Spacecraft Carbon Dioxide
Removal Technology
Allen MacKnight
A History of CO2 Removal Technology
Development for NASA
Mercury
Apollo Application
Skylab
Absorbent
LiOH
Molecular
Sieves
Regenerable
Absorbent
Gemini
Apollo
ISS CDRA
Shuttle
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ECLSS System
Design
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Regenerable
Absorbent
• Outstanding Record for
Reliability and Safety
• Progression Toward
Regenerable Technologies
Absorbent
LiOH
2
Absorbent
LiOH
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Lithium Hydroxide Canisters
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Astronauts Access LiOH Canisters
on Shuttle Mid Deck floor
Changing a Shuttle LiOH Canister
• The mainstay of manned
space flight life support has
been Lithium Hydroxide
canisters
• Simple, light weight, reliable
and effective they have an
excellent history for life
support
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Apollo Command Module LiOH
Canister
3
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Apollo Applications Regenerable Carbon
Dioxide Removal
• System description
- Pressure swing dual composite
-
bed silica and molecular sieve
Indirect thermal contact via cabin temperature
control fluid
126 lb
3.1 ft3
CO2 load 0.27 lb/hr (0.27 lb/hr removal)
H2O load 0.50 lb/hr (0.21 lb/hr removal)
• Advantages
-
Lowest fixed weight
Lowest expendables
High technology level
Best for longer duration missions > 10 days
• Disadvantages
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Apollo Applications CO2
Removal System
- Requires cooling and heating thermal energy
- Thermal integration required
4
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Skylab Background
Missions
Duration
Crew
Date
1
2
3
28 days 49 minutes
59 days 11 hours
84 days 1 hour
3
3
3
5/25/73
7/28/73
11/16/73
• First American Space Station
• Reused Some Apollo Flight Qualified Hardware
• First Use of Regenerable Air Revitalization System
• Environmental Control Systems Installed in Airlock Module
• Operated for Complete Mission Without Flight Incident
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Crew Entering Workshop Module
Note: ECS Ducting
5
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View of Crew Inside
Workshop Module
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Skylab Carbon Dioxide Removal System
• System Description
- Pressure Swing
Molecular Sieve (Zeolite)
- 199 Lb
- 0.281 Lb/hr CO2 Removal
(3 Person)
- 0.223 Lb/hr H2O Removal
- 84 Day Mission
• Advantages
- Simple System
- High Technology Readiness (9)
- Low Equivalent Weight
- Trades Well for Short Missions
6
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International Space Station Carbon Dioxide
Removal System (CDRA)
• Features 4 Bed Molecular Sieve
System for Long Duration Missions
• Currently Operational in Space
• Most Advanced ARS Flown
• Technology Evolved From Skylab
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1997-1998
ISS
CDRA Built and Acceptance
Tested at Honeywell, Torrance
12/2000
Completed All ISS Lab Testing
December 2000
2/7/2001
Launched Aboard ISS Assembly
Flight 5A (STS-98)
2/2/2001
Initial On-orbit Start up
8/20/2002
Full Functional Check Out and
Operation
10/15/2002
Mini Endurance Test (Operates 33 Hr
At a Load of 9 Crew Members)
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CDRA
7
7/1/2004
Desiccant/Adsorbent Bed
Modification Project Start
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Carbon Dioxide Removal Technology
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102025-1
Blower
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Desiccant/Adsorbent
Bed
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Selector Valve
International Space Station CDRA
8
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