3.6.1 Vibration ................................................................................................................... 35 3.6.2 Loads ......................................................................................................................... 38 3.6.3 Thermal ..................................................................................................................... 38 3.6.4 Reserved .................................................................................................................... 40 3.6.5 Reserved .................................................................................................................... 40 3.6.6 Magnetic ................................................................................................................... 40 3.6.7 Pressure ..................................................................................................................... 43

3.7 Human Interfaces .......................................................................................................... 43

3.8 Structures ...................................................................................................................... 44

4.0 Verification ...................................................................................................................... 52

4.1 Verification Methods .................................................................................................... 52

4.2 Performance .................................................................................................................. 53 4.2.1 Reserved .................................................................................................................... 54 4.2.2 Maintenance .............................................................................................................. 54 4.2.3 Reserved .................................................................................................................... 55 4.2.4 Reliability .................................................................................................................. 55 4.2.5 Reserved .................................................................................................................... 56 4.2.6 Reserved .................................................................................................................... 56

4.3 Physical Characteristics ................................................................................................ 56 4.3.1 Mass .......................................................................................................................... 57 4.3.2 Product Marking ....................................................................................................... 57 4.3.3 Cleanliness ................................................................................................................ 57

4.4 Interfaces ....................................................................................................................... 59 4.4.1 Vehicle Umbilical Fluid Interfaces ........................................................................... 60 4.4.2 Vehicle Umbilical Electrical Interfaces .................................................................... 63 4.4.3 Umbilical PLSS Electrical Interfaces ....................................................................... 64 4.4.4 Umbilical PLSS Fluid Interfaces .............................................................................. 64 4.4.5 Reserved .................................................................................................................... 64 4.4.6 Reserved .................................................................................................................... 64 4.4.7 Reserved .................................................................................................................... 64 4.4.8 Reserved .................................................................................................................... 65

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4.5 Design and Construction ............................................................................................... 65 4.5.1 Materials ................................................................................................................... 67 4.5.2 Electrical Design ....................................................................................................... 69 4.5.3 Fluid Design .............................................................................................................. 74 4.5.4 Maintainability .......................................................................................................... 75

4.6 Environments ................................................................................................................ 76 4.6.1 Vibration ................................................................................................................... 77 4.6.2 Loads ......................................................................................................................... 79 4.6.3 Thermal ..................................................................................................................... 80 4.6.4 Reserved .................................................................................................................... 81 4.6.5 Reserved .................................................................................................................... 81 4.6.6 Magnetic ................................................................................................................... 81 4.6.7 Pressure ..................................................................................................................... 81

4.7 Human Interfaces .......................................................................................................... 82

4.8 Structures ...................................................................................................................... 84

Appendix A – Glossary of Terms ............................................................................................... 96

Appendix B - TBX ....................................................................................................................... 98

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List of Figures Figure 3.4-1: EXS.1.205 Vehicle Umbilical (FSE) ...................................................................... 12

List of Tables Table 2.1-1: Applicable Documents ............................................................................................... 3 Table 2.2-1: Reference Documents ................................................................................................. 4 Table 3.4-3: External Interfaces .................................................................................................... 12 Table 3.4-1: Umbilical Supply Water Table ................................................................................. 14 Table 3.4-2: Biocide Concentration .............................................................................................. 17 Table 3.4-4: External Power ......................................................................................................... 18 Table 3.4-5: Umbilical to Vehicle Electrical Pinout Table ........................................................... 18 Table 3.4-6: Hardline Audio Out .................................................................................................. 20 Table 3.4-7: Hardline Audio In ..................................................................................................... 20 Table 3.4-8: Umbilical to Suit (SRC) Electrical Pinout Table ..................................................... 21 Table 3.5-1: Toxic Hazards Levels ............................................................................................... 32 Table 3.6-1: COTS ISS Internal Cargo Environment ................................................................... 34 Table 3.6-2: Ozone Exposure ....................................................................................................... 35 Table 3.6-3: Sinusoidal/ Shock Environment for Pre-Launch Transportation Phase ................... 36 Table 3.6-4: Acoustic Environment for Launch ........................................................................... 36 Table 3.6-5: On-orbit Random Vibration Environment ............................................................... 37 Table 3.6-6: On-orbit Operational Sinusoidal Vibration Envelope .............................................. 37 Table 3.6-7: Sinusoidal/ Shock Environment for All Flight Phases ............................................. 38 Table 3.6-8: Launch / Landing Load Factors Envelope (Any Orientation) .................................. 38 Table 3.6-9: IVA Inadvertent Contact Loads ............................................................................... 38 Table 3.6-11: Temperature Extremes for IVA / Ground Operations ............................................ 39 Table 3.6-12: RF Exposure Limits................................................................................................ 42 Table 3.8-1: Hardline Audio Out .................................................................................................. 45 Table 3.8-2: Umbilical Assembly Minimum Factors of Safety and Test Factors ........................ 47 Table 3.8-3: Minimum Factors of Safety for Beryllium Structures .............................................. 50 Table 4.8-1: VCRM Table ............................................................................................................ 91

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Acronyms A Analysis AAP Airlock Adapter Plates AC Alternating Current ADD Architecture Description Document ADIT Analysis, Demonstration, Inspection and Test ASD Acceleration Spectral Density ATU Audio Terminal Unit Ampere(s) AMP Amps Amperes BCA Battery Charger Assembly BIT Built In Test BITE Built In Test Equipment BOCA Battery to Battery Charger Assembly BRT Body Restraint Tether BSA Battery Stowage Assembly BTA Bends Treatment Adapter BTU British Thermal Unit CAD Computer Aided Design CDO Cognitive Deficit Onset CEI Configuration End Item CETA Crew and Equipment Translation Assembly CFU/mL Colony Forming Units per milliliter CG Center of Gravity CGA Commodity Gas Association CI Configuration Item CO2 Carbon Dioxide COPV Composite Overwrap Pressure Vessel CSSS Constellation Space Suit System CWCS Caution & Warning Control System Comm Communication D Demonstration DC direct current DFMR Design for Minimum Risk DIA Diameter DRD Data Requirements Description DRM Design Reference Mission DUT Device Under Test DWG Drawing DoD Department of Defense ECF Environmental Correction Factor (ECF) EDDA EVA Don/Doff Assembly EGC External Gas Conditioner ELCA EVA Light and Camera Assembly

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EMI Electromagnetic Interference EMU Extravehicular Mobility Unit ER Engineering Record ERCA EVA RF Camera Assembly ESD Electrostatic Discharge EVA Extravehicular Activity EVVA Extravehicular Visor Assembly EXS Exploration Space Env Environment F Fahrenheit FAF Fatigue Analysis Factor FMEA Failure Modes & Effects Analysis FOD Foreign Object Damage FOS Factor of Safety FSE Flight Support Equipment FTA Failure Tree Analysis G Gravity GFE Government Furnished Equipment GHz Gigahertz H2O Water HA Hazard Analysis HDBK Handbook HIDH Human Integration Design Handbook HITL Human in the Loop HP High Pressure HSIR Human System Integration Requirements Hg Mercury Hi High Hz Hertz I Inspection IAPFR Interoperable Articulating Portable Foot Restraint ICD Interface Control Document ID Identification IEEE Institute of Electrical and Electronic Engineers ISO International Organization for Standardization ISS International Space Station ITAR International Traffic in Arms Regulations IVA Intravehicular Activity JP8 JSC Standard 8080 JSC Johnson Space Center K Kilo L&R left and right LCVG Liquid Cooling and Ventilation Garment LEO Low Earth Orbit

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LET Linear Energy Transfer LSS Life Support System LiOh Lithium Hydroxide Lo Low M&P Materials and Processes MAC Medium Access Control MCC Mission Control Center MCP Materials Control Plan MDP Maximum Design Pressure MDS Maximum Design Speed MEP Maximum External Pressure MHz megahertz MIL Military MKS Meter-kilogram-second MMOD Micro Meteoroid and Orbital Debris MOD Mission Operations Directorate MRT Modified Rhyme Test MS Margin of Safety MTBF Mean Time Between Failure MWS Mini Work Station Max Maximum MeV Mega electron Volt Min Minimum N2 Nitrogen NASA National Aeronautics and Space Administration NBL Neutral Buoyancy Laboratory NDE Non Destructive Evaluation NIEL Non-Ionizing Energy Loss NIST National Institute of Standards and Technology NPD Negative Pressure Differential NS Not Specified NaCl Sodium Chloride O2 Oxygen OII Oceaneering International, Inc. ORU Orbital Replacement Unit OSS Oceaneering Space Systems Ops Con Operation Concept P-P Peak To Peak P/N Part number PCAI Power, Control, and Avionics Informatics PDR Preliminary Design Review PGS Pressure Garment Subsystem PGT Pistol Grip Tool PHY Physical Layer

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PLSS Portable Life Support System PMAD Power Management and Distribution PNP Probability of No Penetration PRA Probabilistic Risk Assessment PRF Performance PTRS Project Technical Requirements Specification PTT Push To Talk RAM Reliability, Avilablility and Maintainability RCA Rapid Cycle Amine RCV Receive RF Radio Frequency RFID Radio Frequency Identification RH Relative Humidity RID Review Item Discrepancy RMS Root Mean Square ROD Review Of Design ROM Range of Motion RV Relief Valve S/N Serial Number SAFER Simplified Aid for EVA Rescue SCD Specification Control Drawing SEE Single Event Upset SI International System of Units SIP Suitport Interface Plate SOW Statement of Work SPCE Servicing, Performance and Checkout Equipment SPE Solar Particle Event SPL Sound Pressure Level SSER Space to Space EMU Radio SSP Space Shuttle Program STD standard (as in document) STS Shuttle Transportation System SWME Spacesuit Water Membrane Evaporator T Test TBD To be Determined TBR To be resolved TDS Task Description Sheet TFR Translational Foot Restraint THL Toxicity Hazard Level TID Total Ionizing Dose TMG Thermal Micrometeoroid Garment U.S. United States U5 Update 5 U5I Update 5 Interface

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UCB Umbilical Connector Block UHF Ultra High Frequency USML United States Munitions List UV Ultraviolet V Volt VC Visibly Clean VOX Voice Activated Vdc Volts direct current Vp-p Volts peak to peak W Watts XMT Transmit acfm Actual Cubic Feet Per Minute centigray cGy cm centimeter dB decibels dBm decibel per meter e.g. For Example ft/s Feet per second hr Hour in inch kJ/kg Kilo Joules per kilo gram kPa kilopascal kg Kilograms lb pound lbf pounds force lbm pounds mass mA milliAmperes mg/L Milligrams per Liter microfarad uF milli Second mSEC ml Milliliter mmHg Millimeters of mercury nm nanometer ppO2 Partial Pressure of Oxygen ppm parts per million psi pounds per square inch psia pounds per square inch absolute psid pounds square inch differential psig pounds per square inch gauge scc Standard Cubic Centimeter scfm Standard Cubic Feet Per Minute sec second

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1.0 Introduction The purpose of the Constellation Space Suit System (CSSS) Program is to develop an effective, safe, affordable, reliable, space suit and sustainable architecture to conduct human exploration across the solar system. Development of a next generation space suit is required to enable safe and efficient EVA operations at multiple destinations envisioned by NASA for human space exploration. This Configuration End Item (CEI) document is written to define the requirements for the design, manufacture, test, certification, and delivery of an ISS Umbilical Assembly for the next generation EVA Space Suit for Exploration.

1.1 Purpose The purpose of this document is to define the performance, design, interface, and verification specifications necessary to develop and deliver an ISS Umbilical Assembly used for on-orbit operations in the ISS Airlock.

1.2 Scope This document establishes the design and performance specifications controlled by the CSSS contract for the ISS Umbilical Assembly, one of the configuration end items that make up the Exploration Extravehicular Activity (EVA) Suit. Unless otherwise stated, requirements contained herein apply to a fully configured, flight certified Suit.

1.3 Reserved 1.4 Conventions and Notations 1.4.1 "Shall", "Should", and "Will" The convention used in this document to indicate requirements, goals, and statements of fact is as follows: "Shall" used to indicate a requirement that must be implemented and its implementation verified "Should" used to indicate a goal that must be addressed by the design but is not formally verified "Will" used to indicate a statement of fact and is not verified

1.4.2 "TBX", "TBD" and "TBR" In some cases the values of quantities included in this document have not been established and are designated as "to be determined" (TBD) or "to be resolved" (TBR). In instances where approximate values of such quantities are known and provide useful guides for development, these are shown along with the TBR notation. Specifications containing these unknown values are called "TBX". Each requirement that contains a TBX has the assigned TBX identifier appended to the requirement in {brackets}; e.g., {TBX.0004}. Under no circumstance will flight equipment be built to a requirement containing a TBR or TBD.

1.4.3 Requirement Identification and Ownership Requirements included in this document are identified using an UMB.nnn format designator, where the prefix identifies the requirement as an Umbilical requirement and nnn is a sequentially




assigned number. Complementary verification requirements are identified with a .V suffix. The UMB.nnn identifier also serves as the unique identifier in the CRADLE requirements management application. This CEI is assigned the 205 identifier in the CSSS product breakdown structure.

1.4.4 Naming Conventions This draft document uses the terms EVA Space Suit, Suit, EXS suit and Microgravity Suit interchangeably. Collectively the naming convention used is the Suit. The term "occupied" is used to indicate the suit contains a human "occupant.' This may be a crew member or a non-crewmember such as a test subject or a trainee. The term is gender neutral unless specifically noted otherwise. For the purpose of this specification: The terms 'Umbilical', ‘Recharge Umbilical’ and 'Umbilical Assembly' are used interchangeably.

1.4.5 Use of Measurement Units U.S. Customary or SI units are used as the design units for the document and the mixed units are only allowed in circumstances where another standard using those units is cited (e.g. DIN connectors, requirements, metric or US fastener systems, etc.). Measurement units may be in either SI or U.S. Customary, except that mixing of units within a given category (e.g. dimensional, mass (weight), strength, etc.) is not allowed. Further definition and application is located in CSSS Engineering Record: Implementation of US Customary Units on the Constellation Space Suit System - 106CSS048.

1.4.6 Requirement Traceability Parent requirements are identified in brackets at the end of the unit requirement. Appendix C contains a summary of unit specifications to the parent requirement. For a complete traceability report consult the most recent CSSS traceability report. (Data Requirements Description (DRD) deliverable CSSS-T-004) Unit specifications without parent requirements are derived as part of the design.

1.4.7 Rationale To aid the designer, some (not all) requirements may include a Rationale paragraph to provide origin details and aid in interpretation of a requirement. The Rationale is not part of the requirement and is not intended to supersede or augment the requirement.




1.5 Change Authority / Responsibility OII is responsible for approval of the initial release of this specification and for subsequent changes or revisions until the document is formally delivered to NASA and a NASA approved baseline is established.

1.5.1 Order of Precedence This document provides a set of requirements for designing the Exploration EVA Space Suit to approved applicable documents. Unless otherwise noted herein or in the contract, in the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Resolution of any precedence conflicts are accomplished through the use of waivers and deviations. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

2.0 Documents The documents listed in this section represent the documents that have been identified either in part or in whole within this document.

2.1 Applicable Documents The following documents, of the exact issue shown, form a part of this specification to the extent specified herein (i.e., "shall" statements). Any documents referenced within the following documents are not considered applicable unless also included explicitly in the following list. When the requirements of any of the documents so specified conflict with the requirements of this specification, the requirements of this specification shall take precedence.

Table 2.1-1: Applicable Documents Document Number Version Title

AIAA NAS 412 Foreign Object Damage/Foreign Object Debris (FOD) Prevention

ASTM E1548 Standard Practice for Preparation of Aerospace Contamination Control Plans

CSSS-S-011 Latest Electrical, Electronic, and Electromechanical (EEE) Parts Control Plan

CSSS-T-006 Unreleased Contractor Master Verification Plan CSSS-T-012 Unreleased Material Usage Agreements (MUAs) CSSS-T-013 Unreleased Materials Identification and Usage List (MIUL) CSSS-T-014 Unreleased Exploration Space Suit Contamination Control Plan CSSS-T-015 Unreleased Exploration Space Suit Non Destructive Evaluation Plan CSSS-T-054 Unreleased Exploration Space Suit Fracture Control Plan D-0520227 Exploration Suit Environments Definition Document D-0554450 Unreleased CSSS Component and Mechanism Design Requirements

Document D-0555960 Unreleased Constellation Space Suit Systems Part Marking Plan. ICD-4-0075-0C-0 SPCE/EMU ICD JSC STD 8080 JSC Design and Procedural Standards JSC-33237 UIA-to-Airlock ICD JSC-33277 SPCE PTRS




Document Number Version Title JSC-33281 UIA CEI Specification JSC-65828 Revision A JSC 65828, Structural Design Requirements and Factors of

Safety for Space Flight Hardware MIL-HDBK-6870A Inspection Program Requirements, Nondestructive for

Aircraft and Missile Materials and Parts MIL-PRF-27210 Rev H Performance Specification Oxygen, Aviator’s Breathing,

Liquid and Gas NASA-STD-5009 Nondestructive Evaluation Requirements for Fracture-

Critical Metallic Components NASA-STD-5017 Design and Development Requirements for Mechanisms NASA-STD-5019 Fracture Control Requirements for Spaceflight Hardware NASA-STD-6016 Standard Materials and Processes Requirements for

Spacecraft NASA-STD-4003A Rev A Electrical Bonding for NASA Launch Vehicles,

Spacecraft, Payloads and Flight Equipment NASA/SP-2010-3407 Human Integration Design Handbook (HIDH) SNC-C-005 Shuttle Cleanliness SSP 50260 Rev C International Space Station Medical Operations

Requirements Document (ISS MORD) SSP 50808 International Space Station (ISS) Commercial Orbital

Transportation Services (COTS) Interface Requirements Document (IRD)

SSP 50835 Rev C ISS Common IRD

2.2 Reference Documents The documents listed below were referenced in the preparation of this specification.

Table 2.2-1: Reference Documents Document Number Version Title

AIAA NAS 412 Foreign Object Damage/Foreign Object Debris (FOD) Prevention

ASTM E1548 Standard Practice for Preparation of Aerospace Contamination Control Plans

CTSD-ADV-1008 Shock Hazards during EVAs CxP 70044 Constellation Program Natural Environment Definition for

Design (NEDD) JSC STD 8080 JSC Design and Procedural Standards JSC-28918 Basic Release EVA Design Requirements Considerations JSC-33237 UIA-to-Airlock ICD JSC-33281 UIA CEI Specification JSC-65828 Revision A JSC 65828, Structural Design Requirements and Factors of

Safety for Space Flight Hardware NASA SP-8077 Sep 1971 Transportation and Handling Loads




Document Number Version Title NASA-STD-3001 V2 NASA Space Flight Human-System Standard Volume 2:

Human Factors, Habitability, and Environmental Health PRACA B-EMU-A0007

Contamination Control Cartridges Installed Backwards

SF24-09-023 23 FEB 2009 Review of Constellation Program Space Suits Cleaning Criteria

SLS-SPEC-159 Cross-Program Design Specification for Natural Environments for Aerosol Environments for Ground Operations at KSC

SSP 50808 International Space Station (ISS) Commercial Orbital Transportation Services (COTS) Interface Requirements Document (IRD)

SSP 50835 Rev C ISS Common IRD SVHS7894 EMU Environments Definition Specification

3.0 Requirements 3.1 Description of the ISS Umbilical Assembly When connected to the Exploration Spacesuit, the ISS Umbilical Assembly’s main functions are recharging the Portable Life Support System (PLSS) oxygen tanks and the Feedwater Supply Assembly, transporting vehicle cooling water for thermal control of the suit, transmitting hardline communications/data between the suit and vehicle, transmitting power to operate the suit and charge the suit batteries, and providing vacuum access for carbon dioxide and water vapor rejection by the PLSS swing beds. The Umbilical Assembly consists of high pressure oxygen, water and vacuum lines, a wire bundle, the umbilical recharge connector (URC) for connecting to the suit, the vehicle side connectors for semi-permanently connecting to the vehicle, a data interface for connecting the suit servicing laptop to the suit via the umbilical, and a switch for activating the Push-To-Talk (PTT) audio communications mode.

3.2 Performance UMB.046 Unassisted Operations The Umbilical Assembly shall accommodate unassisted operation of on-orbit EVA Umbilical functions. [EXS.0046] UMB.078 On-Orbit Alignment Features The Umbilical shall incorporate alignment features into the hardware where on-orbit alignment is required for operations, maintenance, assembly or sizing. Rationale: Ensures that: Mechanical systems requiring accurate alignment, adjustment, or rigging of the system or system components incorporate provisions allowing for such alignment, adjustment or rigging to be made without the removal of the system, any of its components, or any neighboring hardware.




Where the actual alignment, adjustment, or rigging equipment is not incorporated into the flight hardware, provisions for mounting and using the necessary alignment, adjustment or rigging equipment are incorporated into the flight system. Where in-flight alignment, adjustment, or rigging is required, such capability is incorporated into the flight hardware. If in-flight alignment, adjustment, or rigging requires tooling, the tools are standard tools.

[EXS.0078]

UMB.137 Allowable Pressure Drop The Umbilical shall have an allowable pressure drop through the water loop of TBD psi.

[EXS.0112] {TBX.0119}

3.2.1 Reserved 3.2.2 Maintenance UMB.108 In-flight Maintenance and Replacement The Umbilical hardware shall be designed for in-flight maintenance, including Umbilical replacement and repair, while utilizing only standard tools already available on ISS. Rationale: Past experience has shown that sparing parts versus entire systems is much more logistically efficient for space flight hardware designs, specifically with regards to designs that are potentially unique and conformal to each crewmember. The suit should be designed to allow for the capability for change out and repair of components.

[EXS.0108] [EXS.0109] {TBX.0111}

UMB.149 Installation Design Umbilical assembly and maintenance items shall be designed such that they cannot be installed in a non-operational orientation. Rationale: PRACA B-EMU-000-A007 - Following STS-114 return of EMUs from ISS it was noted that the Contamination Control Cartridges were installed backwards. This requirement applies to all maintenance components that may be installed incorrectly. This supplements the fluid and electrical connector requirements. Possible design features include installation keying or shapes, installation labeling, or multi-directional installation. The use of testing to ensure proper mechanical installation is less desirable.

[EXS.0149]




UMB.234 ORU Captive Fasteners All fasteners on Umbilical On-Orbit Replaceable Units (ORU) shall be captive.

[EXS.0234]

3.2.3 Reserved 3.2.4 Product Life UMB.047 Umbilical/PLSS Interface Mechanical Components Mate/Demate Cycles The Umbilical mechanical components shall meet structural and functional requirements after a minimum of 750 (TBR) cycles with preventive or limited life maintenance. Rationale: The cycles account for each specific flight unit cycling on ground and on-orbit.

[EXS.0173] {TBX.0093}

UMB.048 Umbilical/Vehicle Interface Mechanical Components Mate/Demate Cycles The Umbilical/Vehicle mechanical components shall meet structural and functional requirements after a minimum of (TBD) cycles with preventive or limited life maintenance. Rationale: The cycles account for each specific flight unit cycling on ground and on-orbit.

[EXS.0173] {TBX.0093}

UMB.049 Umbilical/Vehicle Interface Electrical Connectors Mate/Demate Cycles The Umbilical Electrical connectors shall meet structural and functional requirements after a minimum of (TBD) mate/demate cycles with preventive or limited life maintenance. Rationale: The cycles account for each specific flight unit cycling on ground and on-orbit.

[EXS.0173] {TBX.0093}

UMB.050 Umbilical/PLSS Interface Electrical Connectors Mate/Demate Cycles The Umbilical Electrical connectors shall meet structural and functional requirements after a minimum of 750 (TBR) mate/demate cycles with preventive or limited life maintenance. Rationale: The cycles account for each specific flight unit cycling on ground and on-orbit.

[EXS.0173] {TBX.0093}

UMB.171 Continuous On-Orbit Service Life The Umbilical shall have a minimum on-orbit, continuous design life of 6 years or 936 hours (TBR) of pressurized time at standard ambient temperature and pressure, whichever event occurs first.




