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This paper presents the results of a program to develop the next generation Vapor Phase Catalytic Ammonia Removal (VPCAR) system. VPCAR is a spacecraft water recycling system designed by NASA and constructed by Water Reuse Technology Inc. The technology has been identified by NASA to be the next generation water recycling system [1]. It is designed specifically for a Mars transit vehicle mission. This paper provides a description of the process and an evaluation of the performance of the new system. The equivalent system mass (ESM) is calculated and compared to the existing state-of-the art. A description of the contracting mechanism used to construct the new system is also provided.

The design of advanced closed-loop life support systems requires that the CO2 removed from the cabin atmosphere be reduced to recover its oxygen content. An optimum physical/chemical technology choice for reduction will balance reaction products with the demands and products of the human metabolic process. Although water electrolysis is the technology of choice for oxygen generation, many different processing strategies for CO2 reduction have been proposed. The Sabatier and the Bosch carbon formation reactions and Solid Oxide electrochemical reduction along with Steam Reforming and Fischer-Tropsch synthesis, are among the candidates. Each strategy provides a different level of oxygen recovery. The consequence of each choice directly impacts the water required for electrochemical oxygen generation. This paper reports on a theoretical study of CO2 processing options, both individually and in combinations that result in improved loop closure.

The NASA Shuttle Extravehicular Mobility Unit (EMU) uses a non-regenerable absorbent to remove CO2 from an astronaut's breathing loop. A savings in launch weight, storage volume and life cycle cost may be achieved by incorporating a regenerable CO2 removal system into the EMU. This paper will discuss regenerable CO2 sorbents and their impact on the life support system of an EMU. The systems evaluated will be judged on their technical maturity, impact to the EMU, and impacts to space station and shuttle operation

In 1991, Hamilton Standard initiated an Independent Research and Development program to enhance the performance characteristics of solid amine based regenerative CO2 removal systems. A solid amine based system had been selected by NASA/JSC for Extended Duration Orbiter missions. As a result of this research effort, two promising new solid amine candidates, designated HSC+ and HSG, were identified. Bench scale testing indicated that these formulations provided 25% to 33% greater initial cyclic capacity when compared to the baseline HSC solid amine sorbent. This paper reports on comparative life testing of HSC, HSC+ and HSG. The solid amine sorbents were exposed to accelerated life testing with laboratory air under controlled temperature and flow conditions.