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Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Crew Systems and Life Support
Establishing a Recurring Human Presence on the Moon
Preliminary Design Review
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Overview
• Preliminary Design Review of Crew Systems / Life Support aboard low-cost lunar lander – Atmosphere / O2
– Water
– Food
– Waste Management
• Human Factors and Habitability – Seating
– Control Stations and Windows
– Stowage and Placement
– Ingress / Egress
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Requirements
• 3 Crew Members
• 10 day mission (+3 contingency days) – 3 days transit
– 4 days on lunar surface
– 3 days return to Earth
– Plan for 13 days total (includes 3 contingency days)
• Crew will occupy Crew Vehicle for duration of mission (launch to landing) – Exit Crew Vehicle only during EVAs on lunar surface
– Cannot receive / transfer supplies
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Requirements
• Max diameter 3.57 m (at bottom of spacecraft)
• Half-cone angle of 25°
• Wall thickness 10 cm
• Maximum allowed mass: 1500 kg
– Includes crew systems, life support, crew members, spacesuits, chairs
– Does Not include ladder, avionics, control stations
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Air System Assumptions
• Each EVA 5 hours, airlock remains open, all atmosphere lost each EVA
• CO2 canisters are usable for both cabin and suits
• EMU suit volume is maximum (0.153 m3) and has own dehumidification/heat exchange system
• EMU can be “recharged” with O2/N2 upon return
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Cabin Atmosphere Trade
100
150
200
250
300
350
400
5.6 6.6 7.6 8.6 9.6 10.6
Tan
k M
ass
(kg)
Interior Volume (m3)
Total Tank Mass at Select Spacecraft Volumes
5psi, Heavy Respiration
10 psi, Heavy Respiration
5psi, Light Respiration
10 psi, Light Respiration
APOLLO CM APOLLO LM SPACEX DRAGONLAB [1]
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Pressure / O2 content for Interior Cockpit
Total Pressure (psia)
Normoxic Partial Pressure (psia-O2)
Normoxic Concentrations (percentage of O2)
3.7 3.7 100 4 3.62 90.5 5 3.45 69 6 3.36 56 7 3.29 47 8 3.24 40 9 3.2 35.5 10 3.17 31.7 14.7 3.08 21
Table acquired from [3]
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Final Tank Masses
Atm. Pressure @Light Resp Rate (5psi) (10 psi) O2 mass for consumption, cabin and suit (kg) 118.47 117.64 Tank and gas total (kg) 201.40 199.98 Tank Volume (m3) 0.073 0.072 N2 mass for consumption, cabin and suit (kg) 14.58 27.93 Tank and gas total (kg) 24.79 47.48 Tank Volume (m3) 0.182 0.349
Total mass of tanks (for cabin) (kg) 226.20 247.47 Total Energy Req. (MJ) 28.255 30.733
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Humidity Removal at Low Pressures
• Incredibly large systems required for humidity/distillation process reuse
• Dessicant Requires 266.63 kg + 10% wt packaging [5], Unsuitable
• Dehumidification system suitable for small volume (6.7 m3), allows for condensate removal and relative constant humidity(~40%) based on parameter controls
• Mass 16 kg and 33 x 48 x 25 cm, 410 W power [6]
• May be redundant if heat exchange system is optimized for condensate removal
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Water Accumulated in Module over Time
0
5
10
15
20
25
30
0 2 4 6 8 10 12 14
Lite
rs W
ate
r A
ccu
mu
late
d
Mission Days
Water Produced
0.28 Leftover
.275 Leftover
0.25 Leftover
0.2 Leftover
0.1 Leftover
Rates in L/hr, constant rate of water production at 0.285 L/hr
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Apollo Environmental Control System
Photos via [4]
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
CO2 Level During Mission - Light Resp. Rate
0 2 4 6 8 10 12 14
0
10000
20000
30000
40000
50000
60000
Carbon Dioxide Levels During Mission
EVA Airlock Jettison Inclusion
Mission Days Elapsed
Gra
ms
Ca
rbo
n D
ioxi
de
/ C
ub
ed
Me
ter
SMAC limit [2] (23 g/m3)
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
CO2 Removal Comparisons
Mass (kg) CO2 to remove 43.44 KO2
Used for CO2 and O2 Production in Combination with Liq O2 KO2 140.12 Generates O2 53.25 Total Mass 672.60
LiOH CO2 Removal (ExtendAir® LiOH Absorbent Curtains) LiOH (0.794 kg CO2
/ kg LiOH) 54.71 Packaging (.7 kg/4.6 kg gross mass canister) 9.82 Total Mass 64.53 KO2
Used Only for O2 Production (CO2 Removed with Surplus) KO2 311.77 Generates O2 118.47 Total Mass 1496.50
Infeasible
Option Chosen
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Atmospheric Conclusions
• 5 psi Atmosphere chosen (lowest tank mass, No denitrification needed [R=0.69]) – Advantage in no pre-breathe, but material