Rationale: Service life consists of the time period which begins with the launch of a unit to orbit and expires when either chronological time or pressurized time is exceeded. As an on-orbit requirement, pressurized time on ground does not apply to meeting this requirement. Suit design life is based on 78 EVAs at 8 hours each. Each EVA is estimated to have 10 hours of recharge time and 2 hours of setup and cleanup time associated with each EVA. The umbilical is not used during a nominal EVA, so its usage is 10+2=12 hours/EVA * 78 = 936 hours.

[EXS.0171]

UMB.173 Preventive Maintenance Constraints The Umbilical shall require no preventive or limited life maintenance during a single 12 month period or before 25 eight hour EVAs. Rationale: This requirement addresses the desire to design Umbilical hardware such that failures will not occur nor will maintenance be required during a 12 month period. Corrective maintenance, pre-operational and post-operational preparation procedures and consumable items identified in the Limited Life Items List (LLIL)are exempt from this requirement.

[EXS.0173]

3.2.5 Reserved 3.2.6 Reserved 3.3 Physical Characteristics UMB.327 Umbilical transfer through hatch The Umbilical outer mold line dimensions shall permit the Umbilical passage through a 31.5 inch diameter hatch of existing docking ports. Rationale: Crew must be able to transfer the umbilical assembly. International Docking System Standard Pass-Through requirement is 31.5 inches.

[EXS.0327]

3.3.1 Mass UMB.062 Umbilical Dry Mass The Umbilical shall have a dry mass of equal to or less than 35 lbm (TBR). Rationale: Dry mass is defined as an uncharged unit, without water or oxygen, as well as without any tools or other ancillary hardware. The umbilical mass is based on a nominal overall length of 20 feet and accounts for:

- an Umbilical Recharge Connector (URC) on the suit end of the Umbilical - a modified UCM on the vehicle end of the Umbilical - a high pressure O2 connector on the vehicle end of the Umbilical - 2 3/8" ID x 24.0' L cooling water hoses with fittings on each end - 1 5/8" ID x 24.0' L vacuum hose with fittings on each end - 1 1/4" ID x 24.0' L high pressure O2 hose with fittings on each end




- 1 24.0' L multi-conductor, shielded comm/data cable assembly with connectors on each end - 1 24.0' L multi-conductor, shielded power cable assembly with connectors on each end - 1 20.0' L MLI cover - 1 21.0' L Nomex tether - 2 crew hooks

[EXS.0353] {TBX.0064}

3.3.2 Product Marking UMB.183 Part Identification Marking Umbilical parts shall be visibly marked per D-0555960, CSSS Part Marking Plan. Rationale: Part marking is critical to suit operations and logistics. It is important that numbers and names match the manifests and procedures to ensure proper configurations are assembled and used. There is anecdotal evidence that on-orbit suit parts are difficult to identify by the correct part numbers due to a proliferation of labels on parts from various vendors as they are assembled. If bar codes, UIDs or RFID tags are required they will be specified.

[EXS.0183]

UMB.184 Part Marking on Drawings Locations of Umbilical part markings and method of application shall be identified on engineering drawings per D-0555960, CSSS Part Marking Plan. Rationale: Part marking is critical to suit operations and logistics. It is important that numbers and names match the manifests and procedures to ensure proper configurations are assembled and used. There is anecdotal evidence that on-orbit suit parts are difficult to identify by the correct part numbers due to a proliferation of labels on parts from various vendors as they are assembled.

[EXS.0184]

3.3.3 Cleanliness UMB.115 Elevated Pressure Oxygen Loop Cleanliness All Umbilical oxygen wetted components whose operational pressure exceeds 30 psia pp02, shall meet a minimum cleanliness level of 100A per the Exploration Space Suit Contamination Control Plan (CSSS-T-014). Rationale: Parent requirement specifies cleanliness per a Shuttle document (SNC-C-005). Document D-0335631, Contract DRD CSSS-T-014, is the Exploration Suit Prime Contract required implementation of the requirements of NASA-STD-6016, Standard Materials and Processes Requirements for Spacecraft , ASTM E1548 for contamination control, and AIAA NAS 412 for Foreign Object Damage (FOD) control.

[EXS.0115]




UMB.116 Cooling Water Loop Cleanliness The Umbilical cooling water loop components internal cleanliness shall meet a minimum level of 150A per the EXS Contamination Control Plan (CSSS-T-014). Rationale: Parent requirement specifies cleanliness per a Shuttle document (SNC-C-005). Document D-0335631, Contract DRD CSSS-T-014, is the Exploration Suit Prime Contract required implementation of the requirements of NASA-STD-6016, Standard Materials and Processes.

[EXS.0116]

UMB.237 Low Pressure Oxygen Loop Cleanliness All Umbilical oxygen wetted components whose operational pressure is less than or equal to 30 psia pp02, shall meet a minimum cleanliness level of Visibly Clean (VC) Sensitive per the EXS Contamination Control Plan (CSSS-T-014). Rationale: Parent requirement specifies cleanliness per a Shuttle document (SNC-C-005). Document D-0335631, Contract DRD CSSS-T-014, is the Exploration Suit Prime Contract required implementation of the requirements of NASA-STD-6016, Standard Materials and Processes Requirements for Spacecraft , ASTM E1548 for contamination control, and AIAA NAS 412 for Foreign Object Damage (FOD) control.

[EXS.0237]

UMB.354 Preflight/Ground Fungal Limit The materials selected for the wetted components of the Umbilical assembly shall be capable of being cleaned to a maximum Fungi contamination level of 10 colony forming units (CFUs)/100 cm2. Rationale: These limits are intended to ensure that microbial and fungal contamination on surfaces can be removed to mitigate the risk of contamination to the crew and/or support personal prior to flight, and are consistent with NASA-STD-3001 [V2 6056].

[EXS.0354]

UMB.355 Preflight/Ground Microbial Limit The materials selected for the wetted components of the Umbilical assembly shall be capable of being cleaned to a maximum microbial contamination level of 500 colony forming units (CFUs)/100 cm2. Rationale: These limits are intended to ensure that microbial and fungal contamination on surfaces can be removed to mitigate the risk of contamination to the crew and/or support personal prior to flight, and are consistent with NASA-STD-3001 [V2 6056].

[EXS.0354]




UMB.356 On-orbit Fungal Limit The Umbilical assembly shall be capable of being cleaned to a maximum fungal concentration level of 100 CFU/100 cm2 prior to manned testing/usage using a procedure approved for on orbit use.

[EXS.0355]

UMB.357 On-orbit Microbial Limit The Umbilical assembly shall be capable of being cleaned to a maximum microbial concentration level of 10,000 CFU/100 cm2 prior to manned testing/usage using a procedure approved for on orbit use.

[EXS.0355]

3.4 Interfaces The Umbilical physical interfaces with the vehicle and other EXS Suit CEIs are shown in the PLSS External Interface table and figure. UMB.001 Umbilical External Interfaces The Umbilical shall accommodate external interfaces with the items listed in the Umbilical External Interface Table and Figure. Rationale: The Table defines mechanical, electrical and physical external interfaces between the Umbilical and other CEIs, vehicle or environment and provides a reference to the corresponding products such as drawings, Interface Control Documents (ICDs), etc.

[EXS.0110] [EXS.0117] [EXS.0119] [EXS.0123] [EXS.0124] [EXS.0125] [EXS.0126] [EXS.0128] [EXS.0147] [EXS.0154] [EXS.0193] [EXS.0250] [EXS.0251] [EXS.0318] [EXS.0323] [EXS.0325] [EXS.0326]




Figure 3.4-1: EXS.1.205 Vehicle Umbilical (FSE)

Table 3.4-3: External Interfaces

Name I/F Type Description Products ENET2/ISS Data Interface Elec - Data Ethernet interface from

umbilical to the ISS Laptop.

ENET2/PLSS Data Interface

Elec – Data Ethernet interface from PLSS to the umbilical.

ISS Audio In Elec - Signal Hardline audio signal (pair of pins) produced by Suit and sent to ISS. Called Hardline Audio Out by ISS SPCE ICD.

ISS Audio Out Elec - Signal Hardline audio signal (pair of pins) produced by ISS and sent to Suit. Called Hardline Audio In by ISS SPCE ICD.

ISS Audio shield Elec - Other Audio signal shield connection between the ISS and the umbilical vehicle side connector.

ISS Cooling Water Return Fluid - Liquid

Cooling water returned by suit to ISS for cooling. Suit provides cooling loop pump power. Water is cooled by the ISS Heat Exchanger.

ISS Cooling Water Supply Fluid - Liquid

Chilled cooling water supplied to suit by ISS. Suit provides cooling loop pump power.




Name I/F Type Description Products ISS HP Oxygen Fluid - Gas High pressure oxygen (3000 psi)

supplied by station.

ISS Hardline PTT Key ISS Safety Ground Elec - Signal For connecting suit electrical

ground to vehicle electrical ground.

ISS Suit Power Elec - Power 18.5 VDC power supplied by the ISS to the Suit. This is provided on 4 power and return pairs of connector pins at the UIA interface.

ISS Suit Power Sense Elec - Signal Vehicle supplied power sense signal.

ISS Vehicle Umbilical Strain Relief

Mechanical The UTA incorporates an attach point to accommodate strain relief for the umbilical.

ISS Vehicle Umbilical Strain Relief Attach

Mechanical The UIA has an attach point to accommodate strain relief for the umbilical.

ISS Water Drain Fluid - Liquid

Water returned by suit, shares a common line with the ISS Water Fill.

ISS Water Fill Fluid - Liquid

Consumable water supplied by ISS to suit to top off feedwater supply. Shares a common line with the ISS Water Fill.

UMB Actuation Mechanical Actuation of an umbilical connector by a gloved hand.

Umbilical Audio In Elec - Signal Umbilical Audio In signal (pair of pins) from the vehicle recharge umbilical to the PLSS.

Umbilical Audio Out Elec - Signal Umbilical Audio Out signal (pair of pins) from the PLSS to the vehicle recharge umbilical.

Umbilical Audio Shield Uncategorized

The Umbilical accommodates a signal shield line between the PLSS and the vehicle recharge interface.

Umbilical HP Oxygen Fluid - Gas The Umbilical accommodates a high pressure O2 recharge line from the vehicle recharge interface to the PLSS.

Umbilical Safety Ground Elec - Power Umbilical Safety Ground line from the PLSS to the vehicle recharge interface via umbilical.

Umbilical Suit Power Elec - Power 18.5 VDC power supplied by




Name I/F Type Description Products the ISS to the EXS via umbilical

Umbilical Suit Power Sense

Elec - Power Vehicle supplied voltage sensing signal.

Umbilical Water Return Fluid - Liquid

The Umbilical accommodates water return line from the PLSS to the vehicle recharge interface for PLSS water drainage operations.

Umbilical Water Supply Fluid - Liquid

The Umbilical accommodates a water supply line from the vehicle recharge interface to the PLSS for water fill operations.

Vacuum Access Fluid - Gas The Umbilical accommodates a vacuum line to allow operation of swing beds.

UMB.002 Mating to the ISS UIA Panel The Umbilical shall have a male electrical connector that mates to the UIA Panel J39 311P409-5S-B-12. Rationale: The connector is keyed to provide for proper alignment and polarization for mating to the UIA.

[EXS.0123] UMB.326 Umbilical Stowage During ISS EVA The EVA umbilical shall be stowed in the crew lock during an EVA. Rationale: Establishes environment for the umbilical during an EVA. The umbilical will be connected and disconnected while the crew member is in the ISS crew lock. Other stowage arrangements will be provided as required for other vehicles.

[EXS.0326]

3.4.1 Vehicle Umbilical Fluid Interfaces UMB.061 Umbilical Water Quality The Umbilical wetted components shall be compatible with contaminants present in the water as defined in the Umbilical Supply Water table. Rationale: The Umbilical needs to be robust in regards to acceptable water quality such that contaminants will not foul or degrade performance of the system.

Table 3.4-1: Umbilical Supply Water Table Contaminants Amount (mg/L) Barium 0.1 Calcium 1




Contaminants Amount (mg/L) Chlorine 5 Chromium 0.05 Copper 0.5 Iron 0.2 Lead 0.05 Magnesium 1 Manganese 0.05 Nickel 0.05 Nitrate 1 Potassium 5 Sulfate 5 Zinc 0.5 Organics Total Acids 0.5 Total Alcohols 0.5 Total Organic Carbon 0.3

[EXS.0061] UMB.110 HPO2 Maximum Expected Operating Pressure (MEOP) The HPO2 portion of the umbilical assembly shall have a Maximum Expected Operating Pressure (MEOP) of 3000 +0/-150 psia. Rationale: The specified pressure is the pressure supplied to the umbilical via the updated ISS UIA panel. It is the expectation that the contractor will design the system to a 3000 psia capability.

[EXS.0110]

UMB.111 Umbilical HP O2 Leakage When Attached to Vehicle The umbilical when attached to the Umbilical Interface Panel shall have an external O2 leakage rate that does not exceed 9 scch at 3000 psia and 70 ºF. Rationale: For reference, the ISS external leakage requirement for the IEU is 3 scch O2 at 1050 psia and 70 ºF while attached to the UIA. As the supply pressure increases to 3000 psia, the external leakage increases as well.

[EXS.0111]

UMB.112 Umbilical Vacuum Leakage When Attached to Vehicle and Demated from Suit

The vacuum portion of the umbilical shall have a gas leakage less than TBD SCC/M when the umbilical is attached to the ISS vacuum port, the suit end of the umbilical is demated from the suit and the airlock is at 14.7 psia. Rationale: The umbilical may be left for long periods attached to the ISS UIA but not to the suit, requiring low leakage rates to avoid depleting station resources.




[EXS.0111]

UMB.114 Umbilical Vacuum Leakage When Attached to Vehicle and Mated to Suit

The vacuum portion of the umbilical shall have a gas leakage less than TBD SCC/M when the umbilical is attached to the ISS vacuum port, the suit end of the umbilical is mated to the suit and the airlock is at 14.7 psia. Rationale: Minimal leakage is required into the vacuum line while operating in order for the swing beds to desorb effectively.

[EXS.0111] UMB.113 Umbilical Cooling Water Leakage When Attached to Vehicle The combined umbilical cooling water leakage and feedwater leakage shall not exceed 0.24 cc/hr water at 28.1 psig and 70 F when the umbilical is attached at the ISS Umbilical Interface Assembly and the suit end of the umbilical is demated. Rationale: The umbilical may be left for long periods attached to the ISS UIA but not to the suit, requiring low leakage rates to avoid depleting station resources. The feedwater and cooling fluid paths are joined in the umbilical assembly, so the leakage rate is determined by adding together the acceptable feedwater and cooling fluid leakage rates of 0.16 and 0.08 cc/hr. Because the loop pressure is determined by the suit, the suit's pressure is used in the requirement.

[EXS.0113]

UMB.117 Feed Water Recharge MEOP The Umbilical feedwater recharge line shall have a Maximum Expected Operating Pressure (MEOP) of 39 psid. Rationale: Control of the supply and return is provided at the Vehicle Interface Umbilical Assembly. Airlock Water Re-charge Ops (A/L press.)

+17.0 psid ISS H2O Max recharge pressure +15.2 psia (airlock pressure acting on the ISS H2O water reservoir/bag) +10.0 psid head pressure from PLSS pump -8.3 psid (suit pressure differential acting on the outside of the water loop tubes) = 33.9 psid

Vacuum Water Re-charge Ops (A/L depress.) (this case would be the same as A/L press in the previous scenario.

+17.0 psid ISS H2O Max recharge pressure +15.2 psia (airlock pressure acting on the ISS H2O water reservoir/bag; is still in the pressurized side of the A/L)




+10.0 psid head pressure from PLSS pump - 3.2 psid (Contingency suit pressure when purge open; worst case scenario) = 39 psid

[EXS.0117] {TBX.0057}

UMB.118 Feed Water Biocide Concentration The Umbilical shall accept feedwater with the biocide concentrations identified in the Biocide Table for the given biocide. Rationale: Requirement permits use of iodine or silver as a biocide, but not both. Mixing of iodine and silver biocides forms solids that contaminate the system. Reference JSC 33237 ISS Airlock to UIA ICD 3.2.5.1.5 and 3.2.5.1.6 and ICD-04-0075-0C-0 SPCE/EMU ICD.

Table 3.4-2: Biocide Concentration

Silver Concentration

Iodine Concentration

Silver Biocide 0.1 - 0.3 ppm 0 Iodine Biocide 0 0.5 - 4.0 ppm

[EXS.0118]

UMB.270 Vehicle Supplied Oxygen Standards The Umbilical shall accommodate O2 with a purity level of 99.5% as defined in MIL-PRF-27210G, Type 1, Aviator’s Breathing Oxygen. Rationale: This requirement sets the standard for the quality of oxygen supplied to the suit by the vehicle.

[EXS.0270]

UMB.324 HP O2 Pressure Rise Rate The Umbilical shall limit HP O2 pressure rise rate to 418 psi O2/second maximum given an O2 flow rate of 0 to 7.1 pounds per hour (pph) at a temperature of 60 +40/-20 ºF. Rationale: Requirement is intended to limit the velocity of the gas entering the suit to reduce potential for flammability.

[EXS.0324]

3.4.2 Vehicle Umbilical Electrical Interfaces UMB.126 Push-To-Talk key The Umbilical shall accommodate a hardline key (Push-To-Talk) signal to the vehicle.




Rationale: Push-To-Talk is needed to allow the crewmember to transmit to MCC, when using hardline comm on the umbilical.

[EXS.0254]

UMB.119 Umbilical External Power The Umbilical shall receive external power from the vehicle as identified in the External Power table. Rationale: Voltage requirements extracted from the SPCE PTRS (JSC3327). The values provided in the SPCE ICD are oriented towards specific EMU operating modes not necessarily applicable to the Suit.

Table 3.4-4: External Power Parameter Value Notes Supplied Voltage 18.5 ± 0.5 VDC Nominal Current 6.5 Amps Peak Current 7.5 Amps Supplied Voltage Limiting 22 VDC Supplied Current Limiting 11 Amps

[EXS.0119]

UMB.121 Electrical Path Resistance The Umbilical electrical interface to the Vehicle shall not exceed 0.15 ohms for each power and return path inclusive of umbilical connectors. Rationale: Requirement specifically applied to Recharge Umbilical wiring and connector pins.

[EXS.0121]

UMB.123 Umbilical to Vehicle Electrical Interface Pin Assignments The Umbilical shall receive and provide signals to the Vehicle as shown in the Umbilical to Vehicle Electrical Pinout Table.

Table 3.4-5: Umbilical to Vehicle Electrical Pinout Table Umbilical to Vehicle Electrical Pinout

Table Pin Signal Name

UIA Umbilical Connector (P/N 311P409-5P-B-12)

14 Suit Power1)




Umbilical to Vehicle Electrical Pinout Table

Pin Signal Name 30 Suit Power Return1) 15 Suit Power1) 31 Suit Power Return1) 16 Suit Power1) 32 Suit Power Return1) 17 Suit Power1) 33 Suit Power Return1) 38 Safety Ground 39 Hardline Audio In Lo 23 Hardline Audio In Hi 22 Hardline Audio Out Lo 7 Hardline Audio Out Hi 2 Suit Power Sense Hi 4 Hardline Key2) 5 Hardline Key Return2) 20 Sense Return 21 Signal Shield

Laptop Connector (P/N TBD) TBD Ethernet TX+ TBD Ethernet TX- TBD Ethernet RX+ TBD Ethernet RX-

1)4 pairs of power lines on vehicle side spliced into two pairs on suit side. 2)Hardline key signal originates from switch on umbilical and does not go to the suit.

[EXS.0123] [EXS.0124] [EXS.0125] [EXS.0126] [EXS.0128] {TBX.0118}

UMB.124 Provide Hardline Audio to Vehicle

The Umbilical shall provide a hardline Audio signal to the Vehicle SPCE in conformance with the Hardline Audio Out table.




Rationale: Audio output from the Suit to the UIA in the Airlock. Values in table are from EVA Console Handbook. SPCE ICD (ICD-4-0075-0C-0) assumes that audio is coming directly from microphone.

Table 3.4-6: Hardline Audio Out Parameter Value Notes

Frequency 300- 5000 Hz Level -2 ± 3 dBm 1.2 to 2.5 Vp-p across 600 ohms Impedance 600 Ohms ±10% Balanced and DC Isolated

[EXS.0124] UMB.125 Receive Hardline Audio From Vehicle The Umbilical shall receive a hardline Audio signal from the Vehicle SPCE in conformance with the Hardline Audio In table. Rationale: Audio input from the UIA in the Airlock to the Suit. Values in table are from EVA Console Handbook. The SPCE ICD (ICD-4-0075-0C-0) assumes that audio is going directly to the speaker/earpiece. TBR is to determine final characteristics of interface.

Table 3.4-7: Hardline Audio In Parameter Value Notes

Frequency 300-3000 Hz Level 27 ± 3 dBm 34.7 to 69.3 Vp-p across 600 ohms Impedance 600 Ohms ±10% Balanced and DC Isolated

UMB.126 Push-To-Talk Signal The Umbilical shall accommodate a hardline key (Push-To-Talk) signal to the vehicle. Rationale: Push-To-Talk is needed to allow the crewmember to transmit to MCC, when using hardline comm on the umbilical.

[EXS.0254] [EXS.0125]

UMB.128 Exchange Hardline Data with Vehicle The Umbilical shall provide a 4-wire 100BASE-TX Ethernet data interface between the Suit and a vehicle supplied laptop.




Rationale: The ability to reprogram devices and update software is needed for maintenance. Updates can be applied when the suit is not in use. Changes to configuration data and software patches are included in the scope of software updates.

[EXS.0128] UMB.328 Push-To-Talk Switch The umbilical shall provide a push-to-talk control accessible to the occupant during operations with the umbilical connected to the suit. Rationale: Push to talk is an ISS feature that reconfigures the comm loop when operating on the ISS umbilical. It needs to be accessible by the operator when suited up and connected by the umbilical.

[EXS.0254]

3.4.3 Umbilical PLSS Electrical Interfaces UMB.122 Umbilical to PLSS Electrical Pin Assignments The Umbilical shall receive and provide signals to the PLSS as shown in the Umbilical to Suit (SRC) Electrical Pinout Table.

Table 3.4-8: Umbilical to Suit (SRC) Electrical Pinout Table Umbilical to Suit (SRC) Electrical

Pinout Table Pin Signal Name

Connector 1 (P/N TBD) TBD Suit Power 1 TBD Suit Power 1 Return TBD Suit Power 2 TBD Suit Power 2 Return TBD Safety Ground

Umbilical to Suit (SRC) Electrical

Pinout Table Pin Signal Name

Connector 2 (P/N TBD) TBD Hardline Audio In Lo TBD Hardline Audio In Hi TBD Hardline Audio Out Lo TBD Hardline Audio Out Hi TBD Signal Shield




TBD Ethernet TX+ TBD Ethernet TX- TBD Ethernet RX+ TBD Ethernet RX- TBD Suit Power Sense hi TBD Sense Return

[EXS.0123]

3.4.4 Umbilical PLSS Fluid Interfaces 3.4.5 Reserved 3.4.6 Reserved 3.4.7 Reserved 3.4.8 Reserved 3.5 Design and Construction UMB.035 Pyrotechnic Devices Prohibited The Umbilical assembly design shall perform all functions without the use of pyrotechnical devices.

[EXS.0035] UMB.298 Small Diameter Critical Seal Redundancy Critical Umbilical seals with a major outer diameter less than or equal to 0.5 inches shall have a minimum of one seal at the interface. Rationale: JSC 65828 3.2.14.1 [STR0035] This requirements applies to feed-through connection, rotary, window, hatches/doors, mating mechanisms, and structural seals. Feed-Through connections include valves, gages and transducers. Critical seals should be leak tested at the assembly level after final installation prior to launch. For hatches/doors that are sealed immediately prior to launch this may constitute complete testing in the assembly building and abbreviated testing at the pad.

[EXS.0298]

UMB.299 Large Diameter Critical Seal Redundancy Critical Umbilical seals with a major outer diameter greater than 0.5 inches shall have a minimum of two seals at the interface. Rationale: JSC 65828 3.2.14.2 [STR0036] This requirements applies to feed-through connection, rotary, window, hatches/doors, mating mechanisms, and structural seals. Feed-Through connections include valves, gages and transducers. Critical seals should be leak tested at the assembly level after final installation prior to launch. For hatches/doors that are sealed




immediately prior to launch this may constitute complete testing in the assembly building and abbreviated testing at the pad.

