ADVANCING TECHNOLOGY AND EDUCATION FOR A HUMAN BASE ON THE MOON AND FOOTPRINTS ON MARS

Nancy J. Currie, Ph.D.Deputy Director, JSC EngineeringNASA, Johnson Space Center

Presentation to the Engineering Dean’s Conference

ADVANCING TECHNOLOGY & EDUCATION FOR A HUMAN BASE ON THE MOON AND FOOTPRINTS ON MARS

AGENDAChallenges

Space Shuttle International Space Station Constellation

Examples of Current Collaborations with Academia Dexterous Robotics Autonomous Rendezvous and Docking

Preparation of NASA’s Future Engineering Workforce Working in multi-disciplinary teams Systems Engineering Process and procedures

Vision for Space Exploration

Space Shuttle Use Space Shuttle to transport elements and complete assembly of the

International Space Station (ISS) Retire the Space Shuttle when ISS assembly is complete (2010)

International Space Station Complete ISS assembly including the U.S. components that support U.S.

and foreign partners space exploration goals Focus ISS research on supporting space exploration goals

Space Exploration Beyond Low Earth Orbit Undertake lunar exploration activities to enable sustained human and

robotic exploration of Mars and more distant destinations in the solar system Initiate a series of robotic missions to the Moon to prepare for and support

future human exploration activities Conduct the first extended human expedition to the lunar surface as early

as possible but no later than the year 2020 Use lunar exploration activities to further science, and to develop and test

new approaches, technologies, and systems, including use of lunar and other space resources, to support sustained human space exploration to Mars and other destinations

Engineering Challenges Associated with the Space Shuttle

Safe and successful completion of all missions through end of program life

Risk due to debris can never be completely eliminated Impacts from debris is an inherent risk based on Space Shuttle design Minimal tolerance for debris impacts

Methods to repair the Shuttle’s thermal protection system (TPS) on orbit are desired

TPS repair consists of three problems: Materials capable of withstanding entry temperatures and concepts for

attachment of repair systems Operability problems performing repairs in the space environment

(microgravity, thermal) Engineering verification that repairs can withstand the thermal effects

during entry Repair Capabilities

Tile - Emittance wash; Shuttle Tile Ablator-54; Tile overlay Reinforce Carbon-Carbon - Crack repairs, Plugs, Overlay*

* R&D development project

Space Shuttle Foam Impact Analysis and Testing

Foam projectile representative debris released during STS-107:19” x 11.5” x 5.5”1.67 lbsdensity of 2.4 lbs/ft3

Velocity at liberation ~2,300 fpsVelocity at impact ~1,500 fps ∆V due to low ballistic coefficient of low-density foam

Foam projectile representative debris released during STS-107:19” x 11.5” x 5.5”1.67 lbsdensity of 2.4 lbs/ft3

Velocity at liberation ~2,300 fpsVelocity at impact ~1,500 fps ∆V due to low ballistic coefficient of low-density foam

Foam projectile representative debris released during STS-107:19” x 11.5” x 5.5”1.67 lbsdensity of 2.4 lbs/ft3

Velocity at liberation ~2,300 fpsVelocity at impact ~1,500 fps ∆V due to low ballistic coefficient of low-density foam

Space Shuttle Challenge - Tile Repair

Emittance Wash RTV base material with silicon carbide filler Apply material on damaged tiles to increase

heat rejection through radiation by increasing surface emittance (ε) to >0.76

Shuttle Tile Ablator 54 (STA-54) Mixture of Room-Temperature-Vulcanizing

(RTV) rubber, glass microballoons, silicone oil, a fumed silica, and a catalyst

RTV material serves as the base material for the reaction is mixed with a catalyst

Silicone condensation reaction creates a silicone rubber that is pyrolized during entry heating to a ceramic state

Materials loaded into two separate tubes housed in a caulk-gun-like applicator which mixes the two parts as EVA astronauts dispense it into the damaged area

Space Shuttle Challenge - Tile Repair

Tile Overlay Concept Purpose: Elevate thermal capability of the damaged thermal protection system tiles

by covering damaged area with a thin, flexible plate Tile Overlay repair hardware consists of four parts:

Coated C/SiC overlay plate (0.040” x 15” x 25”) shielding the damage area from plasma flow

Compliant alumina (Saffil) as gasket to eliminate plasma flow between cover plate and tile OML and reduce radiant heating

Saffil blankets/bags inside the cavity to minimize radiant heating Augers/washers to secure cover plate to Vehicle

“Skip” maneuver can be used to adjust landing site to guarantee anytime return from any lunar latitude to a single identified CONUS landing location

Capability to perform a skip entry estimated at Technology Readiness Level 3

Guidance, navigation, control, TPS, aerodynamics, environment, mass properties

STS-107 investigation concluded a number of high atmosphere phenomena (winds, density shears) challenge entry guidance algorithms

Engineering Challenges for Crew Exploration Vehicle Skip Entry

Landing site

TEI

Moon at -28.6 degsMinimum declination

Constant Radius AccessCircle (CRAC) 7,350 nm

Entry Interface

Antipode

7,350 nm DescendingApproach to KSC

SMDisposalFootprint

NominalBallisticAbortLanding

7,350 nm AscendingApproach to KSC

Antipode motionduring lunar month

Engineering Challenges for Automated Rendezvous and Docking

Automated Rendezvous and Docking is not a system; but a complex phase of flight that is tightly integrated with many vehicle subsystems

Automated is typically used to mean “scripted;” Autonomous is used for applications that operate without human intervention

Level of automation or autonomy varies greatly based on application

Influencedby AR&D

Subsystems or Areas that are integrated for

AR&D

Flight System

GN&C

C&DH

COMM.