flammability can be a concern as well as crew comfort
– Light Respiration rate chosen (slightly larger than ALS Baseline Values Assumptions)
• LO2/LN2 and LiOH systems optimal for mass reduction
• Air purification system (3.3 kg, 51 W) based on readily obtainable products (25.4 x 25.4 x 38.4 cm) [7]
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Water System Requirements
• Nominal usage for each mission day (10 days) – 2 kg (2 L) drinking water / CM day
– 0.5 kg (0.5 L) hygiene water / CM day
• Minimal usage for each contingency day (3 days) – 2 kg (2 L) drinking water / CM day
– 0 kg (0 L) hygiene water / CM day
• Total 93 kg water required
Note: / CM day = per crew member per day
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Water Recycling Trades • 15 kg hygiene water reclaimable
– Hygiene water treatment technologies:
• 58 kg urine reclaimable (1.5 kg / CM day) – Urine treatment technologies:
• Mass of recycling systems exceeds amount reclaimable – No Water Recycling System will be used
Mass (kg) Volume (m3)
Reverse Osmosis / Ultrafiltration 214 0.35
MilliQ Absorption Bed 108 0.06
Mass (kg) Volume (m3)
Air Evaporation System 75 0.3
Vapor Compression Distillation 144 0.49
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Water System Specifics
• Water tank will be flexible bladder contained in non-pressurized section
• Water will be moved through a flexible tube using a small pump up to an accessible location
• No heating / cooling of water. Water will be ambient temperature
• Water tank will be filled before launch • NASA requirement: Water supply must be free of micro-
organisms – Water will be supplied with 12 mg iodine / liter of water – This will ensure minimum of 0.5 mg iodine / liter for duration of
mission
• Taste and odor of iodine in water could be negative factor • Total mass: 112 kg (assuming 20% of water mass for tank mass)
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Food System Requirements
• Nominal Activity Metabolic Load: – 11820 kJ / CM day
– Extra 2100 kJ / CM per EVA day
– Total: 486,000 kJ required
• 42 pre-packaged meals provided – 14 days of food / CM
– Total: 496,000 kJ (10,000 kJ more than required)
– Extra meals can be opened as needed for EVA days or for higher metabolic loads
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Food System Specifics
• All meals contained in a food locker – Dimensions: 0.5 m x 0.5 m x 0.8 m = 0.2 m3
– Full locker mass: 74 kg
– Empty locker mass: 6.4 kg
– Similar to food locker used on Space Shuttle
• Pre-packaged meals with individually sealed food items
• Food will contain 42% water (no rehydration required)
• Food will be consumed as-is – No rehydration system / oven / refrigeration / freezing
available
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Waste Management
• Derived from the Apollo missions
• Urine collection – Based on Urine Receptacle Assembly (URA)
– Further testing/development required for: • Consumables minimization/flow performance
• Improved hygiene standards
• Crew comfort
• Female astronaut compatibility
– Additional collection/transfer assembly worn under spacesuit for launches, EVA’s and emergencies
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Waste Management
• Fecal collection
– No positive means for removal of feces
– Adopted Apollo fecal collection assembly
• Fecal Bag with adhering flange
• Sanitary wipes
• Germicide pouch
– Fecal Containment System (FCS), an absorbent undergarment, will be worn under the spacesuit as a safeguard during launches, EVA’s and emergencies
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Waste Management
• Waste disposal
– Urine system contains a purge valve that allows the waste to be selectively released into the vacuum of space
– Feces will be stored
• Production rate : 1.00 x 10-3 m3 per person per day
• Required volume : 0.0975 m3 (Safety Factor = 2.5)
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Waste Management
Figure 1: URA Figure 2: Urine Transfer Assembly
Figure 3: Fecal Bag Assembly Figure 4: FCS
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Overall Design - Exterior
Front Rear
Windows (3x)
EVA Hatch
25°
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Overall Design - Interior
Parachute
Collapsible Seats (3x)
Pressurized Volume
Unpressurized Storage
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Overall Design – Interior (Collapsed Seats)
O2 Tank
N2 Tank
Air Filter / Dehumidifier
Water Storage
Food Storage
Landing Controls / Avionics
Waste Management
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Overall Design - Landing
Lunar Surface
Ingress / Egress