[EXS.0299] UMB.074 Use of Self Sealing Fluid Connectors Fluid connectors specified to be mated and demated on orbit shall be self sealing. Rationale: Minimizes spillage of water when connectors are connected and disconnected.

[EXS.0074] UMB.106 Debris Protection - Mechanical Components Umbilical mechanical components shall perform nominally during and after exposure to debris or foreign material. Rationale: Acceptable protective methods include, but are not limited to, the following: 1. Design and fabricate electrical circuitry to prevent the establishment of unwanted current

paths from such debris. 2. Provide critical electrical items with debris-proof covers, suitable containers, housings,

potting, or conformal coatings. 3. Provide critical mechanical systems with debris-proof covers, shrouds, or containers that

protect the entire system prior to use, or that prevent debris from entering into critical areas of the mechanism where the debris could cause binding, jamming, or seizing.

4. Incorporate filters, strainers, traps, screens, or other devices in moving-fluid components of electrical or mechanical systems to trap debris in a manner that will eliminate it as a threat to critical mechanical or electrical components. In systems where flow reversal may occur, install such devices on both sides of critical components. Make sure all such devices are able to be cleaned in-flight and/or are able to be replaced as part of the maintenance program.

[EXS.0106] UMB.190 Connector Inadvertent Demate Umbilical connectors, designed for pressurized glove operation, shall be designed with a means to prevent inadvertent demate. Rationale: Ensures that connectors do not unintentionally come apart. This may be accomplished through the use of a locking feature of some sort, two stage actuation or two handed actuation.

[EXS.0190] UMB.191 Connector Mating Status Umbilical connectors shall be designed with a means to positively determine mated status. Rationale: Ensures that connectors are mated prior to continuing to next procedure. Implementation may be through visible means such as a band or alignment marking or indicator light or through physical means such as detents or stops that can be felt through an EVA glove.

[EXS.0191]




UMB.193 Vehicle Tether Attach Limit Load The umbilical shall have a tether capable of withstanding an axial limit load of 200 lb (890 N). Rationale: Tether provides strain relief and can prevent umbilical from whipping around in the event of a failure. On the legacy umbilical it is attached to the umbilical TMG. This interface is discussed in JSC-20597 ISS EVA Operations.

[EXS.0193] UMB.236 Comply with Component and Mechanism Design Requirements Document The Umbilical shall comply with the CSSS Component and Mechanism Design Requirements document D-055445. Rationale: This document provides the detailed requirements applicable to all the CSSS mechanism designs that will be used for intra-vehicular activity (IVA) operation and extra-vehicular activity (EVA) operation in any flight mission phase.

[EXS.0236] UMB.257 Separation of Redundant Mechanical Systems Umbilical mechanical assemblies providing redundant functions shall be separated or protected to ensure that damage to one is not likely to prevent its redundant counterpart from performing the function. This specification is not applicable to components or piece parts mounted in common housings. Rationale: For purposes of this standard, "redundancy" is defined as the ability to perform a function by more than one means. This requirement ensures that redundant systems, redundant subsystems, and redundant major elements of subsystems are separated or protected to ensure that an unexpected event which damages one is not likely to prevent the other from performing the functions. This standard is not applicable to redundant components or piece parts mounted in common housings within redundant systems, subsystems, or subsystem elements.

[EXS.0257]

UMB.292 Restraints for Flexible Hoses

Umbilical high pressure flexible hose installations shall be restrained to prevent whiplash in the event of a burst. Rationale: Requirement obtained from JSC 65828 3.2.8.9 [STR0027] SMC-S-005, Section 5.11.2 provides guidance for designing the restraints of flexible hose installations that are six feet long or greater, including factors of safety and the method to calculate the design load. The need for




restraints on flex hoses shorter than six feet should be evaluated based on the specific design and environmental conditions for each installation and the potential result of whiplash.

[EXS.0292]

3.5.1 Materials UMB.218 Materials and Processes All Umbilical parts, components and assemblies shall comply with the requirements of D-0335626, CSSS-T-011, Exploration Space Suit Materials and Processes Selection, Control, and Implementation Plan. Rationale: Document D-0335626, Contract DRD CSSS-T-011, is the Exploration Suit Prime Contract required implementation of the requirements of NASA-STD-6016, Standard Materials and Processes Requirements for Spacecraft and the applicable requirements from JSC-STD-8080, JSC Design and Procedural Standards and NASA-STD-5017, Design and Development Requirements for Mechanisms.

[EXS.0218] UMB.219 Contamination Control All Umbilical parts, components and assemblies shall be cleaned, packaged and handled in accordance with the requirements of the Exploration Space Suit Contamination Control Plan (CSSS-T-014). Rationale: Document D-0335631, Contract DRD CSSS-T-014, is the Exploration Suit Prime Contract required implementation of the requirements of NASA-STD-6016, Standard Materials and Processes Requirements for Spacecraft, ASTM E1548 for contamination control, and AIAA NAS 412 for Foreign Object Damage (FOD) control.

[EXS.0219]

UMB.220 Non-Destructive Evaluation All Umbilical parts, components and assemblies shall comply with the requirements of DRD CSSS-T-015, Exploration Space Suit Non-Destructive Evaluation (NDE) Plan. Rationale: Document D-0335633, Contract DRD CSSS-T-015, is the Exploration Suit Prime Contract required implementation of the requirements of MIL-HDBK-6870A, Inspection Program Requirements, Nondestructive for Aircraft and Missile Materials and Parts and NASA-STD-5009, Nondestructive Evaluation Requirements for Fracture-Critical Metallic Components.

[EXS.0220]

UMB.221 Fracture Control All umbilical parts, components and assemblies shall comply with the requirements of CSSS-T-054, Exploration Space Suit Fracture Control Plan. Rationale: Document D-0335633, Contract DRD CSSS-T-054, is the Exploration Suit Prime Contract required implementation of the requirements of NASA-STD-5019, Fracture Control




Requirements for Spaceflight Hardware and the applicable requirements from JSC-STD-8080, JSC Design and Procedural Standards.

[EXS.0221]

3.5.2 Electrical Design UMB.080 Mating of Electrical Connectors Electrical connectors, plugs, and receptacles shall be designed to prevent incorrect connection with other accessible connectors, plugs, or receptacles. Rationale: NASA-STD-3000 addresses mating provisions and use of constraints built into a cable or harness that locates similar connectors so they cannot be interchanged (paragraph 11.10.3.5, "Connector Identification / Alignment Design Requirements").

[EXS.0080]

UMB.097 Electrostatic Discharge Protection: Non-Operating Unpowered Umbilical electronic equipment shall meet all performance requirements after exposure to Electrostatic Discharges (ESD) less than or equal to 4000 volts to the case or to any pin on external connectors when tested using TBD criteria. Rationale: ESD voltages are the results of charges that may be accumulated and discharged from ground personnel or crew members during equipment installation or removal.

[EXS.0097]

UMB.098 Electrostatic Discharge Protection: Flight Configuration The Umbilical shall meet all performance requirements after exposure to Electrostatic Discharges (ESD) less than or equal to 16,000 volts applied to exposed surfaces while in a flight-installed configuration (both unpowered and powered) and tested using TBD criteria. Rationale: ESD voltages are the results of charges that may be accumulated and discharged from ground personnel or crew members during equipment installation or removal.

[EXS.0098]




UMB.104 Debris Protection - Electrical Critical Electrical components shall be protected such that encounters with debris or foreign material do not cause a malfunction. Rationale: Acceptable methods include, but are not limited to, the following: 1. Design and fabricate electrical circuitry to prevent the establishment of unwanted current

paths from such debris. 2. Provide critical electrical items with debris-proof covers, suitable containers, housings,

potting, or conformal coatings. 3. Provide critical mechanical systems with debris-proof covers, shrouds, or containers that

protect the entire system prior to use, or that prevent debris from entering into critical areas of the mechanism where the debris could cause binding, jamming, or seizing.

4. Incorporate filters, strainers, traps, screens, or other devices in moving-fluid components of electrical or mechanical systems to trap debris in a manner that will eliminate it as a threat to critical mechanical or electrical components. In systems where flow reversal may occur, install such devices on both sides of critical components. Make sure all such devices are able to be cleaned in-flight and/or are able to be replaced as part of the maintenance program.

[EXS.0104] UMB.139 Separation of Redundant Electrical Systems The Umbilical electrical assemblies providing redundant functions shall be separated or protected to ensure that damage to one is not likely to prevent its redundant counterpart from performing the function. This specification is not applicable to components or piece parts mounted in common housings within redundant systems, subsystems, or subsystem elements. This specification does not prevent design redundancy from being incorporated at the component or piece part level as sound practice when practical. Rationale: From JP8: For purposes of this standard, "redundancy" is defined as the ability to perform a function by more than one means.

[EXS.0139]

UMB.192 Electrical Connector Alignment Umbilical connectors shall be designed with provisions to mechanically align the connector before making the electrical path connections and break the electrical path connection before mechanically separating. Rationale: Ensures that connector electrical pins are not being used for mechanical alignment of connectors. This is also related to EXS.0084 arcing prevention.

[EXS.0192] UMB.198 Single Point Ground The Umbilical shall implement a Single Point Ground scheme for all bonded components.




Rationale: Single point grounding is a method of circuit and shield grounding in which each circuit of the system or subsystem has only one physical connection to a common reference point. Single point grounding is effective only for low frequency circuits.

[EXS.0198] UMB.199 Shock Hazard - 160 V The Umbilical shall limit the EVA crewmember's electrical exposure to 0.1 mA or less when the Umbilical is exposed to a 160V DC or AC RMS voltage source across any two metallic components. Rationale: Electrical arcing between vehicles at different potentials and at different exploration destinations is a possible hazard. This potential difference can arise as vehicles move through the plasma environment or during lunar missions when the moon travels through Earth's geomagnetic tail. In addition to the plasma hazard, other electrical hazards include mate and demate of hot connectors as well as contact with batteries and solar arrays. While procedural controls and keep out zones try to protect the EVA crewmember they cannot be enforced in all situations and do not protect from incidental contact. The EMU had no shock protection requirements when it was designed, which translated into development and flight of several pieces of hardware on ISS to mitigate the risk. For future EVA missions it is desirable for the suit to mitigate any shock hazards from the vehicle and/or environment. 160V corresponds to the ISS power supply voltage; 0.1 mA is considered a relatively safe number in a worse case exposure event across the chest. For comparison purposes, the startle reaction threshold is approximately 0.5-2.0 mA depending on frequency. More information related to shock hazards can be found in CTSD-ADV-1008, Shock Hazards during EVAs, Shane McFarland, 2012.

[EXS.0199] UMB.200 Bonding Class Types The Umbilical shall meet bonding class S (TBD) per NASA-STD-4003A, sections 4.1.3, 4.1.4, and 4.1.6 respectively. Rationale: Electrical bonding is the process of providing good electrical connection across mechanical interfaces to minimize electrical potential differences between equipment and individual parts of structure. Good electrical bonding provides: - Fault current paths for protection against fire and personnel shock - A low impedance bond path for antenna installations to ensure no degradation of acceptable

performance and to protect the antenna element from damage caused by P-static, RF currents, or lightning events

- Provides a current path for radio frequencies for proper operation of filters and shields - Provides protection against the effects of lightning - A means to prevent or safely discharge static charges. - Electrical bonds are classified according to the purpose for the bond. There may be more

than one purpose for bonding a specific interface, and the bond shall meet the requirements




of each applicable class. Notes shall be provided on assembly drawings indicating the applicable class or classes.

[EXS.0200] UMB.361 EEE Parts Plan Compliance The selection of Umbilical electrical, electronic, and electromechanical (EEE) parts shall be performed on conformance with the CSSS-S-011 Electrical, Electronic, and Electromechanical (EEE) Parts Control Plan.

[EXS.0368] UMB.082 Moisture Protection for Electrical Components Umbilical electrical components, including connectors and wiring junctions to connectors, shall be protected from moisture encountered in their intended environment. Rationale: The required composition and quality of the seal are dependent upon the environments to which the seal will be subjected. Examples include but are not limited to: 1. Rain, condensation, and other fluid environments on the launch pad 2. Condensation of cabin moisture during flight 3. Electrolytic corrosion 4. Manufacturing and storage environment

[EXS.0082] UMB.084 Mating and Demating of Powered Connectors Umbilical electrical systems shall be designed so that mating and demating of on-orbit connectors can be accomplished without producing electrical arcs. Rationale: Consideration in the design must be given to address the proper controls/inhibits in design features to avoid critical (two inhibits) and catastrophic (three inhibits) hazards (i.e., crew mate/demate of connectors for shock, molten metal & explosive environment hazards). Reference: Space Shuttle Program Memorandum, MA2-99-170 - Crew mating/demating of powered connectors.

[EXS.0084] UMB.085 Protection for Exposed Connectors Exposed Umbilical electrical plugs and receptacles shall be protected at all times except during mating and demating operations by protective covers or caps with the following characteristics: 1. Provide protection from moisture for the plugs and receptacles 2. Provide protection against damage to sealing surfaces, threads, and pins 3. Be made of conductive or dissipative materials that provide electrostatic discharge protection

of components 4. Be resistant to abrasion, chipping, or flaking 5. Be positively marked by bright colors or streamers if they are to be removed prior to launch 6. Be maintained at a level of cleanliness equivalent to the plugs or receptacles on which they

are used 7. Be made of material that is compatible with the connector material




8. Be provided with restraining devices or suitable storage areas if required for on-orbit activities. Pressure-sensitive tape shall not be used to satisfy this requirement.

Rationale: Receptacles and plugs require restraining protection from mechanical damage, dust, dirt, and foreign objects. Incorrect practice has been to allow the disconnected parts to go unprotected.

[EXS.0085] UMB.086 Wiring Harness Stress Relief Umbilical electrical wire(s), cables, bundles, and wire harnesses shall be designed and installed to withstand anticipated stresses experienced during ground handling and flight operations. Rationale: This specification ensures that wire(s), cables, bundles, and wire harnesses are verified during qualification to withstand the anticipated environments.

[EXS.0086] UMB.087 Wiring Harness Protection Umbilical electrical wire(s), cables, bundles, and wire harnesses shall be adequately protected to prevent insulation damage from chafing, abrasion and cold flow when passing through or touching any structure or panel. Rationale: This specification ensures that wire(s), cables, bundles, and wire harnesses are verified during qualification to withstand the anticipated environments. Cold flow of Teflon, and other "soft" polymer wire insulation materials, is the physical movement of the insulator under a compressive/directional load, and is often considered a latent reliability concern for electronic assemblies using wiring harnesses and cables. Cold flow only becomes a reliability issue affecting performance, if the insulation displacement becomes significant enough to thin the insulation jacket below the minimum isolation/electrical separation limit.

[EXS.0087]

UMB.091 Critical Pin Assignments Umbilical electrical circuits shall not be routed through adjacent pins of an on-orbit mated electrical connector if a short circuit between them would constitute a single failure that would cause injury to the crew, or loss of a mission critical function. Rationale: In this standard, "adjacent" includes pins within reach of a bent pin.

[EXS.0091]

UMB.092 Corona Suppression Umbilical electrical and electronic equipment shall preclude damaging or destructive corona in all applicable operating environments.




Rationale: The suit will be subject to pressurization and depressurization while in an energized state. Coronal effects must be controlled to prevent undesired arcing and potential consequences.

[EXS.0092]

UMB.096 Power Transients Umbilical electrical equipment (TBD) shall be compatible with the power bus transient environments defined in Figure TBD. Rationale: A bus environment is the baseline voltage and frequency of the bus plus the aggregate electrical feedback of equipment powered from the bus or coupled with it electrically.

[EXS.0096] {TBX.0117}

3.5.3 Fluid Design UMB.088 Fluid Connector Connections The umbilical fluid connectors shall be designed to: - preclude incorrect installation - indicate the direction of fluid flow with permanent markings on the exterior of the

component and on the parts and lines to be mated with the component. Rationale: In a complex plumbing installation, it is difficult for fabrication or assembly personnel to know the direction of flow.

[EXS.0088] UMB.090 Fluid Particulate Contamination Control The Umbilical fluid system components, subject to malfunction from particulate contamination of TBD characteristics during EVA or reverse flow situations, shall be protected from particulates which might enter from either flow direction. Rationale: Components subject to malfunction from particulate contamination should be protected on their inlet and outlet by filters to ensure that contaminants do not enter or flow backwards into the rest of the system in the event of a part malfunction.

[EXS.0090] {TBX.0113} {TBX.0115}

UMB.136 Use of Toxic Materials The Umbilical shall only use materials and chemicals that are classified as Toxic Hazard Level (THL) 0 as defined by the Toxic Hazard Level Table.




Table 3.5-1: Toxic Hazards Levels Hazard Level

Irritancy Systemic Effects Contain ability and Decontamination

0 (Non hazard)

(green)

Slight irritation that lasts <30 minutes and will not require therapy.

None Gas, solid, or liquid may or may not be containable.

1 (Critical)

(blue)

Slight to moderate irritation that lasts >30 min and will require therapy

Minimal effects, no potential for lasting internal tissue damage.

Gas, solid, or liquid may or may not be containable. However, the crew will be protected from liquids and solids by surgical masks, gloves, and goggles.

2

(Catastrophic) (yellow)

Moderate to severe irritation that has the potential for long-term performance decrement and will require therapy. Eye Hazards: May cause permanent damage.

None Either a solid or nonvolatile liquid. Can be contained by a cleanup procedure and disposed of. The crew will be protected by 5-micron surgical masks, gloves, and goggles.

3 (Catastrophic)

(orange)

Irritancy alone does not constitute a level 3 hazard.

Appreciable effects on coordination, perception, memory, etc., or has the potential for long-term (delayed) serious injury (e.g. cancer), or may result in internal tissue damage.

Either a solid or nonvolatile liquid that can be contained by a cleanup crew and disposed of. Surgical masks and gloves will not protect the crew. Either quick-don masks or SEBS and gloves are required.

4 (Catastrophic)

(red)

Moderate to severe irritancy that has the potential for long-term crew performance decrement (for eye-only hazards, there may be a risk of permanent eye damage). Note: Will require therapy if crew is exposed.

Appreciable effects on coordination, perception, memory, etc., or the potential for long-term (delayed) serious injury (e.g. cancer) or may result in internal tissue damage.

Gas, volatile liquid, or fumes that are not containable. The ARS will be used to decontaminate. Either the quick-don masks or the SEBs are required or the contaminated module will be evacuated.

[EXS.0136]

UMB.194 Pressurized EVA fluid Connections Pressurized glove activated fluid connectors on the Umbilical shall have mating/demating forces less than or equal to 12 pounds.




Rationale: Applies to connectors mated or demated during EVA or by pressurized gloves during IVA. Unless connectors designed for mating under pressure are used, fluid in pressurized systems must be reduced to permit mating. This specification applies to connecting and separation. Most problematic connection would be the HP O2 connection. Operational controls for the vehicle to perform venting on their side of the interface must be captured in an interface document or operational constraint. The value in the requirement was obtained from SP-2010-3407 Human Design Integration Handbook, Appendix B, Table 10.

[EXS.0194] UMB.256 Separation of Redundant Fluid Systems Umbilical fluid assemblies providing redundant functions shall be separated or protected to ensure that damage to one is not likely to prevent its redundant counterpart from performing the function. This specification is not applicable to components or piece parts mounted in common housings. Rationale: For purposes of this standard, "redundancy" is defined as the ability to perform a function by more than one means. This requirement ensures that redundant systems, redundant subsystems, and redundant major elements of subsystems are separated or protected to ensure that an unexpected event which damages one is not likely to prevent the other from performing the functions. This standard is not applicable to redundant components or piece parts mounted in common housings within redundant systems, subsystems, or subsystem elements.

[EXS.0256]

3.5.4 Maintainability UMB.138 Accessibility for Testing of Redundant Features The Umbilical design shall permit verification of redundant features during pre-launch testing or during on-orbit testing. Rationale: From the parent (JP8.G.0008) requirement: This standard is not to be interpreted to require verification of redundancy every time the system, subsystem, or equipment is tested but merely to require that the systems/subsystems/equipment be designed in a manner to allow redundancy verification if it is deemed necessary. Verification of redundancy may occur at any time from acceptance testing through launch processing, mission operations, and post flight.

[EXS.0138] UMB.239 In-Suit Battery Charging The Umbilical shall accommodate the charging of batteries while the batteries are installed in the PLSS.




Rationale: In order to minimize crew overhead, it is required to charge the suit batteries without removing them from the PLSS.

[EXS.0239]

3.6 Environments UMB.003 COTS ISS Internal Cargo Environment The Umbilical, in its stowed configuration, shall meet requirements after exposure to the environments defined in table COTS ISS Internal Cargo Environment. Rationale: The Umbilical needs to be capable of handling the following parameters when flown in a COTS vehicle: Temperature, Humidity, Pressure, and Cleanliness per Section 3.3.1.3 Internal Cargo and Crew Environment of SSP 50808.

Table 3.6-1: COTS ISS Internal Cargo Environment Cargo environment temperature1 50-115 °F Relative humidity range2 25 to 75 percent. Pressure environment range3 13.9 to 14.9 psia

Cleanliness4 Visibly Clean–Sensitive cleanliness requirements as specified in SN-C-0005

Depressurization/Repressurization5 Depress. rates <=7.75 psi/min Repress. rates < 6.96 psi/min

Notes: (1)This temperature range encompasses flight and ground processing internal cargo environment. (2)This range encompasses flight and ground processing relative humidity environment to the internal cargo. (3)This range encompasses flight and ground processing nominal pressure environment to the internal cargo. (4)External surfaces of flight articles integrated into habitable COTS volumes shall conform to Visibly Clean–Sensitive cleanliness requirements as specified in SN-C-0005. Exterior surfaces of COTS flight articles which are exposed to vacuum shall conform to Visibly Clean–Sensitive cleanliness requirements as specified in SN-C-0005. Exterior surface cleanliness, as specified herein, is applicable only when COTS flight articles are in the vehicle assembly building and not while at the launch pad. (5) This range encompasses flight and ground processing depressurization/pressurization rates. UMB.023 Vehicle induced condensation The Umbilical, in its stowed configuration, shall meet its performance requirements after exposure to condensation-inducing vehicle environments with 95% RH and temperatures ranging from 32 to 140 ºF.




Rationale: Temperatures and RH levels encompass pre-launch and nominal flight. [EXS.0023]

UMB.024 Salt Fog The Umbilical, in its packaged configuration, shall be compatible with sea salt particle concentrations of 200-300 particles/cm3 (3277-4916 particles/in3) affecting the launch sites, when packaged and not operating.

[EXS.0024]

UMB.025 Ozone Exposure During Transport The Umbilical, when packaged for transport, shall operate nominally after exposure to Ozone at concentrations specified by the Ozone Exposure Table.

Table 3.6-2: Ozone Exposure Environment Concentration Total Exposure Time Ozone at Sea Level 3 to 6 parts per 100 million 30 days Ozone during air transportation of 35,000ft

100 parts per 100 million 40 days

[EXS.0025] [EXS.0260]

UMB.265 Atmospheric Composition The Umbilical shall operate in an external environmental partial pressure of Oxygen (ppO2) from 3.2 psi to vacuum (TBR). Rationale: ppO2 of 3.2 psi = 15.2 psia * 21% O2, 15.2 psia = highest identified external environment pressure using air, 21 % O2 = nominal composition of air.

[EXS.0265] {TBX.0048}

3.6.1 Vibration UMB.006 Random Vibration (Launch) The Umbilical, in its stowed configuration, shall function after exposure to the launch random vibration environment defined in the Shock Equivalent Damage Potential Random Vibration Environment for Launch Excluding Dragon for Items Packed in Foam table (TBD) when packaged for launch.

[EXS.0006] {TBX.0116}




UMB.007 Pre-Launch Sinusoidal Vibration The Umbilical shall function after exposure to a sinusoidal vibration environment shown in the Sinusoidal/ Shock Environment for Pre-Launch Transportation Phase table. The Umbilical is non-operational and packaged for ground transport during exposure to this environment.

Table 3.6-3: Sinusoidal/ Shock Environment for Pre-Launch Transportation Phase Frequency Range Displacement Or Acceleration Sweep Rate 0.5 – 5 Hz 10 millimeters (mm)

1 octave / minute 5 – 300 Hz 1 g Notes: Constant sweep rate in the broadband. Criteria are the same for all directions (X, Y, Z). Test margins and durations are in SSP 41172.