HUMAN INTERFACE

DOCKING SYSTEM

FLIGHT PROCESSORS

POWER

SENSORS

IVHM

FDIR

Mission Manager

THERMAL

VEHICLECONFIG

PROPULSION

EXTERNAL SYSTEM (Grnd, GPS, TDRSS, Etc.)

GROUND PLANNING

Influencedby AR&D

Subsystems or Areas that are integrated for

AR&D

Flight System

GN&C

C&DH

COMM.

HUMAN INTERFACE

DOCKING SYSTEM

FLIGHT PROCESSORS

POWER

SENSORS

IVHM

FDIR

Mission Manager

THERMAL

VEHICLECONFIG

PROPULSION

EXTERNAL SYSTEM (Grnd, GPS, TDRSS, Etc.)

GROUND PLANNING

Engineering Challenges: Docking/Capture Systems

Docking/capture envelope influences: Relative navigation sensor accuracy requirements Trajectory and approach profile Vehicle thruster size and placement

Extremely specialized field with few experts (even internationally)

Low Impact Docking System (LIDS) for the Crew Exploration Vehicle

Two docking systems are under consideration for CEV docking to the International Space Station - Androgynous Peripheral Attachment System (APAS) and the Low Impact Docking System (LIDS)

Two docking systems are under consideration for CEV docking to the International Space Station - Androgynous Peripheral Attachment System (APAS) and the Low Impact Docking System (LIDS)

Engineering Challenges: Relative Navigation Sensors

Relative navigation sensors are used to provide the crew, vehicle, and

ground elements with relative navigation data between two spacecraft Provide the backbone for the capability to have automated operations Provide “situational awareness” for piloted operations

Relative navigation sensors may be laser-based, radio frequency (RF)-

based, or based on a video system Laser-based and video based typically have reflectors or visual targets on the target

spacecraft

Specific Challenges: Technology is too immature for human spaceflight (low technology readiness levels) Sensor redundancy and overlap for reliability Sensors that provide good accuracy at short range do not necessarily provide long

range capability Sensor placement and visibility Target infrastructure to support sensors (reflectors, transponders, visual targets, etc.)

Academic Collaborations - Robotics

Focus Areas Surface Mobility

Crew mobility on Lunar Surface Movement of cargo on Lunar Surface

Surface Handling Deployment of instruments Assembly and Repair

Command & Control Earth-Moon Time Delays Human-Robot EVA Teams

Current University Collaborations Dexterous Manipulation (UMass) Motion Control (Clemson) Learning Algorithms (Vanderbilt) Autonomous Manipulation (MIT) Lunar Polar Exploration (CMU)

Recent Academic PartnersUniversity of Southern California; University of Texas-Austin; Texas A&M, University of Houston, University of Washington,Rice University, University of Oklahoma

Academic Collaborations - Autonomous Rendezvous and Docking

Ability for two spacecraft to autonomously rendezvous and dock (AR&D) is critical for the success of future human spaceflight missions

Two universities (University of Texas & Texas A&M University) will independently build two spacecraft with communications and mechanically interfaces for successful rendezvous and dock

Project initiated by JSC Engineering, Aeroscience and Flight Mechanics Division in the fall of 2005

Anticipated to be an 8-year program - satellite launches ~ every 2 years JSC Engineers serve as mentors with significant support and assistance

from the faculty and staff of both universities Objectives of the project include:

Demonstrate precision relative navigation Demonstrate precision real-time navigation Provide orbit determination Mission duration - minimum of 24 hours Data collection and downlink over 75% of the mission duration

JSC Engineering Workforce Demographics

Degree Fields - Directorate

1

166

1 2 1 2 1027 20

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3 2 1 111 4

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Degree Field - Directorate

Aero16619% BusAdmin

273%

Comp364%

Elec17120%Math

273%

Mech22426%

All Other19622%

Physics293%

Directorate Distribution by Age

0

5

10

15

20

25

30

35

40

45

50

20 25 30 35 40 45 50 55 60 65 70 75 80 85

Age

Highest Degrees - Directorate

None445%

Bach47656%

Mast26331%

PhD587%

Assoc6

1%

Preparation of JSC’s Engineering Future Workforce

Experience working in multi-disciplinary teams Design of most spacecraft systems requires a “Mechatronics” approach

Electrical, mechanical, aero, software “Optimal” design rarely possible, compromise almost always required to

meet myriad of competing requirements Training in Systems Engineering

Skills in systems engineering and integration are extremely important for design and development of large-scale aerospace projects

Government will have a more substantial role in spacecraft development Use of collaborative engineering tools

NASA and most large aerospace companies are geographically dispersed Process and procedures associated with engineering projects

Student projects can use real-world examples and the phasing of project deadlines can emulate typical project milestones

Requirements, design, and safety reviews Familiarizes students with typical project management constraints –

technical, schedule, cost

Preparation of NASA’s Future Engineering Workforce

Training in Systems Engineering Systems integration and control Systems acquisition and life cycle management Requirements development/analysis/management System verification/validation Integrated planning and scheduling Cost estimating Risk Management

Pilot Program in Systems Engineering 39 engineers at JSC will participate Courses taught by California Institute of Technology (professors will travel to

JSC) and University of Southern California (distance learning)

QUESTIONS?

JSC Engineering Contact Information Director:

Mr. Stephen J. Altemus; 281-483-1396; stephen.j.altemus@nasa.gov

Deputy Director: Dr. Nancy J. Currie; 281-483-8018; n.currie@nasa.gov

Mailing Address:NASA – Johnson Space CenterMailcode EA2101 NASA ParkwayHouston, TX 77058

ADVANCING TECHNOLOGY AND EDUCATION FOR A HUMAN BASE ON THE MOON AND FOOTPRINTS ON MARS