Sight Lines (3 windows evenly spaced around SC)
41.9°
Exterior Height: 3.98 m Interior Height: 2.37 m
Exterior Diameter: 3.57 m Interior Diameter: 3.13 m
Hatch Diameter: 1.0 m
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Launch and Landing
• Earth Launch and Landing
– All crew members will occupy seats in a horizontal position for greater G force tolerance
• Lunar Launch and Landing
– Seats are folded down to the deck
– Pilot will stand at center window / control panel
– Co-pilots will occupy side windows for greater overall visibility
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Lunar Surface Operations
• Seats will remain folded down for duration of lunar surface operations
• Crew members can stand up in middle section for donning / removing spacesuits
• During EVA: – All crew members don spacesuits – Entire cabin depressurized – Two crew members exit, one remains aboard – Exterior hatch remains open for duration of EVA – EVA concludes with enough time to repressurize cabin
• Crew members will eat, sleep, work on cabin floor • After final EVA, ladder and all consumable / disposable
items will be left on lunar surface
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Stowage and Placement
• Unpressurized bottom section – O2 and N2 tanks – Water tank – Air filter / dehumidifier
• Under legs of side seats – Food locker – Waste management system – Additional stowage
• Cabin sides – Spacesuits – Avionics
• Unpressurized top section – Parachute
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Mass Budget
Component Mass (kg)
O2, N2 tanks 226
CO2 , H2O removal canisters 80
Water tank / system 112
Food (full locker) 74
Waste system 25
3 x 95th percentile males 296
3 x Orlan spacesuits (MK model) 360
3 x Launch seats 150
Total 1323
• 177 kg available for extra storage / components • 12% mass margin
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Power Budget
Component Power (kW)
O2, H2 tanks .025
CO2 scrubber/Air Filtration .452
Water pump 0.02
Total 0.497
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
Mission Support Conclusions
• Crew System / Life Support achieves mission – 3 crew members to lunar surface for 4 days
– 4 EVAs in support of recurring human presence on the moon
• Design does not support crew comfort or convenience – 10 day mission is short enough in duration that crew
morale is not a factor
• If crew is stranded on lunar surface – Minimal contingency supplies
– Rescue mission must be launched immediately
– Additional supplies can be pre-staged on lunar surface during cargo mission
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
References • [1] “SpaceX DragonLab Datasheet” Available Online:
http://www.spacex.com/downloads/dragonlab-datasheet.pdf
• [2] J. James, Spacecraft Maximum Allowable Concentrations for Airborne Contaminants. JSC 20584: NASA Johnson Space Centre, Houston, TX, Feb. 1995
• [3]A. Hanford, Advanced Life Support Baseline Values and Assumptions Document
NASA/CR—2004–208941 : Lockheed Martin Space Operations, Houston, TX,
Aug. 2004
• [4]http://www.spaceaholic.com/apollo_artifacts.htm
• [5] “AGM Product Specifications Sheet” AGM Container Controls, Inc. Tucson, AZ. Available Online: http://www.agmcontainer.com/desiccantcity/pdfs/bulkDesSpecifications/920007Specs.pdf
• [6] “Soleus Air Product Review” Available Online: http://www.soleusaircentral.com/product/45-pint-dehumidifier-sg-deh-45-1
• [7]”Honeywell Central Product Review” Available Online: http://www.honeywellcentral.com/product/honeywell-enviracaire-true-hepa-air-purifier-n
Crew Systems Design Project ENAE 788D, Fall 2012
University of Maryland Block, Henninger, Rotunda
References • [9] International Space Station Flight Crew Integration Standard (NASA–
STD–3000/T) - SSP 50005, Rev. C - Space Station Program Office, NASA Johnson Space Center, December 15,1999.
• [10] R. Sauer , G. Jorgensen, “Waste Management System” in Biomedical Results of Apollo Washington, D.C.: NASA, 1974, Ch. 2, Sec. VI. Available Online: http://lsda.jsc.nasa.gov/books/apollo/s6ch2.htm
• [11] R. Sauer , D. Calley, “Potable Water Supply” in Biomedical Results of Apollo Washington, D.C.: NASA, 1974, Ch. 4, Sec. VI. Available Online: http://lsda.jsc.nasa.gov/books/apollo/s6ch4.htm
• [12] A. J. Hanford, “Advanced Life Support Baseline Values and Assumptions Document” NASA/CR—2004–208941, August 2004.
• [13] B. E. Duffield, “Advanced Life Support Requirements Document” JSC-38571C/CTSDADV-245C, February 2003.
• [14] Allen, C. S., et. al., “Guidelines and Capabilities for Designing Human Missions” NASA Exploration Team, Human Subsystems Working Group, March 2002.
• [15] ECLSS Subsystem. (2012). http://www.colorado.edu