[EXS.0007]

UMB.008 Acoustic Launch Environment The Umbilical shall function after exposure to the acoustic environment described in Acoustic Environment for Launch Table, while packaged for flight.

Table 3.6-4: Acoustic Environment for Launch OCTAVE BAND CENTERED FREQUENCY [Hz]

SOUND PRESSURE LEVEL Ref. 2x10-5 N/m2 (20 microPascals) [dB]

31.5 132.0 63 132.0 125 134.0 250 136.0 500 131.0 1000 129.0 2000 119.0 4000 113.0

[EXS.0014]

UMB.273 Micro-Gravity Random Vibration The Umbilical shall meet its performance requirements after exposure to the random vibration environments identified in the Random Vibration Environment table applied at the Umbilical to Suit Recharge Connector (SRC) interface and the umbilical to UIA interface. Rationale: Defines the on-orbit ISS random vibration environment as specified by the SPCE ICD.




Table 3.6-5: On-orbit Random Vibration Environment Frequency (Hz) Level 10-50 0.0005 g2/Hz 50-100 +3dB/Octave 100-1000 0.001 g2/Hz 1000-2000 -3dB/Octave 2000 0.0005 g2/Hz Composite 1.3 grms Duration 10 Hours/Year

Note: Three mutually perpendicular axis [EXS.0273]

UMB.274 Micro Gravity Sinusoidal Vibration The Umbilical shall meet its performance requirements during the peak sinusoidal vibration environment defined in the On-orbit Operational Sinusoidal Vibration Envelope table (TBR) and applied at the Umbilical to don/doff stand interface and Umbilical to UIA interface. Rationale: This requirement is obtained from the SPCE ICD. This defines the on-orbit ISS sinusoidal vibration environment experienced when suit is attached to the EDDA. Analysis must be performed to establish load path and possible amplification/attenuation of loads from the EDDA interface to the SRC/URC interface.

Table 3.6-6: On-orbit Operational Sinusoidal Vibration Envelope Frequency (Hz) (TBR) Level (TBR) 0.05 0.00055 g 0.05 – 0.45 =7.74 dB/Octave 0.45 – 15 0.05 g

[EXS.0274] {TBX.0120}

UMB.365 Sinusoidal Vibration in Flight The Umbilical shall function after exposure to a sinusoidal vibration environment shown in the Sinusoidal/ Shock Environment for All Flight Phases Table. The Umbilical is non-operational and packaged for flight during exposure to this environment. Rationale: All flight phases include launch and landing.




Table 3.6-7: Sinusoidal/ Shock Environment for All Flight Phases Frequency Range Displacement Or Acceleration Sweep Rate

0.5 – 5 Hz 2 g 1 octave / minute

5 – 300 Hz 1 g Notes: 1. Constant sweep rate in the broadband. 2. Criteria are the same for all directions (X, Y, Z). 3. Test margins and durations are in SSP 41172.

[EXS.0365]

3.6.2 Loads UMB.009 Mechanical Shock The Umbilical shall function after exposure to the launch/landing loads defined in the Shock Environments for Launch Including Dragon for Items Packed in Foam table (TBD), while packaged for flight. The shock environment is applied in each direction on each axis.

[EXS.0009] {TBX.0116}

UMB.010 Vehicle Design Load Factors The Umbilical shall function after exposure to the launch and landing load factors defined in the Launch / Landing Load Factors Envelope (Any Orientation) table. The Umbilical is non-operational and packaged appropriately for launch and landing during this exposure

Table 3.6-8: Launch / Landing Load Factors Envelope (Any Orientation) Nx(g) Ny(g) Nz(g) Rx(rad/sec2) Ry(rad/sec2) Rz(rad/sec2) Launch +/-11.6 +/-11.6 +/-11.6 +/-70.8 +/-70.8 +/-70.8 Landing +/-12.5 +/-12.5 +/-12.5 +/-37.1 +/-37.1 +/-37.1

[EXS.0010]

UMB.011 IVA Contact Loads The Umbilical shall function nominally after an impact during IVA operations as defined in the IVA Inadvertent Contact Loads table. The load can be applied anywhere on the external surface of the Umbilical.

Table 3.6-9: IVA Inadvertent Contact Loads Force (lbf) Area (in) 154 lbf 4” x 4”

[EXS.0011]

3.6.3 Thermal UMB.013 Temperature Extremes for IVA / Ground Processing (Dry) The Umbilical shall meet all its requirements after exposure to temperatures ranging from 32 - 104 degrees F for indefinite durations during ground processing.




Rationale: The term "dry" refers to IVA/ ground transported articles that have been drained of fluid.

[EXS.0013]

UMB.014 Vehicle Induced Thermal Temperatures (Launch) The Umbilical, in its stowed configuration, shall function after exposure to the wet and dry temperatures described in the Temperature Extremes for Non-Operational / Stowage table. Rationale: If EXS components are launched in transport vehicles where the lower extreme is 32 °F or below they must be launched dry. Transport vehicles with 32 °F as a lower temperature environment are Progress and HTV.

Table 3.6-10: Temperature Extremes for Non-Operational / STOWAGE Temperature °F Minimum Launched Dry 32 °F Minimum Launched Wet 35 °F Maximum 122 °F

[EXS.0014]

UMB.015 On-orbit Operations Temperatures The Umbilical shall meet its requirements during exposure to an on-orbit temperature range of +40 F to +109 F. Rationale: During normal EVA operations, only the Crewlock is depressurized. Servicing and Performance Checkout Equipment hardware in the Crewlock, specifically the UIA, must therefore operate in the pressure and temperature extremes imposed by this environment.

[EXS.0363]

UMB.363 Temperature Extremes for IVA / Ground Operations (Wet) The Umbilical shall function during and after exposure to the temperatures described in the "Temperature Extremes for IVA/ Ground Operations" Table during checkouts when CEIs or ORUs are wet. Rationale: The term wet refers to articles that contain fluid.

Table 3.6-11: Temperature Extremes for IVA / Ground Operations Temperature °F (Wet Articles)

Minimum 45°F Maximum 90°F

[EXS.0363]




UMB.364 Transport and Launch Location Induced Thermal Temperatures for Shipping Containers

The Umbilical shall meet performance requirements after exposure to the following temperatures and durations during transport while packaged and not operating:

Temperature soak at 65 °F then -65 °F for 2.5 hours. Temperature soak at 90 °F then 150 °F for 6 hours. Temperature soak at 90 °F then 190 °F for 1 hour. Temperature soak at 115 °F then -23 °F for 6 hour.

Rationale: Specifies container environmental performance requirements for transported items that may not meet environmental conditions without protection from the external environment. If EXS components are in transport and launch locations where the lower extreme is 32 °F or below they must be.The term "dry" refers to IVA/ ground transported articles that have been drained of fluid.

[EXS.0364]

3.6.4 Reserved 3.6.5 Reserved 3.6.6 Magnetic UMB.034 Electromagnetic Interference (EMI) /Radio Frequency (RF) The Umbilical shall operate nominally during and after exposure to the EMI / RF fields defined in the RF Exposure Limits table and RF Exposure Limits figure.

Rationale: Servicing and Performance Checkout Equipment electrical and electronic equipment shall meet the requirements as specified in SSP 30237.




Figure 3.6-1: RF Exposure Limits




Table 3.6-12: RF Exposure Limits RF Exposure Test Levels EXS Suit with SSER Type Radio Response above Threshold

Exposure Test Frequency (MHz) EXS/SSER Max. RF

Exposure V/m RMS

0.014 to 200 5 200 to 399 60 400 47 Loss of Comm 400.5 42 Loss of Comm 406 29 Loss of Comm 407 26 Loss of Comm 408 21 Loss of Comm 410 10 Loss of Comm 413 0 Loss of Comm 415 0 Loss of Comm 417.1 0 Loss of Comm 418.8 7 Loss of Comm 422.69 8 Loss of Comm 423.11 11 Loss of Comm 423.35 13 Loss of Comm 423.59 16 Loss of Comm 423.89 19 Loss of Comm 424.1 25 Loss of Comm 424.25 29 Loss of Comm 424.43 33 Loss of Comm 424.58 41 Loss of Comm 424.76 47 Loss of Comm 424.85 48 Loss of Comm 430 55 Loss of Comm 435 to 2000 60 2000 to 2200 89 2200 to 2400 161 2400 to 4000 89 4000 to 6000 78 6000 to 8000 60 8000 to 12000 78 12000 to 13700 47 13700 to 15200 250 15200 to 18000 47 18000 to 40000 43

[EXS.0034]




3.6.7 Pressure UMB.020 Vehicle Induced Pressure (Launch/Return) The Umbilical, shall function after exposure, uncharged and non operational, to an absolute external pressure range from 1.9 x 10^-13 psia to 18.8 psia. Rationale: The 18.8 psia pressure is the upper limit of the pressure in the Soyuz and Progress during launch.

[EXS.0020]

UMB.079 Stowed Item Pressurization The Umbilical stowage containers and packaging hardware, when stowed within pressurized compartments, shall withstand exposure to maximum external pressure rate changes of +/- 1.0 psi/sec. Rationale: Ensures that equipment containers or enclosures for use within pressurized compartments of spacecraft are designed to withstand rapid compression and decompression of the spacecraft without yielding, fracturing, or sustaining damage.

[EXS.0079]

UMB.225 Umbilical Maximum Pressurization Rate The Umbilical shall remain fully functional during and after exposure to vehicle repressurization rates of up to 1.0 psi/sec maximum. Rationale: Identifies the maximum vehicle repressurization rate at which the EXS umbilical must operate in.

[EXS.0225] 3.7 Human Interfaces UMB.076 Tool Free Umbilical Device Actuation Umbilical controls that can be actuated during an EVA shall be actuated without the use of a detached tool. Rationale: Ensures that actuating mechanisms do not require a tool that can be detached and lost at a crucial moment. Not intended to apply to non-EVA operated devices accessed during maintenance.

[EXS.0076]

UMB.077 Positive Indication of Manual Control Position Umbilical controls that are manually operated shall provide a positive indication that they are in the desired position. Rationale: Examples of desired position include ready-to-latch, latched, locked, stowed, deployed, etc.--any state in which a failure to achieve this state results in a failure of the mechanism to perform its function.

[EXS.0077]




UMB.185 Hand Controlled EVA Actuator Torque

Umbilical controls operated during EVA and requiring a gloved hand twisting/turning hand/wrist motion to actuate shall have a maximum actuation torque of 30 in-lb (3.4 Nm). Rationale: Establishes maximum amount of torque that large knobs or actuators require.

[EXS.0185]

UMB.186 Finger Controlled EVA Actuator Torque Umbilical controls operated during EVA and requiring finger control to actuate shall have a maximum actuation torque of 30 in-oz. (21.25 Ncm). Rationale: Establishes maximum amount of torque that small knobs or actuators require to operate.

[EXS.0186]

UMB.244 Mirror Free Control Actuation The Umbilical shall have controls accessible and operable by the crewmembers without requiring the use of a mirror for viewing. Rationale: For the purposes of this requirement, "controls" refer to the controls that the crewmember must utilize to control the umbilical while inside the suit. Some controls may not require direct visibility of the switch/knob to ensure they are properly actuated.

[EXS.0244]

UMB.328 Push-To-Talk Switch Accessibility The umbilical shall provide a push-to-talk control accessible to the occupant during operations with the umbilical connected to the suit. Rationale: Push to talk is an ISS feature that reconfigures the comm loop when operating on the ISS umbilical. It needs to be accessible by the operator when suited up and connected by the umbilical.

[EXS.0254]

3.8 Structures UMB.051 Creep Life The Umbilical creep life shall be 4.0 times the service life. Rationale: Flight hardware design should preclude accumulated damage from creep in the service life environment. Creep is cumulative strain as a function of time (i.e., creep), which could result in rupture, detrimental deformation, or collapse (e.g., buckling) of compression members during the service life. Details of the material selection and method of creep assessment should be included in the SVP. Creep life may be evaluated using a suitable method such as Time –Fraction Rule to determine total damage.




Table 3.8-1: Hardline Audio Out Parameter Value Notes

Frequency 300- 5000 Hz

Level -2 ± 3 dBm 1.2 to 2.5 Vp-p across 600 ohms

Impedance 600 Ohms ±10% Balanced and DC Isolated [EXS.0361]

UMB.288 Pressurized Hardware Dimensional Stability The Umbilical pressurized hardware shall maintain dimensional stability required for functionality of structural and mechanical attachments and pressure connections throughout their service life in the applicable environments.

[EXS.0288]

UMB.290 Pressure Relief Devices All Umbilical pressure relief devices shall provide full-flow relief at a pressure of 110% MDP or lower. Rationale: Requirement obtained from JSC 65828 3.2.8.3 [STR0021] Flow rate capability of the individual pressure relief devices in the redundant system should be sufficient to prevent over-pressure or rupture. There may not be pressure relief devices on the Umbilical.

[EXS.0290]

UMB.291 Flow-Induced Vibrations All Umbilical flexible hoses and bellows shall be designed to exclude or control flow-induced vibrations. Rationale: JSC 65828 3.2.8.8 [STR0026] The configuration of flexible hose and bellow designs should mitigate any detrimental effects on structural integrity or life caused by flow induced vibration.

[EXS.0291]

UMB.302 Simultaneous Application of Loads The Umbilical structural components shall meet or exceed structural factors of safety specified by the Factors of Safety Table when exposed to the highest combination of mechanical, pressure, and thermal loads that may occur simultaneously. Rationale: The most severe combination of thermal, mechanical, and pressure loads occurring at the same time or during the same mission event should be combined in a rational manner. For purposes of this requirement, the mission covers the time period from when it leaves the processing facility to when it returns to the processing facility.




Mechanical loads include loads applied by the user as well as externally applied loads such as from the vehicle.

[EXS.0302]

UMB.303 Combining with Mechanical Stress/Load The Umbilical mechanical stresses/loads shall not be multiplied by the factor of safety in calculating the design yield or ultimate stress/load if they are relieving or stabilizing to the structure.

[EXS.0303]

UMB.304 Combining with Thermal Stress/Load The Umbilical thermal stresses/loads shall be combined with mechanical and pressure stresses/loads when they are additive but not when they are relieving.

[EXS.0304]

UMB.305 Combining with Pressure Stress/Load The Umbilical pressure stresses/loads shall not be multiplied by the factor of safety in calculating the design yield or ultimate stress/load if they are relieving or stabilizing to the structure.

[EXS.0305]

UMB.306 Relieving Pressure Loads In circumstances where Umbilical pressure loads have a relieving or stabilizing effect on structural load capability, the minimum value of such relieving loads shall be used. Rationale: No change from JSC 65828 3.3.2.4 [STR0055]

[EXS.0306]

UMB.307 Fatigue Analysis Factor The Umbilical design analysis used to assess the fatigue life of the Umbilical structure shall multiply limit stress/strain by a Fatigue Analysis Factor (FAF), 1.15 on typical fatigue properties or 1.0 on lower bound fatigue properties, prior to entering the Stress versus Cycle Life (S/N) design curve to determine the low-cycle and high-cycle fatigue life as directed by the CSSS Structural Verification Plan (SVP).

[EXS.0307]

UMB.309 Creep Life Factor The Umbilical structure shall have adequate structural life with a creep life of 4.0 times the service life. Rationale: Flight hardware design should preclude accumulated damage from creep in the service life environment. Details of the material selection and method of creep assessment should be included in the SVP. Creep life may be evaluated using a suitable method such as Time-Fraction Rule to determine total damage.

[EXS.0309]




UMB.201 Umbilical Minimum Factors of Safety (FOS) The Umbilical structural hardware shall be designed and tested to the Factors of Safety (FOS) specified in the Umbilical Minimum Factors of Safety and Test Factors Table.

Table 3.8-2: Umbilical Assembly Minimum Factors of Safety and Test Factors

Notes: (1) Yield and ultimate factors of safety for pressurized hardware are used in the combined loading equation for mechanical (K1), thermal (K2) and pressure (K3) factors. The ultimate factors of safety should be used for the pressure only load case when a burst pressure is not defined. The yield factors of safety or the proof pressure may be used for the pressure only load case to prevent yielding depending on the specific application. (2) Maximum External Pressure (MEP) is the largest pressure differential as measured from outside the pressurized hardware to the inside. Pressure vessels and pressurized structures should be capable of withstanding ultimate external loads and ultimate external pressure (destabilizing) without collapse or rupture when internally pressurized to the minimum anticipated operating pressure. (3) Must be capable of withstanding the Maximum External Pressure (MEP) multiplied by ultimate factor of safety (Negative Pressure Differential) without collapse or rupture when internally pressurized to the minimum anticipated operating pressure. (4)The yield factor of safety is only applicable to metallic portion of the COPV

Component Category Structural Loads

Yield(1) Ult.(1) Qual. Acc/ Proof DBP NPD

Hoses Pressurized flex hoses (Low pressure, water)

Low and high pressure

1.0

1.4

N/A

2.0XMEOP(5) = 30 psi

4.0XMEOP = 60 psi

2.5XMEP(2) = 47 psi

Pressurized flex hoses (High pressure, O2)

2.0XMEOP(5) = 6000 psi

4.0XMEOP = 12000 psi

2.5XMEP(2) = 47 psi

Wire Ropes & Cables

tether load 4.0 2.0

Lines & fittings < 1.5OD

Pressure 1.0 1.4 1.5XMEOP

4.0XMEOP

2.5XMEP(2)

Connectors, handle

Metallic Contact, IF loads

1.0 1.4 1.4

Non-Metallic

1.4(7) 2.0(8)

1.4 1.05

Hoses Wire ropes and cables

Tether load, Interface loads

4.0 2.0

Tether rope Tether load 2.0 2.0 1.2 Assumptions: MEOP = 39(TBR) psi and 3000 psi, MEP = 18.8 psia




(5)In a system with fluid lines and flex hoses, the individual flex hoses should be proof tested to 2.00X MEOP. This factor does not apply at the assembly level. (6)The minimum proof facto for COPVs is 1.25. AIAA S-081A requires a proof factor of 1.5 for COPVs designed to a burst factor of 2.0. Use of a proof factor of 1.25 should be coordinated with applicable ground and range safety organizations to meet the intent of those requirements (e.g. auto frottage pressure cycle during tank fabrication at factors of 1.5 or above). Ground or range safety proof test factors may exceed the proof factor defined in this table. (7)Uniform areas (8)Discontinuity areas. Applies to concentrated stresses in structures where failure could result in a critical or catastrophic hazard. Discontinuities in composite structures that are development tested (e.g. for ramp downs and tapers) can be counted as tested structures. Discontinuities are an interruption in the physical structure or configuration of the part such as: reinforced holes or cut-outs; bolted, pinned, mechanically fastened or other junctions with fittings; rapid ply drops or pad-ups; core ramps for sandwich structures; pre-form junctions; adhesive joints; or discrete areas with load introduction or boundary conditions. The table above consolidates the following Umbilical requirements:

UMB.202 Metallic FOS (EXS.0202, STR.0039, SDVR.0035) UMB.204 Non-metallic FOS (EXS.0204, STR.0041, SDVR.0037) UMB.206 Pressurized Hardware FOS (EXS.0206, STR.0044, SDVR.0041) UMB.211 Wire Ropes and Cables FOS (EXS.0211, STR.0049, SDVR.0046) UMB.212 Pressure Garment Softgoods FOS (EXS.0213, STR.0042, SDVR.0040)

Definitions: Design Burst Pressure (DBP) - A pressure level that pressurized hardware must withstand without rupture in the applicable operating environment. Factor of Safety (FOS) - Multiplying factors to be applied to limit loads or stresses for purposes of analytical assessment (design factors) or test verification (test factors) of design adequacy in strength or stability. Factors of safety are deterministically-based and are necessary to assure no failures due to uncertainties that result from the design process, manufacturing process, and the loading environment. Maximum Design Pressure (MDP) – The highest pressure defined by the maximum relief pressure, maximum regulator pressure, maximum temperature and transient pressure excursions based on two credible system failures. Maximum Expected Operating Pressure (MEOP) – The maximum pressure which the pressurized hardware is expected to experience during its service life, in association with its applicable operating environments.




Maximum External Pressure (MEP) - The maximum pressure environment which the pressurized hardware is expected to experience during its service life. Negative Pressure Differential (NDP) – The Maximum External Pressure (MEP) multiplied by the ultimate factor of safety.

[EXS.0201] UMB.310 Loads Due to Friction (Relieving) Umbilical structural components shall be designed and analyzed such that friction is not considered when it is relieving.

[EXS.0310] UMB.311 Loads Due to Friction (Additive) Umbilical structural components shall be designed and analyzed such that friction forces are included when they increase the magnitude of the applied load or stress or when they are detrimental to the function of the part.

[EXS.0311] UMB.312 Design Loads for Collapse Umbilical design loads for collapse shall be ultimate loads, unless a load component alleviates buckling in which case the ultimate factor of safety is not applied to that component.

[EXS.0312]

UMB.313 Destabilizing External Pressure or Torsional Loads Umbilical destabilizing external pressure or torsional limit loads shall be increased by the ultimate factor of safety.

[EXS.0313]

UMB.314 Stabilizing Internal Pressure Loads Umbilical internal-pressure loads that stabilize the structure shall not be increased by the ultimate factor of safety unless they reduce structural capability. Rationale: No change from JSC 65828 3.4.4.2 [STR0065]

[EXS.0314]

UMB.315 Consideration of Gapping at Interfaces For Umbilical interfaces which exhibit gapping at less than limit load, loads analyses shall be supported by non-linear analysis.

[EXS.0315]

UMB.358 Metallic Pressurized Hardware Metallic pressure vessels, pressurized structures, special pressurized equipment and pressure components shall comply with ANSI/AIAA-S-080, Standard for Space Systems – Metallic Pressure Vessels, Pressurized Structures, and Pressure Components, with the following exceptions:




a. Applicable loads and environments to be used in place of those defined in the AIAA standard are documented in the Structural Verification Plan.

b. Applicable minimum factors of safety to be used in place of those defined in the AIAA standard are defined in UMB.201.

c. Applicable design pressures to be used in place of those defined in the AIAA standard are defined in UMB.201.

d. Applicable design pressures to be used in place of those defined in the AIAA standard for cryostats (dewars) are the higher of MDP or the pressure achieved under maximum venting conditions.

Rationale: The AIAA standard for metallic pressurized hardware is tailored to account for human spaceflight safety factor requirements and design loads. UMB.203 Beryllium Structures FOS The Umbilical structural hardware constructed of beryllium shall be designed and tested to the minimum factors of safety specified in the Minimum Factors of Safety for Beryllium table. Rationale: JSC 65828 3.3.1.2.1 It is not anticipated that there will be beryllium structures in the EXS suit. However there may be Beryllium alloy motor and fan bushings that this requirement will apply to. Special consideration must be given to beryllium structures due to the brittle nature of the material and sensitivity to flaws that can be induced during the fabrication process.

Table 3.8-3: Minimum Factors of Safety for Beryllium Structures Minimum Factors of Safety for Beryllium Structures Yield Ultimate Prototype 1.00 1.40 Qual Acceptan Minimum buckl

[EXS.0203]

UMB.279 Ultimate Margin of Safety The Umbilical structural components shall maintain structural integrity with +0.00 or positive Margin(s) of Safety (MS) when exposed to limit loads multiplied by ultimate factors of safety during the service life, including the effect of aging on the hardware.




The basic equation for calculating a margin of safety is: MSult = [Hardware Ultimate Capability / (Ultimate Factor of Safety x Applied Limit Load)] – 1 Rationale: Requirement obtained from JSC 65828 3.2.1.1 [STR0005]. The Suit must be capable of sustaining ultimate load without rupture. Structural integrity is lost when the structure can no longer maintain its load-carrying capacity. Ultimate load is defined as limit load multiplied by the required Factor(s) of Safety for ultimate. The basic equation for calculating a margin of safety is: MSult = [Hardware Ultimate Capability / (Ultimate Factor of Safety x Applied Limit Load)] – 1

[EXS.0279]

UMB.280 Detrimental Deformation The Umbilical structural components shall have no detrimental deformation when exposed to limit loads multiplied by yield factors of safety during their service life. Rationale: Requirement obtained from Requirement obtained from JSC 65828 3.2.1.2 [STR0006] Detrimental deformation is structural deformation, deflection, or displacement that adversely affects the form, fit, function, or load carrying capability of flight hardware structure.

