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The carbon dioxide removal assembly (CDRA) is part of the International Space Station (ISS) Air Revitalization (AR) system. As such, this system selectively removes carbon dioxide generated by the crew members, and discharges it overboard to space vacuum. During initial operation sequences aboard the ISS, CDRA adsorbent particulates were not properly contained, resulting in operational failures. To resolve these adsorbent particulate containment problems, the desiccant/adsorbent bed (DAB), a key component of the CDRA, was redesigned and modified. In addition, a set of in-line filters that were added to the CDRA as a short-term on-orbit solution, were retained in the design. The incorporation of these modified DAB's and the in-line filters changed the CDRA configuration from a “-1-1” to a “-1-7”. Following this conversion of the CDRA, performance verification testing was performed. The data from these tests was compared to that previously acquired from the CDRA “-1-1” configuration.

The Carbon Dioxide Removal Assembly (CDRA) is a part of the International Space Station (ISS) Environmental Control and Life Support (ECLS) system. The CDRA provides carbon dioxide (CO2) removal from the ISS on-orbit modules. Currently, the CDRA is the secondary removal system on the ISS, with the primary system being the Russian Vozdukh. Within the CDRA are two Desiccant/Adsorbent Beds (DAB), which perform the carbon dioxide removal function. The DAB adsorbent containment approach required improvements with respect to adsorbent containment. These improvements were implemented through a redesign program and have been implemented on units on the ground and returning from orbit. This paper presents a DAB design modification implementation description, a hardware performance comparison between the unmodified and modified DAB configurations, and a description of the modified DAB hardware implementation into the on-orbit CDRA.

An important aspect of air revitalization for life support in spacecraft is the removal of carbon dioxide from cabin air. Several types of carbon dioxide removal systems are in use or have been proposed for use in spacecraft life support systems. These systems rely on various removal techniques that employ different architectures and media for scrubbing CO2, such as permeable membranes, liquid amine, adsorbents, and absorbents. Sorbent systems have been used since the first manned missions. The current state of key technology is the existing International Space Station (ISS) Carbon Dioxide Removal Assembly (CDRA), a system that selectively removes carbon dioxide from the cabin atmosphere. The CDRA system was launched aboard UF-2 in February 2001 and resides in the U.S. Destiny Laboratory module. During the past four years, the CDRA system has experienced operational limitations.

An important aspect of air revitalization for life support in spacecraft is the removal of carbon dioxide from cabin air. Several types of carbon dioxide removal systems are in use in spacecraft life support. These systems rely on various removal techniques that employ different architectures and media for scrubbing CO2, such as permeable membranes, liquid amine, adsorbents, and absorbents. Sorbent systems have been used since the first manned missions. The current state of key technology is the existing International Space Station (ISS) Carbon Dioxide Removal Assembly (CDRA), a system that selectively removes carbon dioxide from the cabin atmosphere. The CDRA system was launched aboard UF-2 in February 2001 and resides in the U.S. Destiny Laboratory module. During the past three years, the CDRA system has operated with varying degrees of success.

The Carbon Dioxide Removal Assembly (CDRA) is an essential part of the International Space Station (ISS) Environmental Control and Life Support (ECLS) system. The CDRA provides carbon dioxide (CO2) removal from the ISS on-orbit modules. Currently, the CDRA is the secondary removal system on the ISS, with the primary system being the Russian Vozdukh. The CDRA encountered some operational problems since being launched to orbit on Flight 5A in February 2001. While on-orbit, several hardware modifications and maintenance activities have been necessary to restore the CDRA to nominal capability. This paper describes the troubleshooting activities and briefly explains the failures, the operational workarounds, and the on-orbit hardware repairs performed to return the CDRA to operational status.

Carbon dioxide removal is an essential part of any environmental control and life support system of an enclosed atmosphere. The current state of key technology is the existing International Space Station (ISS) Carbon Dioxide Removal Assembly (CDRA) used to selectively remove carbon dioxide from the cabin atmosphere. The CDRA is part of the ISS air revitalization system. This paper will present approaches to recover the carbon dioxide for down stream processing. A discussion of a closed-loop CDRA system that will selectively remove carbon dioxide from the cabin air supply and this product will be routed to a carbon dioxide reduction system, where the oxygen will be recovered. Using a CDRA system modified for closed loop operation, a case by case illustration of the sequential operation will be presented.

Advances in carbon dioxide removal technology for spacecraft air revitalization promise to reduce the size and power consumption of carbon dioxide removal systems on future space missions. AlliedSignal has developed a Functionalized Carbon Molecular Sieve (FCMS) that can simultaneously remove carbon dioxide and water vapor. A thermally-coupled pressure-swing adsorption system has been designed using FCMS as the sorbent to provide regenerative carbon dioxide removal. The low regeneration temperature of FCMS results in lower power consumption than is required for conventional adsorbents, which typically desorb carbon dioxide at higher temperatures. The thermally-coupled pressure-swing system was tested, and results were compared to the Space Station Carbon Dioxide Removal Assembly (CDRA) as a reference design. The comparison indicated that a thermally-coupled pressure-swing system with FCMS offers significant savings in mass, volume and power consumption.

In the closed environment of an inhabited spacecraft, a critical aspect of the air revitalization system is the removal of the carbon dioxide (CO2) and water vapor produced by the crew. A number of different techniques can be used for CO2 removal, but current methods are either non-regenerative or require a relatively high power input for thermal regeneration. Two-bed CO2 adsorption systems that can remove CO2 from humid air and be regenerated using pressure-swing desorption offer mass, volume, and power advantages when compared with the other methods. Two classes of sorbent materials show particular promise for this application: Zeolite sorbents, similar to those in the International Space Station (ISS) CO2 removal assembly Functionalized carbon molecular sieves (FCMS), which adsorb CO2 independent of the humidity in the airstream Pressure-swing testing of these two different sorbents under both space station and space suit conditions are currently underway.

The Lunar-Mars Life Support Test Project (LMLSTP), formerly known as the Early Human Testing Initiative (EHTI), was established to perform the necessary research, technology development, integration, and verification of regenerative life support systems to provide safe, reliable, and self-sufficient human life support systems. Four advanced life support system test phases make up LMLSTP. Phase I of the test program demonstrated the use of plants to provide the atmosphere revitalization requirements of a single test subject for 15 days. The primary objective of the Phase II test was to demonstrate an integrated regenerative life support system capable of sustaining a human crew of four for 30 days in a closed chamber. The third test phase, known as Phase IIA, served as a demonstration of International Space Station (ISS) representative life support technology, supporting a human crew of four for 60 days.