Preliminary Design Review

Transcription

1 Crew Systems and Life Support Establishing a Recurring Human Presence on the Moon Preliminary Design Review

2 Overview Preliminary Design Review of Crew Systems / Life Support aboard low-cost lunar lander Atmosphere / O 2 Water Food Waste Management Human Factors and Habitability Seating Control Stations and Windows Stowage and Placement Ingress / Egress

3 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

4 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

5 Air System Assumptions Each EVA 5 hours, airlock remains open, all atmosphere lost each EVA CO 2 canisters are usable for both cabin and suits EMU suit volume is maximum (0.153 m 3 ) and has own dehumidification/heat exchange system EMU can be recharged with O 2 /N 2 upon return

6 Tank Mass (kg) Cabin Atmosphere Trade 400 Total Tank Mass at Select Spacecraft Volumes psi, Heavy Respiration 10 psi, Heavy Respiration 5psi, Light Respiration 10 psi, Light Respiration APOLLO CM APOLLO LM Interior Volume (m 3 ) SPACEX DRAGONLAB [1]

7 Pressure / O 2 content for Interior Cockpit Total Pressure Normoxic Partial Normoxic Concentrations (psia) Pressure (psia-o 2 ) (percentage of O 2 ) Table acquired from [3]

8 Final Tank Masses Atm. Resp Rate (5psi) (10 psi) O 2 mass for consumption, cabin and suit (kg) Tank and gas total (kg) Tank Volume (m 3 ) N 2 mass for consumption, cabin and suit (kg) Tank and gas total (kg) Tank Volume (m 3 ) Total mass of tanks (for cabin) (kg) Total Energy Req. (MJ)

9 Humidity Removal at Low Pressures Incredibly large systems required for humidity/distillation process reuse Dessicant Requires kg + 10% wt packaging [5], Unsuitable Dehumidification system suitable for small volume (6.7 m 3 ), 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

10 Liters Water Accumulated Water Accumulated in Module over Time Rates in L/hr, constant rate of water production at L/hr Mission Days Water Produced 0.28 Leftover.275 Leftover 0.25 Leftover 0.2 Leftover 0.1 Leftover

11 Apollo Environmental Control System Photos via [4]

12 CO 2 Level During Mission - Light Resp. Rate Carbon Dioxide Levels During Mission EVA Airlock Jettison Inclusion Grams Carbon Dioxide/ Cubed Meter Mission Days Elapsed SMAC limit [2] (23 g/m 3 )

13 CO2 Removal Comparisons Infeasible Mass (kg) CO 2 to remove KO 2 Used for CO 2 and O 2 Production in Combination with Liq O 2 KO Generates O Total Mass LiOH CO 2 Removal (ExtendAir LiOH Absorbent Curtains) LiOH (0.794 kg CO 2 / kg LiOH) Packaging (.7 kg/4.6 kg gross mass canister) 9.82 Total Mass KO 2 Used Only for O 2 Production (CO 2 Removed with Surplus) KO Generates O Total Mass Option Chosen

14 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) LO 2 /LN 2 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]

15 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

16 Water Recycling Trades 15 kg hygiene water reclaimable Hygiene water treatment technologies: Mass (kg) Volume (m 3 ) Reverse Osmosis / Ultrafiltration MilliQ Absorption Bed kg urine reclaimable (1.5 kg / CM day) Urine treatment technologies: Mass (kg) Volume (m 3 ) Air Evaporation System Vapor Compression Distillation Mass of recycling systems exceeds amount reclaimable No Water Recycling System will be used

17 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 microorganisms 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)

18 Food System Requirements Nominal Activity Metabolic Load: 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

19 Food System Specifics All meals contained in a food locker Dimensions: 0.5 m x 0.5 m x 0.8 m = 0.2 m 3 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

20 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

21 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

22 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 m 3 per person per day Required volume : m 3 (Safety Factor = 2.5)

23 Waste Management Figure 1: URA Figure 2: Urine Transfer Assembly Figure 3: Fecal Bag Assembly Figure 4: FCS

24 Overall Design - Exterior Front Rear Windows (3x) 25 EVA Hatch

25 Overall Design - Interior Parachute Pressurized Volume Collapsible Seats (3x) Unpressurized Storage

26 Overall Design Interior (Collapsed Seats) Landing Controls / Avionics Waste Management Food Storage Air Filter / Dehumidifier N 2 Tank O 2 Tank Water Storage

27 Overall Design - Landing Exterior Height: 3.98 m Interior Height: 2.37 m Sight Lines (3 windows evenly spaced around SC) Ingress / Egress Hatch Diameter: 1.0 m 41.9 Exterior Diameter: 3.57 m Interior Diameter: 3.13 m Lunar Surface

28 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

29 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

30 Stowage and Placement Unpressurized bottom section O 2 and N 2 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

31 Mass Budget Component O 2, N 2 tanks 226 CO 2, H 2 O removal canisters 80 Water tank / system 112 Food (full locker) 74 Waste system 25 3 x 95th percentile males x Orlan spacesuits (MK model) x Launch seats 150 Total 1323 Mass (kg) 177 kg available for extra storage / components 12% mass margin

32 Power Budget Component Power (kw) O 2, H 2 tanks.025 CO 2 scrubber/air Filtration.452 Water pump 0.02 Total 0.497

33 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

34 References [1] SpaceX DragonLab Datasheet Available Online: [2] J. James, Spacecraft Maximum Allowable Concentrations for Airborne Contaminants. JSC 20584: NASA Johnson Space Centre, Houston, TX, Feb [3]A. Hanford, Advanced Life Support Baseline Values and Assumptions Document NASA/CR : Lockheed Martin Space Operations, Houston, TX, Aug [4] [5] AGM Product Specifications Sheet AGM Container Controls, Inc. Tucson, AZ. Available Online: pecs.pdf [6] Soleus Air Product Review Available Online: [7] Honeywell Central Product Review Available Online:

35 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: [11] R. Sauer, D. Calley, Potable Water Supply in Biomedical Results of Apollo Washington, D.C.: NASA, 1974, Ch. 4, Sec. VI. Available Online: [12] A. J. Hanford, Advanced Life Support Baseline Values and Assumptions Document NASA/CR , August [13] B. E. Duffield, Advanced Life Support Requirements Document JSC C/CTSDADV-245C, February [14] Allen, C. S., et. al., Guidelines and Capabilities for Designing Human Missions NASA Exploration Team, Human Subsystems Working Group, March [15] ECLSS Subsystem. (2012).