[EXS.0280]

UMB.281 Yielding during Ground Transportation The Umbilical structural components shall not yield when exposed to ground limit loads multiplied by yield factors of safety, specified in the Factors of Safety (FOS) Table, during ground transportation, rollout or handling operations. Rationale: Requirement obtained from JSC 65828 3.2.1.3 [STR0007] Yielding of flight hardware during transportation could damage the structure, rendering it incapable of meeting its design service life. Loads during ground transportation should be limited to avoid any damage, including non-detrimental yielding.

[EXS.0281]

UMB.282 Yield Margins of Safety The Umbilical structural components shall have +0.00 or positive MS for all yield design load conditions, including the effect of aging on the hardware, except for cases of non-detrimental deformation. The basic equation for calculating a yielding margin of safety is: MSyld = [Hardware Yield Capability / (Yield Factor of Safety x Applied Limit Load)] – 1 Rationale: Requirement obtained from JSC 65828 3.2.1.4 [STR0008] Structural yield margins of safety need to be assessed for all cases where material yield is detrimental. The basic equation for calculating a margin of safety is:




MSyld = [Hardware Yield Capability / (Yield Factor of Safety x Applied Limit Load)] – 1 [EXS.0282]

UMB.286 Fatigue Life Umbilical structural components (excluding soft goods) shall have a minimum fatigue life of 4.0 times the service life. Rationale: Requirement obtained from JSC 65828 3.2.3.1 [STR0012] Flight hardware structure design should preclude failure resulting from cumulative damage due to cyclic or repeated loading and sustained stress. The design assessment should consider all relevant load cycles over the service life as well as self-induced conditions due to operation.

[EXS.0286]

UMB.287 High-Cycle Fatigue Life The Umbilical structure subjected to high-cycle fatigue shall have a minimum fatigue life of 10.0 times the service life.

[EXS.0287]

4.0 Verification The verification requirements defined in Section 4 describe how the respective requirements in Sections 3.2 through 3.6 are to be verified. Each verification requirement is tagged with the corresponding requirement identifier appended with a V (i.e.,UMB.nnn.V). CSSS-T-006, Contractor Master Verification Plan identifies the roles and responsibilities of OII. A Verification Cross Reference Matrix (VCRM) is provided as part of this document.

4.1 Verification Methods Verification may be accomplished by analysis, demonstration, test, inspection, or any combination thereof. The methods used to accomplish verification are defined below.

A. Analysis - a method of verification using techniques and tools such as computer and hardware simulations, analog modeling, and similarity assessments. Analysis is the evaluation of the results of multiple tests and analyses at a lower level as they would apply to a higher level of assembly. Analytical methods selected for verification will be supported by appropriate rationale and will be detailed in the applicable documents.

D. Demonstration - a qualitative exhibition of functional performance (i.e., serviceability, accessibility, transportability, and human engineering features) usually accomplished with no or minimal instrumentation.

T. Test - a method of verification wherein requirements are verified by measurement during or after the controlled application of functional and environmental stimuli. These measurements may require the use of laboratory equipment, recorded data, procedures, test support items, or services. For all verification, qualification, and acceptance test activities, pass or fail test criteria or acceptance tolerance bands (based upon design and performance requirements) shall be specified prior to conducting the test. This will ensure that the actual performance of tested equipment or systems meets or exceeds specifications.




I. Inspection - a method of verification of physical characteristics that determines compliance of the item with requirements without the use of special laboratory equipment, procedures, test support items, or services. Inspection uses standard methods such as visuals, gauges, etc., to verify compliance with requirements.

Hardware may be inspected for the following: a. Construction b. Workmanship c. Physical condition d. Specification and/or drawing compliance inspection may be used to confirm that engineering

drawings call out proper design and construction features (i.e., materials and processes). Inspection includes Review of Design (ROD). This is typically a review of the as-built drawings to confirm that a design feature has been incorporated into the design.

e. Review of lower-level requirements' verification closure documentation.

4.2 Performance UMB.046.V Unassisted Operations The Umbilical Assembly's ability to meet this requirement shall be verified by demonstration at the integrated suit level. The Demonstration shall show that a suited test subject can perform unassisted operation of all the Umbilical's on-orbit EVA functions as part of the Integrated Suit Assembly in a 1G environment. The Demonstration will include multiple test subjects at various pressures and be supplemented by analysis to extend the results to the full crew size range and the EVA environment. This demonstration will be conducted as part of the suit level demonstration to verify requirement EXS.0046. Success Criteria: The verification shall be considered successful when the suit level demonstration shows, as documented in a Crew Consensus Report, that suited test subjects can perform unassisted operation of all on-orbit EVA Umbilical functions. UMB.078.V On-Orbit Alignment Features The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall be by inspection of the drawings, hardware and documentation. Success Criteria: The verification shall be considered successful when Inspection of the drawings, hardware and documentation shows that alignment features are provided where on-orbit alignment is required for operations, maintenance, assembly or sizing. UMB.137.V Allowable Pressure Drop The Umbilical ability to meet this requirement shall be verified by test.




The verification shall consist of a test pressurizing the Umbilical to 3000 psi and verifying that the Umbilical has a pressure drop through the water loop of less than TBD psi. Success Criteria: The verification shall be considered successful when the test shows that the Umbilical pressure drop through the water loop is less than TBD psi.

4.2.1 Reserved 4.2.2 Maintenance UMB.108.V In-flight Maintenance and Replacement The Umbilical ability to meet this requirement shall be verified by inspection and demonstration. The verification shall consist of an inspection of the assembly and review of its accommodations for maintenance and repair. The demonstration shall consist of removing and installing the Umbilical assembly in a 1G environment, and any other nominal replacement tasks with the standard ISS tools complement. Success Criteria: The verification shall be considered successful when the inspection and demonstration show that the umbilical can be replaced without the use of special tools and the inspection of maintenance manuals and procedures shows no requirement for special tools other than the tools already present on board the ISS. UMB.149.V Installation Design The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the drawings, installation and maintenance procedures to verify the presence of design features precluding the installation of assemblies in a non-operational orientation. Success Criteria: The verification shall be considered successful when the inspection shows that the assemblies and maintenance items are designed such that they cannot be installed in a non-operational orientation. UMB.234.V ORU Captive Fasteners The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the Umbilical assembly drawings and documentation to verify that any fasteners used for On-Orbit Replaceable Units (ORU) are captive. Success Criteria: The verification shall be considered successful when the inspection shows that any On-Orbit Replaceable Units (ORU) fasteners are captive.




4.2.3 Reserved 4.2.4 Reliability UMB.047.V Umbilical/PLSS Interface Mechanical Components Mate/Demate Cycles The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test to evaluate condition and performance of the assembly at 4 x the identified maintenance interval as part of the life cycle testing. Functional checkout will include actuation of mechanical components. Success Criteria: The test shall be considered successful when it shows that the Umbilical mechanical components meet structural and functional requirements at 4 x the identified maintenance interval as part of the life cycle testing. Functional checkout will include actuation of mechanical components. UMB.048.V Umbilical/Vehicle Interface Mechanical Components Mate/Demate Cycles The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test to evaluate condition and performance of the assembly at 4 x the identified maintenance interval as part of the life cycle testing. Functional checkout will include actuation of mechanical components. Success Criteria: The test shall be considered successful when it shows that the Umbilical mechanical components meet structural and functional requirements at 4 x the identified maintenance interval as part of the life cycle testing. UMB.049.V Umbilical/Vehicle Interface Electrical Connectors Mate/Demate Cycles The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test to evaluate condition and performance of the assembly at 2 x the identified maintenance interval as part of the life cycle testing. Functional checkout will include mate-demate of electrical connectors followed by performing preventative maintenance and continuation of life cycle testing. Success Criteria: The test shall be considered successful when it shows that the Umbilical electric connectors meet their structural and functional requirements at 2 x the identified maintenance interval as part of the life cycle testing. UMB.050.V Umbilical/PLSS Interface Electrical Connectors Mate/Demate Cycles The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test to evaluate condition and performance of the assembly at 2 x the identified maintenance interval as part of the life cycle testing. Functional checkout will




include mate-demate of electrical connectors followed by performing preventative maintenance and continuation of life cycle testing. Success Criteria: The test shall be considered successful when it shows that the Umbilical electric connectors meet their structural and functional requirements at 2 x the identified maintenance interval as part of the life cycle testing. UMB.171.V Continuous On-Orbit Service Life The Umbilical ability to meet this requirement shall be verified by analysis and test. The analysis shall assess the Umbilical materials for their suitability for a 6 year design life. The test shall include life cycle testing of the pressurized Umbilical hoses for 2 x 936 hours in an ambient environment. The test shall include 20% (TBR) of the cycles and pressurized operations time at vacuum. The hose dimensions (diameter and length) will be measured pre- and post- testing. Success Criteria: The verification shall be considered successful when the analysis shows that the Umbilical materials can meet or exceed a 6 year design life and the test results show that the Umbilical hoses do not dimensionally change more than TBD % after extended pressurized time. UMB.173.V Preventive Maintenance Constraints The Umbilical ability to meet this requirement shall be verified by test. The test shall evaluate condition and performance of the Umbilical assembly at the identified maintenance interval of 300 (TBR) hours as part of the life cycle testing. Functional checkout will include actuation of mechanisms along with proof and leak testing. Analysis may be used to supplement testing by extrapolating data over the specified timeframe. Success Criteria: The verification shall be considered successful when the test shows that the assembly meets structural and functional requirements after a minimum of 300 hours (TBR) of life cycle testing without preventive or limited life maintenance. The 300 hours (TBR) include 2 hours of pre- and post- EVA checkout and maintenance activities and 10 hours of suit recharge activities after each EVA for the specified 25 EVAs.

4.2.5 Reserved 4.2.6 Reserved 4.3 Physical Characteristics UMB.327.V Umbilical transfer through hatch The Umbilical's ability to meet this requirement shall be verified by inspection. The verification shall consist of inspection of the Umbilical Assembly drawings to verify the Umbilical components will pass through a 31.5 inch diameter hatch.




Success Criteria: The verification shall be considered successful when an inspection of the Umbilical Assembly drawings shows that the Umbilical Assembly will pass through a 31.5 inch diameter hatch.

4.3.1 Mass UMB.062.V Umbilical Dry Mass The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of weighing the Umbilical Assembly components that are part of the Integrated Umbilical Assembly and recording their dry mass. Success Criteria: The verification shall be considered successful when weighing the Umbilical components that are part of the Umbilical Assembly shows that their total dry mass is less than or equal to 35 lbm (TBR).

4.3.2 Product Marking UMB.183.V Part Identification Marking The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall be an inspection of the Umbilical assembly for nomenclature, part number (P/N) and serial number (S/N) when applicable. Success Criteria: The verification shall be considered successful when the inspection shows that the assembly parts shall be visibly marked showing nomenclature, part number (P/N) and serial number (S/N) when applicable. UMB.184.V Part Marking on Drawings The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the drawings for identification of the location for assembly part markings and method of application. Success Criteria: The verification shall be considered successful when the inspection shows that the location of assembly part markings and method of application are identified on engineering drawings.

4.3.3 Cleanliness UMB.115.V Elevated Pressure Oxygen Loop Cleanliness The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the Umbilical design documentation to ensure that there are notes specifying that the oxygen wetted components must be cleaned to a minimum cleanliness level of 100A per the EXS Contamination Control Plan (CSSS-T-014).




Success Criteria: The verification shall be considered successful when the inspection of the Umbilical's design documentation shows that Umbilical components are required to be cleaned to a minimum level of 100A per CSSS-T-014 UMB.116.V Cooling Water Loop Cleanliness The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the Umbilical's design documentation to ensure that there are notes specifying that the umbilical components of the cooling water loop meet a minimum cleanliness level of 150A per the EXS Contamination Control Plan (CSSS-T-014). Success Criteria: The verification shall be considered successful when the inspection of the Umbilical design documentation shows that Umbilical components are required to be cleaned to a minimum level of 150A per CSSS-T-014 UMB.237.V Low Pressure Oxygen Loop Cleanliness The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the Inspection of the Umbilical design documentation to ensure that there are notes specifying that the low pressure oxygen wetted components must be cleaned to a minimum cleanliness level of Visibly Clean (VC) Sensitive per the EXS Contamination Control Plan (CSSS-T-014). Success Criteria: The verification shall be considered successful when the inspection of the Umbilical design documentation shows that Umbilical components are required to be cleaned to a minimum level of Visibly Clean (VC) Sensitive per CSSS-T-014. UMB.354.V Preflight/Ground Fungal Limit The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of materials selected for the wetted components Umbilical Assembly ventilation loop, the cleaning procedures and Umbilical Assembly wetted components design documentation. Success Criteria: The verification shall be considered successful when the inspection shows that appropriate materials have been selected, cleaning procedures are included on the drawings and the assembly can be cleaned to a maximum fungi contamination level of 10 colony forming units (CFUs)/100 cm2. UMB.355.V Preflight/Ground Microbial Limit The Umbilical ability to meet this requirement shall be verified by inspection.




The verification shall consist of an inspection of materials selected for the wetted components of the Umbilical assembly ventilation loop, the cleaning procedures and Umbilical wetted components design documentation. Success Criteria: The verification shall be considered successful when the inspection shows that appropriate materials have been selected, cleaning procedures are included on the drawings and the assembly can be cleaned to a maximum microbial contamination level of 500 colony forming units (CFUs)/100 cm2. UMB.356.V On-orbit Fungal Limit The Umbilical ability to meet this requirement shall be verified by test and analysis. The analysis shall evaluate the Umbilical hardware assembly configuration and material compatibility with On Orbit Cleaning Procedure TBD. The test shall clean the hardware according to the approved procedure. Success Criteria: The verification shall be considered successful when the analysis and test shows that the On Orbit Cleaning Procedure (TBD) performed on the hardware results in surfaces with a fungal concentration level at or below100 CFU/100 cm2. UMB.357.V On-orbit Microbial Limit The Umbilical ability to meet this requirement shall be verified by test and analysis. The analysis shall evaluate the Umbilical hardware assembly configuration and material compatibility with On Orbit Cleaning Procedure TBD. The test shall clean the hardware according to the approved procedure. Success Criteria: The verification shall be considered successful when the analysis and test shows that the On Orbit Cleaning Procedure (TBD) performed on the Umbilical hardware results in surfaces with a microbial concentration level at or below 10,000 CFU/100 cm2.

4.4 Interfaces UMB.001.V Umbilical External Interfaces The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the Umbilical Assembly drawings and Integrated Suit Assembly drawings to determine compliance with the interfaces defined by the Umbilical External Interfaces Table. Success Criteria: The verification shall be considered successful when the inspection shows that the Umbilical Assembly possesses all the interfaces defined in the Umbilical External Interfaces Table.




UMB.002.V Mating to the ISS UIA Panel The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the Umbilical connector and UIA panel drawings to verify proper mating to the UIA. Success Criteria: The verification shall be considered successful when the inspection shows that the Umbilical connector is keyed to provide for proper alignment and polarization for mating to the UIA. UMB.326.V Umbilical Stowage During ISS EVA The Umbilical ability to meet this requirement shall be verified by Analysis. The verification shall consist of an analysis of the volumetric fit of the Umbilical assembly, in its stowed configuration, within the crew lock. Success Criteria: The verification shall be considered successful when the analysis shows that the Umbilical assembly, in its stowed configuration, fits volumetrically within the crew lock.

4.4.1 Vehicle Umbilical Fluid Interfaces UMB.061.V Umbilical Water Quality The Umbilical's ability to meet this requirement shall be verified by analysis. The verification shall consist of an analysis of the materials and components that make up the Umbilical Assembly to determine that they will not be affected by the contaminants listed in the Cooling Fluid Contaminants Table. Success Criteria: The verification shall be considered successful when the analysis shows that the materials and components that make up the Umbilical Assembly are not affected by the contaminants listed in the Cooling Fluid Contaminants Table. UMB.110.V HPO2 Maximum Expected Operating Pressure (MEOP) The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test of the HPO2 portion of the Umbilical assembly to show that it can receive high pressure oxygen in accordance with the values specified by UMB.110. Success Criteria: The verification shall be considered successful when the test of the HPO2 portion of the Umbilical assembly shows that it can receive high pressure oxygen in accordance with the values specified by UMB.110. UMB.111.V Umbilical HP O2 Leakage When Attached to Vehicle The Umbilical ability to meet this requirement shall be verified by test and analysis.




The verification shall consist of a test measuring the Umbilical’s high pressure O2 leakage rate when the vehicle end of the Umbilical is connected to a ground support Umbilical Connector Block (UCB) pressurized to 3000 psia at 70 °F. If an inert gas is used for the test, then analysis will be used to extrapolate the results for oxygen properties. Success Criteria: The verification shall be considered successful when the test shows that the Umbilical’s water leakage does not exceed 0.24 cc/hr at 28.1 psig and 70 °F. UMB.112.V Umbilical Vacuum Leakage When Attached to Vehicle The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a vacuum test of the vacuum line assembly portion of the Umbilical and measuring the leakage of the Umbilical’s connector mated to a functional mockup of the ISS-provided vacuum port. Success Criteria: The verification shall be considered successful when the test shows that the vacuum line assembly portion of the Umbilical has a leakage less than TBD SCC/M when the umbilical is attached to the ISS vacuum port and operating in a pressure range between 10^-6 Torr and 4 Torr (TBR). UMB.113.V Umbilical Cooling Water Leakage When Attached to Vehicle The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of testing the Umbilical connection to a mockup of the ISS UIA panel at 28.1 psig x FOS (TBD) and 70 °F for a TBD duration to verify that the Umbilical connector's leakage does not exceed an external cooling water leakage of 0.24 cc/hr. The Suit Recharge Connector will be demated from the suit during this test. Success Criteria: The verification shall be considered successful when the test shows that the Umbilical connector's leakage does not exceed an external cooling water leakage of 0.24 cc/hr at 28.1 psig x FOS (TBD) and 70 °F. UMB.114.V Umbilical Vacuum Leakage When Attached to Vehicle and Mated to Suit The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a vacuum test of the vacuum line assembly portion of the Umbilical mated to both a functional mockup of the ISS-provided vacuum port and the Suit Recharge Connector (SRC). Success Criteria: The verification shall be considered successful when the test shows that the vacuum line assembly portion of the Umbilical has a leakage less than TBD SCC/M when the umbilical is mated to both a functional mockup of the ISS-provided vacuum port and the Suit Recharge Connector (SRC).




UMB.117.V Feed Water Recharge MEOP The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test of the Integrated Umbilical Assembly. The test set up will include the umbilical connected to a functional simulator of the ISS SPCE. The test will show that the Umbilical Assembly can receive feed water from the ISS SPCE simulator through the recharge umbilical at a maximum pressure of 39.0 psid. The pressure and flow rate will be measured at the supply interface between the Umbilical Assembly and the SPCE. Success Criteria: The verification shall be considered successful when the test of the Umbilical Assembly shows that it can receive feed water from the ISS SPCE via the recharge umbilical at a maximum pressure of 39.0 psid when measured at the supply interface between the Umbilical Assembly and the recharge ISS SPCE. UMB.118.V Feed Water Biocide Concentration The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of the materials of the Umbilical wetted components for compatibility with the biocide concentrations identified in the Biocide Table. Success Criteria: The verification shall be considered successful when the inspection of Umbilical wetted components' materials show compatibility with the biocide concentrations identified in the Biocide Table. UMB.270.V Vehicle Supplied Oxygen Standards The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the Inspection of lower level verification documentation that shows that the Umbilical high pressure O2 components have been designed to accommodate O2 with a purity level of 99.5% as defined in MIL-PRF-27210G, Type 1, Aviator’s Breathing Oxygen. Success Criteria: The verification shall be considered successful when inspection of the lower level verification documentation shows the Umbilical will accommodate O2 with a purity level of 99.5% as defined in MIL-PRF-27210G, Type 1, Aviator’s Breathing Oxygen. UMB.324.V HP O2 Pressure Rise Rate The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test that includes recharging the high pressure O2 system and monitoring the pressure rate increase in the primary and secondary O2 bottles. Success Criteria: The verification shall be considered successful when the test data shows that the Suit limits the HP O2 pressure rise rate to less than 418 psi O2/second.




4.4.2 Vehicle Umbilical Electrical Interfaces UMB.119.V Umbilical External Power The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test of the Umbilical Assembly to ensure it can withstand the power and power transient requirements specified in the External Power Table. Success Criteria: The verification shall be considered successful when the test shows that the Umbilical Assembly can withstand the power and power transient requirements specified in the External Power Table. UMB.121.V Electrical Path Resistance The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test of the Umbilical Assembly and UIA to verify that the Umbilical electrical interface to the vehicle does not exceed 0.15 ohms for each power and return path. Success Criteria: The verification shall be considered successful when the test shows that the interface between the Umbilical Assembly and the UIA does not exceed 0.15 ohms for each power and return path. UMB.123.V Umbilical Electrical Interface Pin Assignments The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of Umbilical's vehicle side connector electrical pinout for compliance with the Umbilical to Vehicle Electrical Pinout Table. Success Criteria: The verification shall be considered successful when consist the inspection of Umbilical's vehicle side connector electrical pinout shows compliance with the Umbilical to Vehicle Electrical Pinout Table. UMB.124.V Provide Hardline Audio To Vehicle The Umbilical ability to meet this requirement shall be verified by test. The test shall consist of measuring the frequency, signal level, and impedance of the Hardline Audio Out lines at the vehicle side connector when a test signal is applied to the Hardline Audio Out lines at the suit side connector. Success Criteria: The verification shall be considered successful when the test of the Hardline Audio Out lines shows compliance with the Hardline Audio Out table. UMB.125.V Receive Hardline Audio from Vehicle The Umbilical ability to meet this requirement shall be verified by inspection.




The verification shall consist of inspection of the Umbilical's drawings to ensure the presence of a hardline audio interface from the vehicle. Success Criteria: The verification shall be considered successful when the inspection of the Umbilical's drawings shows the presence of a hardline audio interface from the vehicle. UMB.126.V Push-To-Talk Signal The Umbilical ability to meet this requirement shall be verified by inspection and test. The verification shall consist of inspection of the Umbilical drawings to verify the presence of a Push-To-Talk signal line and a test verifying the signal is properly transmitted. Success Criteria: The verification shall be considered successful when the inspection of Umbilical drawings shows the presence of a Push-To-Talk signal line and the test verifies that the signal is properly transmitted. UMB.128.V Exchange Hardline Data with Vehicle The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of inspection of the Umbilical drawings to ensure the presence of a data hardline to the vehicle for software updates. Success Criteria: The verification shall be considered successful when the inspection of the Umbilical drawings shows the presence of a data hardline for software updates.

4.4.3 Umbilical PLSS Electrical Interfaces UMB.122.V Umbilical to PLSS Electrical Pin Assignments The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of Umbilical's suit side connector electrical pinout for compliance with the Umbilical to Suit (SRC) Electrical Pinout Table. Success Criteria: The verification shall be considered successful when the inspection of Umbilical's suit side connector electrical pinout shows compliance with the Umbilical to Suit (SRC) Electrical Pinout Table.

4.4.4 Umbilical PLSS Fluid Interfaces 4.4.5 Reserved 4.4.6 Reserved 4.4.7 Reserved




4.4.8 Reserved 4.5 Design and Construction UMB.035.V Pyrotechnic Devices Prohibited The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of inspection of the assembly parts list. Success Criteria: The verification shall be considered successful when the inspection shows that the assembly does not contain pyrotechnical devices UMB.298.V Small Diameter Critical Seal Redundancy The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of the Umbilical drawings to determine if critical seals with a major outer diameter less than or equal to 0.5 inches have a minimum of one seals at the interface. Success Criteria: The verification shall be considered successful when inspection of the Umbilical drawings shows that critical Umbilical seals with a major outer diameter less than or equal to 0.5 inches have a minimum of one seal at the interface. UMB.299.V Large Diameter Critical Seal Redundancy The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of integrated Umbilical drawings. Success Criteria: The verification shall be considered successful when inspection of the Umbilical drawings shows that critical Umbilical seals with a major outer diameter greater than 0.5 inches have a minimum of two seals at the interface. UMB.074.V Use of Self Sealing Fluid Connectors The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the Umbilical drawings to confirm that fluid connectors specified to be mated and demated on-orbit are self sealing. Success Criteria: The verification shall be considered successful when the inspection of the Umbilical drawings shows that the fluid connectors that will be mated and demated on-orbit are self sealing. UMB.106.V Debris Protection - Mechanical Components The Umbilical ability to meet this requirement shall be verified by inspection and analysis.




The verification shall be by inspection of the umbilical drawings to show that critical umbilical mechanical components are protected from debris or foreign material that could cause the component to malfunction. An analysis shall be performed to identify the umbilical mechanical components that are considered critical. Success Criteria: The verification shall be considered successful when the inspection shows that the umbilical assembly contains protective measures such as proof covers, seals, shrouds, or containers and the analysis confirms the umbilical Mechanical components that are considered critical are provided with such protective measures. UMB.190.V Connector Inadvertent Demate The Umbilical ability to meet this requirement shall be verified by inspection and demonstration. The verification shall consist of the inspection of Umbilical drawings and design documentation to verify the presence of controls to prevent inadvertent demate. A demonstration shall be performed to verify that the connector has dissimilar actuation feature that prevent inadvertent demate. Success Criteria: The verification shall be considered successful when the inspection of Umbilical drawings and design documentation confirms the presence of controls to prevent inadvertent demate and the demonstration shows dissimilar actuation features that prevent UMB.191.V Connector Mating Status The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of Umbilical drawings and design documentation to verify the presence of mated status markings. Success Criteria: The verification shall be considered successful when the inspection of Umbilical drawings and design documentation confirms the presence of mated status markings. UMB.193.V Vehicle Tether Attach Limit Load The Umbilical's ability to meet this requirement shall be verified by test. The verification shall consist of the test of the Umbilical tether at an axial limit load of 200 lb (890 N) times the factor of safety specified by the Factors of Safety (FOS) table as directed by the SVP. Success Criteria: The verification shall be considered successful when the test shows that the umbilical can withstand an axial limit load of 200 lb (890 N) times the factor of safety specified by the Factors of Safety (FOS) table as directed by the SVP. UMB.236.V Comply with Component and Mechanism Design Requirements Document The Umbilical ability to meet this requirement shall be verified by analysis and inspection.




The analysis shall consist of reviewing the Umbilical Assembly design against the CSSS Component and Mechanism Design Requirements document applicability checklist, completing the checklist and performing any required verifications. Success Criteria: The verification shall be considered successful when inspection of the completed CSSS Component and Mechanism Design Requirements document applicability checklist shows the checklist has been completed and approved, and each applicable item has been verified. UMB.257.V Separation of Redundant Mechanical Systems The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of inspection of the Umbilical drawings and hardware. Success Criteria: The verification shall be considered successful when the inspection of the Umbilical drawings and hardware shows that Umbilical mechanical assemblies providing redundant functions are separated or protected to ensure that damage to one is not likely to prevent its redundant counterpart from performing the function. UMB.292.V Restraints for Flexible Hoses The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of lower level verification documentation. Success Criteria: The verification shall be considered successful when inspection of lower level verification documentation shows that high pressure flexible hose installations are restrained to prevent whiplash in the event of a burst.

4.5.1 Materials UMB.218.V Materials and Processes The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the documentation for the verification steps called out in the Exploration Space Suit Materials and Processes Selection, Control, and Implementation Plan, including drawing approval by Materials and Process Engineering. If this verification occurs before flight certification, then all the documentation (including signatures on drawings, MUAs, MIUL, etc) and analysis shall be completed and reviewed prior to acceptance testing. Success Criteria: The verification shall be considered successful when the inspection shows the verification steps called for in the M&P Plan have been completed and documented, and all drawings, procedures, specifications and process control documents affecting flight and ground




support hardware have been approved by M&P Engineering, the Materials and Processes Control Board and signed by Materials and Processes. UMB.219.V Contamination Control The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the drawings and procedures to verify the presence of cleanliness notes; drawing and procedure approval by Materials and Process Engineering and inspection of manufacturing and processing documentation to verify the presence of requirements for cleanliness, packaging and handling the assembly in accordance with the Exploration Space Suit Contamination Control Plan (CSSS-T-014). Success Criteria: The verification shall be considered successful when the inspection shows that the drawings and manufacturing documentation include cleanliness notes; all drawings, procedures, specifications and processing documents affecting flight and ground support hardware have been approved by M&P Engineering, the Materials and Processes Control Board and have been signed by Materials and Processes; processing and manufacturing documentation has been completed and includes the specified quality assurance verifications. UMB.220.V Non Destructive Evaluation The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the documentation for the verification steps called out in the Non-Destructive Evaluation Plan, including drawing approval by Materials and Process Engineering. Success Criteria: The verification shall be considered successful when the inspection shows the verification steps called for in the NDE Plan have been completed and documented, and all drawings, procedures, specifications and process control documents affecting flight and ground support hardware have been approved by M&P Engineering, the Materials and Processes Control Board and signed by Materials and Processes. UMB.221.V Fracture Control The Umbilical's ability to meet this requirement shall be verified by inspection and analysis. The verification shall include fracture control documentation summarized in a Fracture Control Summary Report along with detailed Fracture Control Analysis Reports. The verification shall also include an inspection of the drawings for Materials and Process Engineering approval. Success Criteria: Verification that the design complies with the requirements of CSSS-T-054, Exploration Space Suit Fracture Control Plan shall be considered successful when the Fracture Control Summary Report and all drawings, procedures, specifications and process control documents affecting flight and ground support hardware have been approved by M&P Engineering, the Materials and Processes Control Board and signed by Materials and Processes.




4.5.2 Electrical Design UMB.080.V Mating of Electrical Connectors The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of a inspection of the Umbilical drawings and hardware to verify that design feature are in place to prevent incorrect mating of electrical connectors, plugs, and receptacles with other accessible connectors, plugs, or receptacles. A demonstration shall verify that it is not possible to incorrectly mate electrical connectors, plugs, and receptacles with other accessible connectors, plugs, or receptacles. Success Criteria: The verification shall be considered successful when Inspection of the Umbilical drawings and the hardware shows that electrical connectors, plugs, and receptacles possess design features that prevent incorrect mating with other accessible electrical connectors, plugs, and receptacles and the demonstration shows that it is not possible to incorrectly mate electrical connectors, plugs, and receptacles with other accessible connectors, plugs, or receptacles. UMB.097.V Electrostatic Discharge Protection: Non-Operating The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall be by analysis of the Umbilical design that shows the Umbilical and its components will not be damaged by ESD less than or equal to 4000 volts to the case or to any pin on external connectors when tested using TBD criteria. Success Criteria: The verification shall be considered successful when the analysis of the Umbilical design shows that the Umbilical and its components meet the requirement. UMB.098.V Electrostatic Discharge Protection: Flight Configuration The Umbilical's ability to meet this requirement shall be verified by analysis. The verification shall be by analysis of the Umbilical design that shows the Umbilical and its components will not be damaged by ESD less than or equal to 16,000 volts applied to exposed surfaces while in a flight-installed configuration (both unpowered and powered) and tested using TBD criteria. Success Criteria: The verification shall be considered successful when the analysis of the Umbilical design shows that the Umbilical and its components meet the requirement. UMB.104.V Debris Protection - Electrical The Umbilical ability to meet this requirement shall be verified by inspection and analysis. The verification shall be by inspection of the Umbilical drawings to show that critical Umbilical's electrical components are protected from debris or foreign material that could cause




the component to malfunction. An analysis shall be performed to identify the Umbilical electrical components that are considered critical. Success Criteria: The verification shall be considered successful when inspection of documentation shows that analysis has been performed to identify critical electrical components that are subject to malfunction from debris or foreign material. In addition, the inspection of the Umbilical's drawings verifies the Umbilical's design includes debris-proof covers, shrouds, potting, conformal coating or containers that protect the entire Umbilical prior to use, or that prevent debris from entering into critical areas of the Umbilical's electrical components where the debris could cause a malfunction. UMB.139.V Separation of Redundant Electrical Systems The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall include an inspection of the Umbilical drawings and design documentation to verify that redundant functions of electrical systems are separated or protected to ensure that damage to one is not likely to prevent its redundant counterpart from performing the function. Success Criteria: The verification shall be considered successful when the inspection shows that redundant functions of electrical systems are separated or protected to ensure that damage to one is not likely to prevent its redundant counterpart from performing the function. UMB.192.V Electrical Connector Alignment The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of Umbilical drawings and design documentation to verify the presence of mechanical alignment features. Success Criteria: The verification shall be considered successful when the inspection of Umbilical drawings and design documentation confirms the presence of mechanical alignment features. UMB.198.V Single Point Ground The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of the Umbilical's drawings and hardware to verify the existence of a Single Point Ground scheme for all bonded components. Success Criteria: The verification shall be considered successful when the inspection of the Umbilical drawings and hardware shows the existence of a Single Point Ground scheme for all bonded components. UMB.199.V Shock Hazard - 160 V The Umbilical ability to meet this requirement shall be verified by test.




The verification shall consist of a test to ensure that the Umbilical Assembly limits the crewmember's electrical exposure to 0.1 mA or less when the suit is exposed to a 160V DC or AC RMS voltage source across any two metallic components. Success Criteria: The verification shall be considered successful when the test shows that the assembly limits the crewmember's electrical exposure to 0.1 mA or less when the suit is exposed to a 160V DC or AC RMS voltage source across any two metallic components. UMB.200.V Bonding Class Types The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of inspecting the Umbilical assembly drawings and the manufacturing process documentation to ensure bonding requirements are implemented correctly. Success Criteria: The verification shall be considered successful when the Umbilical assembly drawings and quality inspections prove the bonding was implemented correctly. UMB.361.V EEE Parts Plan Compliance The Umbilical compliance with the CSSS-S-011 Electrical, Electronic, and Electromechanical (EEE) Parts Control Plan shall be verified by inspection. The verification shall consist of an inspection of lower level documentation to verify that the selection of Umbilical electrical, electronic, and electromechanical (EEE) parts is in conformance with the CSSS-S-011 Electrical, Electronic, and Electromechanical (EEE) Parts Control Plan. Success Criteria: The verification shall be considered successful when the inspection of lower level documentation verifies that the selection of Umbilical electrical, electronic, and electromechanical (EEE) parts is in conformance with the CSSS-S-011 Electrical, Electronic, and Electromechanical (EEE) Parts Control Plan. UMB.082.V Moisture Protection for Electrical Components The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the Umbilical Assembly design documentation to verify protection of electrical components from environmental moisture is included in the design. Success Criteria: The verification shall be considered successful when an Inspection of the Umbilical Assembly design documentation shows that electrical components including connectors and wiring junctions to connectors are protected from moisture encountered in their intended environment.




UMB.084.V Mating and Demating of Powered Connectors The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the Umbilical Assembly design and operating procedures to verify that there are no connections of energized components. Success Criteria: The verification shall be considered successful when the inspection of the Umbilical Assembly design and operating procedures shows that there are no connections of energized components. UMB.085.V Protective Covers or Caps for Electrical Receptacles and Plugs The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the Umbilical operating procedures, drawings and design documentation to ensure that the design includes protective covers that achieve the following objectives: 1. Provide protection from moisture for the plugs and receptacles 2. Provide protection against damage to sealing surfaces, threads, and pins 3. Be made of conductive or dissipative materials that provide electrostatic discharge protection


are used 7. Be made of material that is compatible with the connector material 8. Be provided with restraining devices or suitable storage areas if required for on-orbit

activities. Success Criteria: The verification shall be considered successful when Inspection of the Umbilical operating procedures, drawings and design documentation shows that exposed electrical plugs and receptacles include covers that achieve the following objectives: 1. Provide protection from moisture for the plugs and receptacles 2. Provide protection against damage to sealing surfaces, threads, and pins 3. Be made of conductive or dissipative materials that provide electrostatic discharge protection


are used 7. Be made of material that is compatible with the connector material 8. Be provided with restraining devices or suitable storage areas if required for on-orbit

activities.




UMB.086.V Wiring Harness Stress Relief The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall consist of an analysis of stresses that Umbilical electrical wires, cables, bundles and wire harnesses will experience during ground handling and flight operations both at the Integrated Umbilical Assembly and at the integrated suit level. Success Criteria: The verification shall be considered successful when the analysis shows that the electrical wire(s), cables, bundles, and wire harnesses will withstand the stresses they will be subjected to during ground handling and flight operations. UMB.087.V Wiring Harness Protection The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an Inspection of the Umbilical design documentation and hardware both at the Integrated Umbilical Assembly and at the integrated suit level to verify that the Umbilical electrical wire(s), cables, bundles, and wire harnesses are protected to prevent insulation damage from chafing, abrasion and cold flow when passing through or touching any structure or panel. Success Criteria: The verification shall be considered successful when the inspection shows that the Umbilical electrical wire(s), cables, bundles, and wire harnesses are adequately protected from damage to insulation from chafing, abrasion and cold flow. UMB.091.V Critical Pin Assignments The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall be by inspection of the Umbilical drawings to show Umbilical electrical circuits are not routed through adjacent pins of an on-orbit mated electrical connector if a FMEA indicates that a short circuit between them would constitute a single failure that would cause injury to the crew, or loss of a mission critical function. Success Criteria: The verification shall be considered successful when the inspection of the Umbilical's drawings shows that Umbilical's electrical circuits are not routed through adjacent pins of an on-orbit mated electrical connector if a short circuit between them would constitute a single failure that would cause injury to the crew, or loss of a mission critical function. UMB.092.V Corona Suppression The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall be by analysis of an operating integrated Umbilical assembly showing that the Umbilical electrical and electronic equipment precludes corona effects.




Success Criteria: The verification shall be considered successful when the analysis of the Umbilical electrical and electronic equipment shows that the Umbilical design precludes destructive corona effects in applicable operating environments. UMB.096.V Power Transients The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall be by analysis to show that the Umbilical electrical equipment is compatible with the power bus transient environments defined in Figure TBD. Success Criteria: The verification shall be considered successful when the analysis of the Umbilical electrical equipment is compatible with the power bus transient environments.

4.5.3 Fluid Design UMB.088.V Fluid Connector Connections The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the Umbilical drawings to verify that all Umbilical fluid connectors are designed uniquely to prevent incorrect connections with other accessible connectors, plugs or receptacles. Success Criteria: The verification shall be considered successful when inspection of the Umbilical drawings illustrates unique connectors, plugs and receptacles at each fluid connection location. UMB.090.V Fluid Particulate Contamination Control The Umbilical ability to meet this requirement shall be verified by analysis and inspection. The verification shall consist of an analysis of the Umbilical fluid system components to identify those components which are subject to malfunction from particulate contamination of TBD characteristics during EVA or reverse flow situations and an inspection of the Umbilical drawings to verify that appropriate filters have been incorporated where needed. Success Criteria: The verification shall be considered successful when the analysis and inspection show that either no Umbilical fluid system components are subject to malfunction from particulate contamination of TBD characteristics during EVA or reverse flow situations or that appropriate filters have been incorporated to protect those components which are subject to malfunction. UMB.136.V Use of Toxic Materials The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall consist of hazard analysis to show that the Umbilical does not use toxic materials capable of producing toxic fumes.




Success Criteria: The verification shall be considered successful when the hazard analysis has been verified and closed showing that the hardware does not use toxic materials capable of producing toxic fumes above a THL of 0 as defined by the Toxic Hazard Level Table. UMB.194.V Pressurized EVA fluid connectors The Umbilical's ability to meet this requirement shall be verified by test. The verification shall consist of the test of the Umbilical mate/demate mechanism and measuring mating/demating forces. Success Criteria: The verification shall be considered successful when the test of the Umbilical mate/demate mechanism shows that the umbilical connector can be mated/demated with mating/demating forces less than or equal to 12 pounds. UMB.256.V Separation of Redundant Fluid Systems The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of inspection of the Umbilical drawings and hardware. Success Criteria: The verification shall be considered successful when the inspection of the Umbilical drawings and hardware shows that Umbilical fluid assemblies providing redundant functions are separated or protected to ensure that damage to one is not likely to prevent its redundant counterpart from performing the function.

4.5.4 Maintainability UMB.138.V Accessibility for Testing of Redundant Features The Umbilical's ability to meet this requirement shall be verified by inspection. The verification shall include an inspection of the drawings and design documentation to verify accessibility of redundant features for pre-launch testing or on-orbit testing if necessary. Success Criteria: The verification shall be considered successful when the inspection shows that redundant features are designed in such a way that they are accessible for pre-launch testing or on-orbit testing if necessary. UMB.239.V In-Suit Battery Charging The Umbilical ability to meet this requirement shall be verified by analysis and test. The verification shall consist of an analysis that shows that the Umbilical power connector pins and wiring are sized appropriately to handle the battery charging current and voltage levels and a test that demonstrates the Umbilical’s ability to provide the desired current and voltage levels at the suit end of the Umbilical.




Success Criteria: The verification shall be considered successful when the analysis shows that the Umbilical power connector pins and wiring are sized appropriately to handle the battery charging current and voltage levels and the test demonstrates the Umbilical’s ability to provide the desired current and voltage levels at the suit end of the Umbilical.

4.6 Environments UMB.003.V COTS ISS Internal Cargo Environment The Umbilical ability to meet this requirement shall be verified by test and inspection. A thermal vacuum test shall be performed to show that the Umbilical will function after exposure to the thermal and pressure environment defined by the COTS ISS Internal Cargo Environment Table. An inspection of the Umbilical documentation shall verify compliance to the cleanliness requirements defined by the COTS ISS Internal Cargo Environment Table. Success Criteria: The verification shall be considered successful when a functional test shows that the Umbilical Assembly functions after exposure to the thermal and pressure environment as defined by the COTS ISS Internal Cargo Environment Table. UMB.023.V Vehicle induced condensation The Umbilical's ability to meet this requirement shall be verified by analysis. Analyses of the properties of the materials used in the Umbilical will be performed to show that the Umbilical will function after exposure to a condensation level of 95% within a temperature range of 32 to 140 °F. Success Criteria: The verification shall be considered successful when material analyses shows that the Umbilical functions after exposure to humidity within the range specified by the requirement. UMB.024.V Salt Fog The Umbilical ability to meet this requirement shall be verified by analysis. Analyses of the properties of the materials used in the Umbilical will be performed to show that when properly packaged the Umbilical will be compatible with sea salt particle concentrations of 200-300 particles/cm3 (3277-4916 particles/in3) affecting the launch sites, when packaged and not operating. Success Criteria: The verification shall be considered successful when material analyses shows that the Umbilical is compatible with the required sodium chloride concentrations. UMB.025.V Ozone Exposure During Transport The Umbilical ability to meet this requirement shall be verified by analysis.




The verification shall consist of an analysis to evaluate performance of the packaged assembly after exposure to Ozone at concentrations of 3 to 6 parts per 100 million at sea level. The evaluation/analysis (pre-CDR) will determine whether a test is required for verification as part of qualification. Success Criteria: The verification shall be considered successful when the analysis results show that the packaged assembly meets its requirements after being exposed to Ozone at concentrations of 3 to 6 parts per 100 million at sea level. UMB.265.V Atmospheric Composition The Umbilical ability to meet this requirement shall be verified by analysis and inspection. The analysis shall consist of a flammability assessment of the Umbilical assembly in an external environmental partial pressure of Oxygen (ppO2) from 3.2 psi to 8.3 psi (TBR). The verification shall include the inspection of lower level flammability analyses and tests of the integrated Umbilical assembly in an external environmental partial pressure of Oxygen (ppO2) from 3.2 psi to 8.3 psi (TBR). Success Criteria: The verification shall be considered successful when the inspection of lower level flammability analyses and tests shows that the Umbilical Assembly is able to operate in an external environmental partial pressure of Oxygen (ppO2) from 3.2 psi to 8.3 psi (TBR).

4.6.1 Vibration UMB.006.V Random Vibration (Launch) The Umbilical ability to meet this requirement shall be verified by test. The Umbilical shall be properly packaged for launch and the test shall include the margins and durations identified in the CSSS Master Verification Plan (MVP) and Structural Verification Plan (SVP) for both qualification and acceptance tests. The Umbilical will be subjected to a random vibration test using the random vibration environment defined in the Random Vibration for Launch table. The vibration test shall be conducted in all three orthogonal axes. A functional test including leak check, pressure drop and proof pressure will be performed on the Umbilical before and after the random vibration test. Success Criteria: The verification shall be considered successful when the Umbilical successfully completes a functional test after being exposed to the random vibration environment defined in the Random Vibration for Launch Table. UMB.007.V Pre-Launch Sinusoidal Vibration The Umbilical ability to meet this requirement shall be verified by test The Umbilical will be subjected to a sine sweep test. The frequency range for the test shall be 5 to 35 Hz with amplitude of plus and minus 0.25 gs peak to peak. The sweep shall be one octave per minute. The Umbilical will be packaged for transport during the test. A functional test




including leak check, pressure drop and proof pressure will be performed on the Umbilical before and after the sine sweep test. The sine sweep test shall be conducted in three orthogonal axes. Success Criteria: The verification shall be considered successful when the Umbilical passes a functional test after being exposed to the sine sweep test specified in the requirement. UMB.008.V Acoustic Launch Environment The Umbilical ability to meet this requirement shall be verified by analysis. The Analysis shall determine the susceptibility of the hardware as packaged for launch to the defined acoustic environment. If it is determined that the acoustic environment is more severe than the random vibration environment, an acoustic test shall be performed as identified in the CSSS MVP. Success Criteria: The verification shall be considered successful when the analysis shows that the packaged article is not susceptible to the acoustic vibration environment. If the packaged assembly is susceptible to the acoustic vibration environment, the verification shall be considered successful when recorded results show that the assembly is functional after exposure to the specified environment. UMB.273.V Micro-Gravity Random Vibration The Umbilical ability to meet this requirement shall be verified by test. The test shall consist of exposing the Umbilical Assembly to the random vibration environment identified in the random vibration table applied to the Suit/Umbilical and UIA/Umbilical interface. The test shall be preceded and followed by an Umbilical functional test. Success Criteria: The verification shall be considered successful when the test shows the Umbilical hardware meets its performance requirements after exposure to the random vibration environment identified in the on orbit random vibration table applied to the Suit/Umbilical and UIA/Umbilical interface. UMB.274.V Micro Gravity Sinusoidal Vibration The Umbilical ability to meet this requirement shall be verified by test. The Test shall consist of exposure of the Umbilical Assembly to the peak sinusoidal vibration environment defined in the On-orbit Operational Sinusoidal Vibration Envelope table (TBR) and applied to the Suit/Umbilical and UIA/Umbilical interface. The test shall be preceded and followed by an Umbilical functional test. Success Criteria: The verification shall be considered successful when the Umbilical hardware functions properly after exposure to the peak sinusoidal vibration environment defined in the On-orbit Operational Sinusoidal Vibration Envelope table (TBR) and applied to the Umbilical to Suit SRC/URC interface.




UMB.365.V Sinusoidal Vibration in Flight The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test subjecting the packaged and non operating Umbilical assembly to the environment described by the Sinusoidal/ Shock Environment for All Flight Phases Table in all three orthogonal axes. The test shall include the margins and durations identified in the CSSS MVP and SVP for both qualification and acceptance tests. A functional test of the Umbilical assembly is performed before and after exposure to the sinusoidal vibration environment to verify nominal operation. Success Criteria: The verification shall be considered successful when the functional test shows that the Umbilical assembly operates nominally after exposure to the environment described by the Sinusoidal/ Shock Environment for All Flight Phases Table.

4.6.2 Loads UMB.009.V Mechanical Shock The Umbilical ability to meet this requirement shall be verified by test. The Test shall apply MIL-STD-810g, Method 516, Procedure I, as modified to the packaged assembly. Success Criteria: The verification shall be considered successful when the Umbilical successfully completes a functional test after being exposed to the random vibration environment defined in the Shock Environments for Launch Including Dragon for Items Packed in Foam table (TBD). UMB.010.V Vehicle Design Load Factors The Umbilical ability to meet this requirement shall be verified by test. The Test shall follow the Structural Verification Plan (SVP) and shall apply the launch and landing load factors to the Umbilical assembly. Success Criteria: The verification shall be considered successful when the recorded results show that the Umbilical is functional after the launch and landing load. UMB.011.V IVA Contact Loads The Umbilical ability to meet this requirement shall be verified by test. The Test shall follow the Structural Verification Plan (SVP) and shall apply the IVA contact loads to the assembly. The loads can be applied anywhere on the external surface of the umbilical assembly.




Success Criteria: The verification shall be considered successful when the recorded results show that the Umbilical is functional after the IVA contact loads are applied.

4.6.3 Thermal UMB.013.V Temperature Extremes for IVA / Ground Processing (Dry) The Umbilical's ability to meet this requirement shall be verified by analysis. An analysis shall be performed to show that the Umbilical will function during and after exposure to the temperatures described in the "Temperature Extremes for IVA / Ground Operations" table during checkouts. Success Criteria: The verification shall be considered successful when the analysis shows that the Umbilical functions properly during and after exposure to the temperatures described in the requirement during checkouts. UMB.014.V Vehicle Induced Thermal Temperatures (Launch) The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall consist of a thermal analysis to show that the Umbilical assembly, in its stowed configuration, will function after exposure to the wet and dry temperatures described in the Temperature Extremes for Non-Operational/Stowage Table. Success Criteria: The verification shall be considered successful when the analysis shows that the Umbilical functions properly after exposure to the wet and dry temperatures described in the Temperature Extremes for Non-Operational/Stowage table. UMB.015.V On-orbit Operations Temperatures The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall consist of a thermal analysis to show that the Umbilical assembly, in its operational configuration, will function during exposure to the temperature range of +40 F to +109 F. Success Criteria: The verification shall be considered successful when the analysis shows that the Umbilical functions properly during exposure to the temperature range of +40 F to +109 F. UMB.363.V Temperature Extremes for IVA / Ground Operations (Wet) The Umbilical ability to meet this requirement shall be verified by analysis and test. The verification shall consist of a thermal analysis of an operating Umbilical assembly which accounts for ventilation and cooling loop temperatures in the environment's temperature range described in the "Temperature Extremes for IVA / Ground Operations" Table during checkouts. The analysis shall be correlated to a thermal test of the Umbilical assembly.




Success Criteria: The verification shall be considered successful when the analysis results show that the operating Umbilical assembly functions properly during and after exposure to the temperatures described in the requirement during checkouts and the analysis results are corroborated by test results. UMB.364.V Transport and Launch Location Induced Thermal Temperatures for

Shipping Containers The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of placing the packaged and non operating Umbilical assembly in the environment described by the Transport and Launch Location Induced Thermal Temperatures requirement and for the specified durations followed by a functional test of the Umbilical assembly. Success Criteria: The verification shall be considered successful when the functional test shows that the Umbilical assembly operates nominally after exposure to the Transport and Launch Location Induced Thermal Temperatures.

4.6.4 Reserved 4.6.5 Reserved 4.6.6 Magnetic UMB.034.V Electromagnetic Interference (EMI) /Radio Frequency (RF) The Umbilical ability to meet this requirement shall be verified by test The Test shall expose an operating Umbilical to the EMI / RF fields defined in the RF Exposure Limits table and RF Exposure Limits figure and record the results. The test shall include a full operational evaluation such as the functional self-checkout test. Success Criteria: The verification shall be considered successful when the Test results show that the Umbilical Assembly operates nominally during and after exposure to the EMI / RF fields defined in the RF Exposure Limits table and RF Exposure Limits figure. 4.6.7 Pressure UMB.020.V Vehicle Induced Pressure (Launch/Return) The Umbilical ability to meet this requirement shall be verified by test. The Umbilical Assembly, uncharged and non operational, shall be subjected to a test using the 8 Foot Chamber. Testing will be conducted for the pressure range 4.0 x 10^-4 to 14.7 psia which is the pressure range of the 8 Foot Chamber followed by a functional test of the Umbilical assembly.




Success Criteria: Verification will be considered successful when the test results show that the Umbilical Assembly will function after exposure to the absolute pressure range of 1.9 x 10^-13 psia to 18.8 psia. UMB.079.V Stowed Item Pressurization The Umbilical stowage containers' ability to meet this requirement shall be verified by test. The verification shall consist of a test involving the Umbilical's stowage containers and packaging hardware used to stow the Umbilical assembly in a flight-like configuration and exposing the containers to an external pressure rate changes of +/- 1.0 psi/sec. The test shall follow SVP directive for additive and relieving loads. Success Criteria: The test shall be considered successful when it is shown that the packaging hardware has undergone rapid decompression without yielding, fracturing, or sustaining damage. UMB.225.V Umbilical Maximum Pressurization Rate The Umbilical ability to meet this requirement shall be verified by test. The verification shall consist of a test of the umbilical in an operational configuration in a vacuum chamber exposed to external pressurization rates of up to 1.0 psi/sec maximum starting at vacuum and ending at standard atmospheric pressure. Success Criteria: The verification shall be considered successful when the Umbilical successfully completes functional checks during and after being exposed to a vacuum chamber's re-pressurization at rates of up to 1.0 psi/sec maximum.

4.7 Human Interfaces UMB.076.V Tool Free Umbilical Device Actuation The Umbilical ability to meet this requirement shall be verified by inspection and demonstration. The verification shall consist of an inspection of Umbilical drawings to confirm that the Umbilical controls do not require a detached tool to be actuated. A demonstration by suited subjects both in a pressurized and unpressurized suit configuration, shall verify that the subjects can operate Umbilical controls without the aid of a detached tool. The demonstration shall consist of a suited subject and a mockup of Umbilical connectors and controls. Success Criteria: The verification shall be considered successful when all suited subjects, in an unpressurized and pressurized suit, are able to operate umbilical controls without the use of a detached tool. UMB.077.V Positive Indication of Manual Control Position The Umbilical ability to meet this requirement shall be verified by inspection.




The verification shall consist of an inspection of the Umbilical drawings, hardware and design documentation to confirm that the Umbilical controls manually operated will provide a positive indication they are in the desired position. Success Criteria: The verification shall be considered successful when the inspection of the Umbilical drawings shows that the Umbilical controls have markings and features that provide positive indication of manual control. UMB.185.V Hand Controlled EVA Actuator Torque The Umbilical ability to meet this requirement shall be verified by test and demonstration. The test shall consist of measuring the torque required to actuate umbilical controls. The demonstration shall consist of multiple subjects actuating Umbilical controls by gloved hand. Success Criteria: The verification shall be considered successful when the test shows that the motion required to actuate the Umbilical controls does not exceed a torque of 30 in-lb (3.4 Nm) and the suited evaluation of Umbilical controls actuation by gloved hand performed by multiple subjects provide consensus that actuation motions are acceptable. UMB.186.V Finger Controlled EVA Actuator Torque The Umbilical ability to meet this requirement shall be verified by test and demonstration. The test shall consist of measuring the torque required to actuate umbilical controls requiring finger control. The demonstration shall consist of multiple subjects actuating Umbilical controls by gloved hand. Success Criteria: The verification shall be considered successful when the test shows that the motion required to actuate the Umbilical controls does not exceed a torque of 30 in-oz. (21.25 Ncm) and the suited evaluation of Umbilical controls actuation by gloved hand performed by multiple subjects provide consensus that the Umbilical controls actuation motions are acceptable. UMB.244.V Mirror Free Control Actuation The Umbilical ability to meet this requirement shall be verified by demonstration. The verification shall consist of a suited demonstration by various suit subjects of umbilical controls actuation without the use of mirrors in both unpressurized and pressurized (8.3 psid) configurations. Success Criteria: The verification shall be considered successful when the demonstration shows that the suited subjects can operate the Umbilical's controls without requiring the use of a mirror while unpressurized and pressurized at 8.3 psid. UMB.328.V Push-To-Talk Switch Accessibility The Umbilical ability to meet this requirement shall be verified by inspection and demonstration.




The verification shall consist of inspection of the Umbilical Assembly drawings to verify the presence of a push to talk feature and a suited demonstration of the crew's ability to reach and operate the PTT feature. Success Criteria: The verification shall be considered successful when the inspection of the Umbilical Assembly drawings shows the presence of a push to talk feature and a suited demonstration shows that all suited subjects can reach and operate the PTT feature.

4.8 Structures UMB.051.V Software Updates The Umbilical ability to meet this requirement shall be verified by Inspection. The inspection shall include an evaluation of lower level verification documentation. Success Criteria: The verification shall be considered successful when inspection of lower level verification documentation shows that Suit structural components have a minimum creep life of 4.0 times the service life. UMB.288.V Pressurized Hardware Dimensional Stability The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall consist of an analysis to determine if the Umbilical assembly's pressurized hardware maintains dimensional stability required for functionality of structural and mechanical attachments and pressure connections throughout their service life in the applicable environments. The analysis parameters are included in the Structural Verification Plan. Success Criteria: The verification shall be considered successful when the analysis results show the assembly's pressurized hardware maintains dimensional stability required for functionality of structural and mechanical attachments and pressure connections throughout their service life in the applicable environments. UMB.290.V Pressure Relief Devices The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of lower level verification documentation. Success Criteria: The verification shall be considered successful when inspection of lower level verification documentation shows that pressure relief devices provide full-flow relief at a pressure of 110% MDP or lower. UMB.291.V Flow-Induced Vibrations The Umbilical ability to meet this requirement shall be verified by inspection.




The verification shall consist of the inspection of lower level verification documentation. Success Criteria: The verification shall be considered successful when inspection of lower level verification documentation shows that flexible hoses and bellows are designed to exclude or control flow-induced vibrations. UMB.302.V Simultaneous Application of Loads The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of lower level documentation of structural analysis and test procedures to determine if the umbilical structural components meet or exceed structural factors of safety, specified by the Factors of Safety table, when exposed to the highest combination of mechanical, pressure and thermal loads that may occur simultaneously. Success Criteria: The verification shall be considered successful when the lower level verification documentation shows that the Umbilical structural components meet or exceed structural factors of safety, specified by the Factors of Safety table, when exposed to the highest combination of mechanical, pressure, and thermal loads that may occur simultaneously. UMB.303.V Combining with Mechanical Stress/Load The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the stress analysis documentation to determine if the Umbilical assembly mechanical stresses/loads are multiplied by the factor of safety in calculating the design yield or ultimate stress/load if they are relieving or stabilizing to the structure Success Criteria: The verification shall be considered successful when the inspection of the analysis reports shows that the assembly mechanical stresses/loads are not multiplied by the factor of safety in calculating the design yield or ultimate stress/load if they are relieving or stabilizing to the structure. UMB.304.V Combining with Thermal Stress/Load The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the stress analysis documentation to determine if the Umbilical assembly thermal stresses/loads are combined with mechanical and pressure stresses/loads when they are additive but not when they are relieving. Success Criteria: The verification shall be considered successful when the inspection of the analysis reports shows that the assembly thermal stresses/loads are combined with mechanical and pressure stresses/loads when they are additive but not when they are relieving.




UMB.305.V Combining with Pressure Stress/Load The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of lower level documentation. Success Criteria: The verification shall be considered successful when the lower level verification documentation shows that pressure stresses/loads are not multiplied by the factor of safety in calculating the design yield or ultimate stress/load if they are relieving or stabilizing to the structure. UMB.306.V Relieving Pressure Loads The Umbilical's ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of lower level documentation. Success Criteria: The verification shall be considered successful when the lower level verification documentation shows that where Umbilical pressure loads have a relieving or stabilizing effect on structural load capability, the minimum value of such relieving loads is used. UMB.307.V Fatigue Analysis Factor The Umbilical's ability to meet this requirement shall be verified by inspection. The verification shall include an inspection of the fatigue analysis report to determine if the design analysis used to assess the fatigue life of the assembly structure used a Fatigue Analysis Factor (FAF), 1.15 on typical fatigue properties or 1.0 on lower bound fatigue properties, prior to entering the Stress versus Cycle Life (S/N) design curve to determine the low-cycle and high-cycle fatigue life. Success Criteria: The verification shall be considered successful when the inspection shows the assembly design analysis used to assess the fatigue life of the assembly structure multiplied limit stress/strain by a Fatigue Analysis Factor (FAF), 1.15 on typical fatigue properties or 1.0 on lower bound fatigue properties, prior to entering the Stress versus Cycle Life (S/N) design curve to determine the low-cycle and high-cycle fatigue life. UMB.309.V Creep Life Factor The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall include an inspection of the creep life analysis report to determine that the Umbilical structure has adequate structural life with a creep life of 4.0 times the service life. Success Criteria: The verification shall be considered successful when the inspection shows that the Umbilical structure has adequate structural life with a creep life of 4.0 times the service life.




UMB.201.V Umbilical Minimum Factors of Safety (FOS) The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of inspection of verification documentation including analysis and tests at the CI level. Success Criteria: The verification shall be considered successful when an inspection of verification documentation confirms that the Factors of Safety (FOS) and test factors used in the Umbilical design are compliant with the Umbilical Minimum Factors of Safety and Test Factors Table. UMB.310.V Loads Due to Friction (Relieving) The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall include an inspection of the design stress analysis report to determine if the structural components are designed and analyzed such that friction is not considered when it is relieving. Success Criteria: The verification shall be considered successful when the design analysis shows assembly structural components are designed and analyzed such that friction is not considered when it is relieving. UMB.311.V Loads Due to Friction (Additive) The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall include an inspection of the design stress analysis report to determine if the structural components are designed and analyzed such that friction forces are included when they increase the magnitude of the applied load or stress or when they are detrimental to the function of the part. Success Criteria: The verification shall be considered successful when the design analysis shows assembly structural components are designed and analyzed such that friction forces are included when they increase the magnitude of the applied load or stress or when they are detrimental to the function of the part. UMB.312.V Design Loads for Collapse The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of lower level documentation. Success Criteria: The verification shall be considered successful when the lower level verification documentation shows that the Umbilical design loads for collapse use ultimate loads, unless a load component alleviates buckling in which case the ultimate factor of safety is not applied to that component.




UMB.313.V Destabilizing External Pressure or Torsional Loads The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of lower level documentation. Success Criteria: The verification shall be considered successful when the lower level verification documentation shows that Umbilical destabilizing external pressure or torsional limit loads are increased by the ultimate factor of safety. UMB.314.V Stabilizing Internal Pressure Loads The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of umbilical structural analysis to verify that the internal pressure loads applied to the umbilical have not been augmented by the ultimate Factor of Safety unless they reduce structural capability. Success Criteria: The verification shall be considered successful when the inspection of umbilical structural analysis verifies that the internal pressure loads applied to the umbilical have not been augmented by the ultimate Factor of Safety unless they reduce structural capability. UMB.315.V Consideration of Gapping at Interfaces The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall consist of an analysis that determines if the Umbilical assembly exhibits gapping at less than limit load, and if so non-linear analysis shall be included. The analysis parameters are included in the Structural Verification Plan. Success Criteria: The verification shall be considered successful when the analysis shows that non-linear analysis was included if the assembly exhibits gapping at less than limit load UMB.358.V Metallic Pressurized Hardware The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of Umbilical metallic pressure vessels design and manufacturing documentation to verify compliance with ANSI/AIAA-S-080, Standard for Space Systems – Metallic Pressure Vessels, Pressurized Structures, and Pressure Components as specified by UMB.358. Success Criteria: The verification shall be considered successful when the inspection of PLSS metallic pressure vessels design and manufacturing documentation shows compliance with ANSI/AIAA-S-080, Standard for Space Systems – Metallic Pressure Vessels, Pressurized Structures, and Pressure Components as specified by UMB.358.




UMB.203.V Beryllium Structures FOS The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of an inspection of the design and test documentation for the Umbilical beryllium structural hardware to verify that the hardware has been designed and tested to the minimum factors of safety specified in the Minimum Factors of Safety for Beryllium table. Success Criteria: The verification shall be considered successful when the inspection of the design and test documentation for the Umbilical beryllium structural hardware verifies that the hardware has been designed and tested to the minimum factors of safety specified in the Minimum Factors of Safety for Beryllium table. UMB.279.V Ultimate Margin of Safety The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall consist of an analysis to determine if the Umbilical assembly maintains structural integrity with +0.00 or positive Margin(s) of Safety (MS) when exposed to limit loads multiplied by ultimate factors of safety during the service life, including the effect of aging on the hardware. The analysis parameters are included in the Structural Verification Plan. Success Criteria: The verification shall be considered successful when the analysis results show the assembly maintains structural integrity with +0.00 or positive Margin(s) of Safety (MS) when exposed to limit loads multiplied by ultimate factors of safety during the service life, including the effect of aging on the hardware. UMB.280.V Detrimental Deformation The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall consist of an analysis that includes an Umbilical Assembly level summary of the limit loads, stresses, yield safety factors, deformation and margins for the service life of the hardware. The analysis report shall include a summary of various lower level analyses and test data and reports for Umbilical assembly. Success Criteria: The verification shall be considered successful when the analysis results show that the Umbilical structural components have no detrimental deformation when exposed to limit loads multiplied by yield factors of safety during its service life. UMB.281.V Yielding during Ground Transportation The Umbilical's ability to meet this requirement shall be verified by analysis. The verification shall consist of an analysis of the Umbilical assembly structural components to determine if they yield when exposed to ground limit loads multiplied by yield factors of safety during ground transportation, rollout or handling operations. The analysis parameters are




included in the Structural Verification Plan. The analysis report shall include a summary of various lower level analyses and test data and reports for the Umbilical assembly. Success Criteria: The verification shall be considered successful when the analysis results show the assembly structural components do not yield when exposed to ground limit loads multiplied by yield factors of safety during ground transportation, rollout or handling operations UMB.282.V Yield Margins of Safety The Umbilical's ability to meet this requirement shall be verified by analysis. The verification shall consist of an analysis to determine if the Umbilical assembly structural components have +0.00 or positive MS for all yield design load conditions, including the effect of aging on the hardware, except for cases of non-detrimental deformation. The analysis parameters are included in the Structural Verification Plan. The analysis report shall include a summary of various lower level analyses and test data and reports for the Umbilical assembly. Success Criteria: The verification shall be considered successful when the analysis results show the assembly structural components have +0.00 or positive MS for all yield design load conditions, including the effect of aging on the hardware, except for cases of non-detrimental deformation. UMB.286.V Fatigue Life The Umbilical ability to meet this requirement shall be verified by analysis. The verification shall consist of an analysis to determine if the Umbilical assembly structural components have a minimum fatigue life of 4.0 times the service life. The analysis parameters are included in the Structural Verification Plan. Success Criteria: The verification shall be considered successful when the analysis results show the assembly structural components have a minimum fatigue life of 4.0 times the service life. UMB.287.V High-Cycle Fatigue Life The Umbilical ability to meet this requirement shall be verified by inspection. The verification shall consist of the inspection of lower level verification documentation. Success Criteria: The verification shall be considered successful when inspection of lower level verification documentation shows that the Umbilical's structural components subjected to high-cycle fatigue have a minimum fatigue life of 10.0 times the service life.




Table 4.8-1: VCRM Table A:Applicable N/A:Not Applicable N/A

or A Verification

Methods Qual

Acceptance Requirements A D I T Qual Accept 3 REQUIREMENTS N/A 3.1 DESCRIPTION OF THE RECHARGE UMBILICAL ASSEMBLY

N/A

3.2 PERFORMANCE N/A UMB.046 Unassisted Operations A X X UMB.078 On-Orbit Alignment Features A X X UMB.126 Push-To-Talk Signal A X X X X UMB.137 Allowable Pressure Drop A X X X 3.2.1 Reserved N/A 3.2.2 Maintenance N/A UMB.108 In-flight Maintenance and Replacement A X X X UMB.149 Installation Design A X X UMB.234 ORU Captive Fasteners A X X 3.2.3 Reserved N/A 3.2.4 Reliability N/A UMB.047 Umbilical/PLSS Interface Mechanical Components Mate/Demate Cycles

A X X X

UMB.048 Umbilical/Vehicle Interface Mechanical Components Mate/Demate Cycles

A X X X

UMB.049 Umbilical/Vehicle Interface Electrical Connectors Mate/Demate Cycles

A X X X

UMB.050 Umbilical/PLSS Interface Electrical Connectors Mate/Demate Cycles

A X X X

UMB.171 Continuous On-Orbit Service Life A X X X UMB.173 Preventive Maintenance Constraints A X X X 3.2.5 Reserved N/A 3.2.6 Reserved N/A 3.3 PHYSICAL CHARACTERISTICS N/A UMB.327 Umbilical transfer through hatch A X X 3.3.1 Mass N/A UMB.062 Umbilical Dry Mass A X X X 3.3.2 Product Marking N/A UMB.183 Part Identification Marking A X X X UMB.184 Part Marking on Drawings A X X 3.3.3 Cleanliness N/A UMB.115 Elevated Pressure Oxygen Loop Cleanliness A X X X UMB.116 Cooling Water Loop Cleanliness A X X UMB.237 Low Pressure Oxygen Loop Cleanliness A X X X UMB.354 Preflight/Ground Fungal Limit A X X UMB.355 Preflight/Ground Microbial Limit A X X UMB.356 On-orbit Fungal Limit A X X X UMB.357 On-orbit Microbial Limit A X X X




A:Applicable N/A:Not Applicable N/A

or A Verification

Methods Qual

Acceptance Requirements A D I T Qual Accept 3.8 STRUCTURES N/A UMB.051 Creep Life A X X X UMB.201 Umbilical Minimum Factors of Safety (FOS) A X X UMB.203 Beryllium Structures FOS A X X UMB.279 Ultimate Margin of Safety A X X UMB.280 Detrimental Deformation A X X UMB.281 Yielding during Ground Transportation A X X UMB.282 Yield Margins of Safety A X X UMB.286 Fatigue Life A X X UMB.287 High-Cycle Fatigue Life A X X UMB.288 Pressurized Hardware Dimensional Stability A X X UMB.290 Pressure Relief Devices A X X X UMB.291 Flow-Induced Vibrations A X X UMB.302 Simultaneous Application of Loads A X X UMB.303 Combining with Mechanical Stress/Load A X X UMB.304 Combining with Thermal Stress/Load A X X UMB.305 Combining with Pressure Stress/Load A X X UMB.306 Relieving Pressure Loads A X X UMB.307 Fatigue Analysis Factor A X X UMB.309 Creep Life Factor A X X UMB.310 Loads Due to Friction (Relieving) A X X UMB.311 Loads Due to Friction (Additive) A X X UMB.312 Design Loads for Collapse A X X UMB.313 Destabilizing External Pressure or Torsional Loads

A X X

UMB.314 Stabilizing Internal Pressure Loads A X X UMB.315 Consideration of Gapping at Interfaces A X X UMB.358 Metallic Pressurized Hardware A X X X 3.4 INTERFACES N/A UMB.001 Umbilical External Interfaces A X X X UMB.002 Mating to the ISS UIA Panel A X X X UMB.326 Umbilical Stowage During ISS EVA A X X 3.4.1 Vehicle Umbilical Fluid Interfaces N/A UMB.061 Umbilical Water Quality A X X UMB.110 HPO2 Maximum Expected Operating Pressure (MEOP)

A X X X

UMB.111 Umbilical HP O2 Leakage When Attached to Vehicle

A X X X X


A X X X

UMB.113 Umbilical Cooling Water Leakage When Attached to Vehicle

A X X X


A X X X

UMB.117 Feed Water Recharge MEOP A X X UMB.118 Feed Water Biocide Concentration A X X





or A Verification

Methods Qual

Acceptance Requirements A D I T Qual Accept UMB.270 Vehicle Supplied Oxygen Standards A X X UMB.324 HP O2 Pressure Rise Rate A X X X 3.4.2 Vehicle Umbilical Electrical Interfaces N/A UMB.119 Umbilical External Power A X X UMB.121 Electrical Path Resistance A X X X UMB.123 Umbilical to Vehicle Electrical Interface Pin Assignments

A X X X

UMB.124 Provide Hardline Audio to Vehicle A X X X UMB.125 Receive Hardline Audio From Vehicle A X X UMB.128 Exchange Hardline Data with Vehicle A X X X UMB.328 Push-To-Talk Switch Accessibility A X X X X 3.4.3 Umbilical PLSS Electrical Interfaces N/A UMB.122 Umbilical to PLSS Electrical Pin Assignments A X X X 3.4.4 Umbilical PLSS Fluid Interfaces N/A 3.4.5 Reserved N/A 3.4.6 Reserved N/A 3.4.7 Reserved N/A 3.4.8 Reserved N/A 3.5 DESIGN AND CONSTRUCTION N/A UMB.035 Pyrotechnic Devices Prohibited A X X UMB.074 Use of Self Sealing Fluid Connectors A X X UMB.106 Debris Protection - Mechanical Components A X X X UMB.190 Connector Inadvertent Demate A X X X UMB.191 Connector Mating Status A X X UMB.193 Vehicle Tether Attach Limit Load A X X UMB.236 Comply with Component and Mechanism Design Requirements Document

A X X X

UMB.257 Separation of Redundant Mechanical Systems A X X UMB.292 Restraints for Flexible Hoses A X X UMB.298 Small Diameter Critical Seal Redundancy A X X UMB.299 Large Diameter Critical Seal Redundancy A X X 3.5.1 Materials N/A UMB.218 Materials and Processes A X X X UMB.219 Contamination Control A X X UMB.220 Non Destructive Evaluation A X X X UMB.221 Fracture Control A X X X 3.5.2 Electrical Design N/A UMB.080 Mating of Electrical Connectors A X X X UMB.082 Moisture Protection for Electrical Components A X X UMB.084 Mating and Demating of Powered Connectors A X X UMB.085 Protection for Exposed Connectors A X X X UMB.086 Wiring Harness Stress Relief A X X X UMB.087 Wiring Harness Protection A X X X UMB.091 Critical Pin Assignments A X X X UMB.092 Corona Suppression A X X





or A Verification

Methods Qual

Acceptance Requirements A D I T Qual Accept UMB.096 Power Transients A X X UMB.097 Electrostatic Discharge Protection: Non-Operating

A X X

UMB.098 Electrostatic Discharge Protection: Flight Configuration

A X X

UMB.104 Debris Protection - Electrical A X X X UMB.139 Separation of Redundant Electrical Systems A X X UMB.192 Electrical Connector Alignment A X X UMB.198 Single Point Ground A X X X UMB.199 Shock Hazard - 160 V A X X UMB.200 Bonding Class Types A X X UMB.361 EEE Parts Plan Compliance A X X X 3.5.3 Fluid Design N/A UMB.088 Fluid Connector Connections A X X UMB.090 Fluid Particulate Contamination Control A X X X UMB.136 Use of Toxic Materials A X X UMB.194 Pressurized EVA fluid Connections A X X UMB.256 Separation of Redundant Fluid Systems A X X 3.5.4 Maintainability N/A UMB.138 Accessibility for Testing of Redundant Features

A X X X

UMB.239 In-Suit Battery Charging A X X X X 3.6 ENVIRONMENTS N/A UMB.003 COTS ISS Internal Cargo Environment A X X X UMB.023 Vehicle induced condensation A X X UMB.024 Salt Fog A X X UMB.025 Ozone Exposure During Transport A X X UMB.265 Atmospheric Composition A X X X 3.6.1 Vibration N/A UMB.006 Random Vibration (Launch) A X X X UMB.007 Pre-Launch Sinusoidal Vibration A X X UMB.008 Acoustic Launch Environment A X X UMB.273 Micro-Gravity Random Vibration A X X X UMB.274 Micro Gravity Sinusoidal Vibration A X X UMB.365 Sinusoidal Vibration in Flight A X X 3.6.2 Loads N/A UMB.009 Mechanical Shock A X X UMB.010 Vehicle Design Load Factors A X X UMB.011 IVA Contact Loads A X X 3.6.3 Thermal N/A UMB.013 Temperature Extremes for IVA / Ground Processing (Dry)

A X X

UMB.014 Vehicle Induced Thermal Temperatures (Launch)

A X X

UMB.015 On-orbit Operations Temperatures A X X UMB.363 Temperature Extremes for IVA / Ground A X X X





or A Verification

Methods Qual

Acceptance Requirements A D I T Qual Accept Operations (Wet) UMB.364 Transport and Launch Location Induced Thermal Temperatures for Shipping Containers

A X X

3.6.4 Reserved N/A 3.6.5 Reserved N/A 3.6.6 Magnetic N/A UMB.034 Electromagnetic Interference (EMI) /Radio Frequency (RF)

A X X

3.6.7 Pressure N/A UMB.020 Vehicle Induced Pressure (Launch/Return) A X X UMB.079 Stowed Item Pressurization A X X UMB.225 Umbilical Maximum Pressurization Rate A X X 3.7 HUMAN INTERFACES N/A UMB.076 Tool Free Umbilical Device Actuation A X X UMB.077 Positive Indication of Manual Control Position A X X UMB.185 Hand Controlled EVA Actuator Torque A X X X X UMB.186 Finger Controlled EVA Actuator Torque A X X X X UMB.244 Mirror Free Control Actuation A X X




Appendix A – Glossary of Terms Term Definition Umbilical For the purpose of this specification the Umbilical consists of hoses and

cable bundle, vehicle side recharge connector and active side of the suit recharge connector.

Umbilical and Umbilical Assembly

For the purpose of this specification "Umbilical" and "Umbilical Assembly" terminology may be used interchangeably

Critical Seal A critical seal is one through which leakage would constitute a catastrophic or critical failure. Seals through which atmosphere of any habitable volume may leak to the external environment are critical seals. Seals through which flow may intrude into the spacecraft during atmospheric entry are critical seals.

Critical Seal EXS Suit A critical seal is one through which leakage would constitute a catastrophic or critical failure. Seals through which atmosphere of any habitable volume may leak to the external environment at a rate in excess of a critical rate are critical seals. The critical rate is 1.7 lbm GOX with a differential pressure across the seal of 3.1 psid and the seal venting to vacuum. Evaluations of critical rate leakage are to be made assuming full seal bypass [joint evaluated with seal element (e.g. o-ring) removed]. <TBR> <TBR Rationale for Critical Seal Definitions> The critical rate shown is the lower bound for leakage rates that support an emergency EVA return in the event of failure in suit operation in the exploration design. Use of this definition supports a DFMR approach for seals. The GOX pressure system backup supply provides a safe redundancy. Definition is a modification of standard structures definition and will require approval of Safety Review Panel and Structural Engineering at NASA.

Class of bond for fault current return

Class of bond for radio frequency current

Composite Overwrap Pressure Vessel

Design Burst Pressure (DBP)

A pressure level that pressurized hardware must withstand without rupture in the applicable operating environment.

Electrostatic discharge Multiplying factors to be applied to limit loads or stresses for purposes of analytical assessment (design factors) or test verification (test factors) of design adequacy in strength or stability. Factors of safety are deterministically-based and are necessary to assure no failures due to uncertainties that result from the design process, manufacturing process, and the loading environment.

Factor of Safety (FS) Multiplying factors to be applied to limit loads or stresses for purposes of analytical assessment (design factors) or test verification (test factors) of design adequacy in strength or stability. Factors of safety are deterministically-based and are necessary to assure no failures due to




Term Definition uncertainties that result from the design process, manufacturing process, and the loading environment

Maximum Design Pressure (MDP)

The Maximum Design Pressure (MDP) for a pressurized system is the highest pressure defined by the maximum relief pressure, maximum regulator pressure, maximum temperature and transient pressure excursions based on two credible system failures.

Maximum Expected Operating Pressure (MEOP)

The maximum pressure which the pressurized hardware is expected to experience during its service life, in association with its applicable operating environments.

Maximum External Pressure

The maximum pressure environment which the pressurized hardware is expected to experience during its service life.

Negative Pressure Differential

The Maximum External Pressure (MEP) multiplied by the ultimate factor of safety.

Structural Verification Plan




Appendix B - TBX

TBX TBX Type Details Linked Items TBX.0048

TBD

Resolve the external environmental partial pressure of Oxygen (ppO2) and suit pressures in referenced requirement.

UMB.265

TBX.0057

TBR

Parent requirement SS-2026 which identified a higher operating pressure was deleted in the 01 November drop and VI-1017 Feed Water Supply Flow Rate describing the vehicle interface was added. The TBR is to ensure the EXS Suit meets the new parameters.

UMB.117

TBX.0064

TBD

Reconcile EXS mass allotments with parent requirements. Note that government has not defined ancillary mass requirements.

UMB.062

TBX.0080

TBR

This is an early MTBF allocation based on an Engineering Analysis ER 146CSS044 CSSS MTBF Allocation and Apportionment. It needs to be updated.

TBX.0093

TBR TBD, TBD,

TBD

Determine number of cycles and on-time of life support components. This number will feed maintenance plans. Determine number of cycles to be performed at 8.3 psid. TDS 1249 will resolve.

UMB.047, UMB.048, UMB.049, UMB.050

TBX.0111 TBD

Determine PLSS components that are supposed to be maintained or repaired on-orbit.

UMB.108

TBX.0113

TBD

Determine characteristics of particulate contaminants that could affect the ventilation and water loop during an EVA.

UMB.090

TBX.0115 TBD

UMB.090

TBX.0116 TBD, TBD

Determine the launch environments for items packed in foam.

UMB.006, UMB.009

TBX.0117 TBD

Determine Umbilical Electrical Equipment susceptible to power transients.

UMB.096

TBX.0118 TBD

Determine ISS Laptop Connector P/N and PINs UMB.123

TBX.0119 TBD

Determine Umbilical allowable pressure drop through the water loop.

UMB.137

TBX.0120

TBD

Analysis must be performed to establish load path and possible amplification/attenuation of loads from the EDDA interface to the SRC/URC interface and determine appropriate load envelope table.

UMB.274




Appendix C – Requirements to Parents Trace

CEI Req. Num

CEI Req. Name EXS Req. Num

EXS Req. Name

UMB.001 Umbilical External Interfaces EXS.0110 Receive High Pressure Oxygen EXS.0117 Feed Water Fill and Drain EXS.0119 Suit External Power EXS.0123 Suit Electrical Interface Pin

Assignments EXS.0124 Provide Hardline Audio to

Vehicle EXS.0125 Receive Hardline Audio From

Vehicle EXS.0126 Provide Hardline Audio Key

Signal EXS.0128 Exchange Hardline Data with

Vehicle Laptop EXS.0147 Provide Tether Points EXS.0154 Receive Potable Water From

Galley EXS.0193 Vehicle Tether Attach EXS.0250 Provide External Power Interface EXS.0251 Provide External Data Interface EXS.0318 Recharge Suit Consumables

During EVA EXS.0323 Software and Firmware

Modification Control EXS.0325 Data Exchange Through

Umbilical EXS.0326 Umbilical Stowage During ISS

EVA UMB.002 Mating to the ISS UIA Panel EXS.0123 Suit Electrical Interface Pin

Assignments UMB.003 COTS ISS Internal Cargo

Environment

UMB.006 Random Vibration (Launch) EXS.0006 Random Vibration UMB.007 Pre-Launch Sinusoidal Vibration EXS.0007 Sinusoidal Vibration UMB.008 Acoustic Launch Environment EXS.0014 Temperature Extremes for Non-

Operational / Stowage UMB.009 Mechanical Shock EXS.0009 Mechanical Shock UMB.010 Vehicle Design Load Factors EXS.0010 Load Factors UMB.011 IVA Contact Loads EXS.0011 IVA Contact Loads




CEI Req. Num


EXS Req. Name

UMB.013 Temperature Extremes for IVA / Ground Processing (Dry)

EXS.0013 Temperature Extremes for IVA / Ground Operations - Dry

UMB.014 Vehicle Induced Thermal Temperatures (Launch)

EXS.0014 Temperature Extremes for Non-Operational / Stowage

UMB.015 On-orbit Operations Temperatures EXS.0363 Temperature Extremes for IVA / Ground Operations - Wet

UMB.020 Vehicle Induced Pressure (Launch/Return)

EXS.0020 Absolute Pressure

UMB.023 Vehicle induced condensation EXS.0023 Humidity UMB.024 Salt Fog EXS.0024 Salt Fog UMB.025 Ozone Exposure During Transport EXS.0025 Ozone Exposure During Transport EXS.0260 Exposure to Ozone UMB.034 Electromagnetic Interference

(EMI) /Radio Frequency (RF) EXS.0034 Electromagnetic Interference

(EMI) /Radio Frequency (RF) UMB.035 Pyrotechnic Devices Prohibited EXS.0035 Pyrotechnic Devices Prohibited UMB.046 Unassisted Operations EXS.0046 Unassisted Operations UMB.047 Umbilical/PLSS Interface

Mechanical Components Mate/Demate Cycles

EXS.0173 Preventive Maintenance Constraints

UMB.048 Umbilical/Vehicle Interface Mechanical Components Mate/Demate Cycles


UMB.049 Umbilical/Vehicle Interface Electrical Connectors Mate/Demate Cycles


UMB.050 Umbilical/PLSS Interface Electrical Connectors Mate/Demate Cycles


UMB.051 Creep Life EXS.0361 Creep Life UMB.061 Umbilical Water Quality EXS.0061 Feedwater Contamination UMB.062 Umbilical Dry Mass EXS.0353 Suit Ancillary Dry Mass UMB.074 Use of Self Sealing Fluid

Connectors EXS.0074 Use of Self Sealing Fluid

Connectors UMB.076 Tool Free Umbilical Device

Actuation EXS.0076 Tool Free Suit Device Actuation

UMB.077 Positive Indication of Manual Control Position

EXS.0077 Positive Indication of Manual Control Position

UMB.078 On-Orbit Alignment Features EXS.0078 On-Orbit Alignment Features UMB.079 Stowed Item Pressurization EXS.0079 Stowed Item Pressurization UMB.080 Mating of Electrical Connectors EXS.0080 Mating of Electrical Connectors UMB.082 Moisture Protection for Electrical EXS.0082 Moisture Protection for Electrical




CEI Req. Num


EXS Req. Name

Components Components UMB.084 Mating and Demating of Powered

Connectors EXS.0084 Mating and Demating of Powered

Connectors UMB.085 Protection for Exposed

Connectors EXS.0085 Protection for Exposed

Connectors UMB.086 Wiring Harness Stress Relief EXS.0086 Wiring Harness Stress Relief UMB.087 Wiring Harness Protection EXS.0087 Wiring Harness Protection UMB.088 Fluid Connector Connections EXS.0088 Fluid Connector Connections UMB.090 Fluid Particulate Contamination

Control EXS.0090 Fluid Particulate Contamination

Control UMB.091 Critical Pin Assignments EXS.0091 Critical Pin Assignments UMB.092 Corona Suppression EXS.0092 Corona Suppression UMB.096 Power Transients EXS.0096 Power Transients UMB.097 Electrostatic Discharge

Protection: Non-Operating EXS.0097 Electrostatic Discharge

Protection: Non-Operating UMB.098 Electrostatic Discharge

Protection: Flight Configuration EXS.0098 Electrostatic Discharge

Protection: Flight Configuration UMB.104 Debris Protection - Electrical EXS.0104 Debris Protection - Electrical UMB.106 Debris Protection - Mechanical

Components EXS.0106 Debris Protection - Mechanical

Components UMB.108 In-flight Maintenance and

Replacement EXS.0108 On-Orbit Replaceable Units

EXS.0109 Interchangeability UMB.110 HPO2 Maximum Expected

Operating Pressure (MEOP) EXS.0110 Receive High Pressure Oxygen

UMB.111 Umbilical HP O2 Leakage When Attached to Vehicle

EXS.0111 Suit HP O2 Leakage When Attached to Vehicle



UMB.113 Umbilical Cooling Water Leakage When Attached to Vehicle

EXS.0113 Suit Umbilical Cooling Water Leakage When Attached to Vehicle



UMB.115 Elevated Pressure Oxygen Loop Cleanliness

EXS.0115 Elevated Pressure Oxygen Loop Cleanliness

UMB.116 Cooling Water Loop Cleanliness EXS.0116 Cooling Water Loop Cleanliness UMB.117 Feed Water Recharge MEOP EXS.0117 Feed Water Fill and Drain UMB.118 Feed Water Biocide EXS.0118 Feed Water Biocide




CEI Req. Num


EXS Req. Name

Concentration Concentration UMB.119 Umbilical External Power EXS.0119 Suit External Power UMB.121 Electrical Path Resistance EXS.0121 Electrical Path Resistance UMB.122 Umbilical to PLSS Electrical Pin

Assignments EXS.0123 Suit Electrical Interface Pin

Assignments UMB.123 Umbilical to Vehicle Electrical

Interface Pin Assignments EXS.0123 Suit Electrical Interface Pin

Assignments EXS.0124 Provide Hardline Audio to


Vehicle EXS.0126 Provide Hardline Audio Key

Signal EXS.0128 Exchange Hardline Data with

Vehicle Laptop UMB.124 Provide Hardline Audio to

Vehicle EXS.0124 Provide Hardline Audio to

Vehicle UMB.125 Receive Hardline Audio From


Vehicle UMB.126 Push-To-Talk Signal EXS.0254 Suit Communication Audio

Modes UMB.128 Exchange Hardline Data with

Vehicle EXS.0128 Exchange Hardline Data with

Vehicle Laptop UMB.136 Use of Toxic Materials EXS.0136 Use of Toxic Fluids UMB.137 Allowable Pressure Drop EXS.0112 Pump Cooling Water Through

Vehicle Heat Exchanger UMB.138 Accessibility for Testing of

Redundant Features EXS.0138 Testing of Redundant Features

UMB.139 Separation of Redundant Electrical Systems

EXS.0139 Separation of Redundant Electrical Systems

UMB.149 Installation Design EXS.0149 Installation Design UMB.171 Continuous On-Orbit Service Life EXS.0171 Continuous On-Orbit Service Life UMB.173 Preventive Maintenance

Constraints EXS.0173 Preventive Maintenance

Constraints UMB.183 Part Identification Marking EXS.0183 Part Identification Marking UMB.184 Part Marking on Drawings EXS.0184 Part Marking on Drawings UMB.185 Hand Controlled EVA Actuator

Torque EXS.0185 Hand Controlled EVA Actuator

Torque UMB.186 Finger Controlled EVA Actuator

Torque EXS.0186 Finger Controlled EVA Actuator

Torque UMB.190 Connector Inadvertent Demate EXS.0190 EVA Connector Inadvertent




CEI Req. Num


EXS Req. Name

Demate UMB.191 Connector Mating Status EXS.0191 EVA Connector Mating Status UMB.192 Electrical Connector Alignment EXS.0192 EVA Electrical Connector

Alignment UMB.193 Vehicle Tether Attach Limit Load EXS.0193 Vehicle Tether Attach UMB.194 Pressurized EVA fluid

Connections EXS.0194 Pressurized EVA fluid

Connections UMB.198 Single Point Ground EXS.0198 Single Point Ground UMB.199 Shock Hazard - 160 V EXS.0199 Shock Hazard UMB.200 Bonding Class Types EXS.0200 Bonding Class Types UMB.201 Umbilical Minimum Factors of

Safety (FOS) EXS.0201 Mechanical and Thermal Factors

of Safety UMB.203 Beryllium Structures FOS EXS.0203 Beryllium Structures FOS UMB.218 Materials and Processes EXS.0218 Materials and Processes UMB.219 Contamination Control EXS.0219 Contamination Control UMB.220 Non-Destructive Evaluation EXS.0220 Non-Destructive Evaluation UMB.221 Fracture Control EXS.0221 Fracture Control UMB.225 Umbilical Maximum

Pressurization Rate EXS.0225 Suit Maximum Pressurization

Rate UMB.234 ORU Captive Fasteners EXS.0234 ORU Captive Fasteners UMB.236 Comply with Component and

Mechanism Design Requirements Document

EXS.0236 Comply with Component and Mechanism Design Requirements Document

UMB.237 Low Pressure Oxygen Loop Cleanliness

EXS.0237 Low Pressure Oxygen Loop Cleanliness

UMB.239 In-Suit Battery Charging EXS.0239 In Suit Battery Charging UMB.244 Mirror Free Control Actuation EXS.0244 Mirror Free Control Actuation UMB.256 Separation of Redundant Fluid

Systems EXS.0256 Separation of Redundant Fluid

Systems UMB.257 Separation of Redundant

Mechanical Systems EXS.0257 Separation of Redundant

Mechanical Systems UMB.265 Atmospheric Composition EXS.0265 Atmospheric Composition UMB.270 Vehicle Supplied Oxygen

Standards EXS.0270 Vehicle Supplied Oxygen

Standards UMB.273 Micro-Gravity Random Vibration EXS.0273 Suit Micro-Gravity Random

Vibration UMB.274 Micro Gravity Sinusoidal

Vibration EXS.0274 Suit Micro Gravity Sinusoidal

Vibration UMB.279 Ultimate Margin of Safety EXS.0279 Ultimate Margin of Safety UMB.280 Detrimental Deformation EXS.0280 Detrimental Deformation




CEI Req. Num


EXS Req. Name

UMB.281 Yielding during Ground Transportation

EXS.0281 Yielding during Ground Transportation

UMB.282 Yield Margins of Safety EXS.0282 Yield Margins of Safety UMB.286 Fatigue Life EXS.0286 Fatigue Life UMB.287 High-Cycle Fatigue Life EXS.0287 High-Cycle Fatigue Life UMB.288 Pressurized Hardware

Dimensional Stability EXS.0288 Pressurized Hardware

Dimensional Stability UMB.290 Pressure Relief Devices EXS.0290 Relief Devices UMB.291 Flow-Induced Vibrations EXS.0291 Flow-Induced Vibrations UMB.292 Restraints for Flexible Hoses EXS.0292 Restraints for Flexible Hoses UMB.298 Small Diameter Critical Seal

Redundancy EXS.0298 Small Diameter Critical Seal

Redundancy UMB.299 Large Diameter Critical Seal

Redundancy EXS.0299 Large Diameter Critical Seal

Redundancy UMB.302 Simultaneous Application of

Loads EXS.0302 Combined Loading

UMB.303 Combining with Mechanical Stress/Load

EXS.0303 Combining with Mechanical Stress/Load

UMB.304 Combining with Thermal Stress/Load

EXS.0304 Combining with Thermal Stress/Load

UMB.305 Combining with Pressure Stress/Load

EXS.0305 Combining with Pressure Stress/Load

UMB.306 Relieving Pressure Loads EXS.0306 Relieving Pressure Loads UMB.307 Fatigue Analysis Factor EXS.0307 Fatigue Analysis Factor UMB.309 Creep Life Factor EXS.0309 Creep Life Factor UMB.310 Loads Due to Friction (Relieving) EXS.0310 Loads Due to Friction (Relieving) UMB.311 Loads Due to Friction (Additive) EXS.0311 Loads Due to Friction (Additive) UMB.312 Design Loads for Collapse EXS.0312 Design Loads for Collapse UMB.313 Destabilizing External Pressure or

Torsional Loads EXS.0313 Destabilizing External Pressure or

Torsional Loads UMB.314 Stabilizing Internal Pressure

Loads EXS.0314 Stabilizing Internal Pressure

Loads UMB.315 Consideration of Gapping at

Interfaces EXS.0315 Consideration of Gapping at

Interfaces UMB.324 HP O2 Pressure Rise Rate EXS.0324 HP O2 Pressure Rise Rate UMB.326 Umbilical Stowage During ISS

EVA EXS.0326 Umbilical Stowage During ISS

EVA UMB.327 Umbilical transfer through hatch EXS.0327 Unpressurized Suit Size

Constraint UMB.328 Push-To-Talk Switch

Accessibility EXS.0254 Suit Communication Audio

Modes




CEI Req. Num


EXS Req. Name

UMB.354 Preflight/Ground Fungal Limit EXS.0354 Cleaning Levels, Pre Flight UMB.355 Preflight/Ground Microbial Limit EXS.0354 Cleaning Levels, Pre Flight UMB.356 On-orbit Fungal Limit EXS.0355 Cleaning Levels, On Orbit UMB.357 On-orbit Microbial Limit EXS.0355 Cleaning Levels, On Orbit UMB.358 Metallic Pressurized Hardware UMB.361 EEE Parts Plan Compliance EXS.0368 Selection of EEE Parts

Compliance UMB.363 Temperature Extremes for IVA /

Ground Operations (Wet) EXS.0363 Temperature Extremes for IVA /

Ground Operations - Wet UMB.364 Transport and Launch Location

Induced Thermal Temperatures for Shipping Containers

EXS.0364 External Environments for Shipping Containers

UMB.365 Sinusoidal Vibration in Flight EXS.0365 Sinusoidal Vibration in Flight