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A regenerable carbon dioxide (CO2) removal system has been certified for use with the Extravehicular Mobility Unit (EMU), or space suit. The new system, nicknamed “Metox” to reflect its use of metal-oxide as the CO2 sor-bent material, was designed and developed by Hamilton Standard Space Systems International (HSSSI), Inc., under contract1 to the National Aeronautics and Space Administration (NASA) Johnson Space Center (JSC). As a part of the certification process, one hundred (100) operating cycles were accumulated on the certification canister and sixteen (16) regeneration cycles on the certification regenerator. This paper presents a summary of those tests. The results characterize canister performance for a wide range of temperatures, pressures and metabolic rates. It also presents regenerator performance under nominal and worst case operating conditions.

Hamilton Standard has developed a non-venting Metal Oxide Regenerable EMU CO2 Removal Subsystem (MORES) for the NASA Johnson Space Center. This system has the potential for application to an Advanced EMU or retrofit to the existing Shuttle EMU. The MORES system uses a catalyzed, silver based metal oxide to achieve the CO2 removal during Extravehicular Activity (EVA) and uses no supplemental cooling. Regeneration is easily accomplished using cabin air in a simple hot air regeneration process. The MORES technology has been demonstrated in a full size EMU Contaminant Control Cartridge (CCC) using a conventional packed bed and also an improved sheet matrix configuration. The packed bed MORES used pellets encased in a porous shell to meet the design performance goal of 3.5 - 5 hours per simulated EVA for more than 50 cycles. The sheet matrix configuration has demonstrated performance of 6 - 8 hours for greater than 50 cycles.

A design of a self-contained Smoke and Contaminant Removal System (SCRS) and its capabilities in removing airborne particulates and toxic gases generated from a Space Station fire are presented. Based on potential fire scenarios, an SCRS has been sized to weigh 52 lb, consume 50 watts and occupy less than 3 ft3. The replaceable filter/sorbent beds provide the SCRS with the capability of handling multiple contaminant challenges. The SCRS will reduce the necessity to compromise mission objectives by changing out Space Station air. The SCRS option provides the crew with the added flexibility of restoring and maintaining the quality of the habitable environment.

The Extravehicular Activity (EVA) operations for Space Station (SS) require that a regenerable carbon dioxide (CO2) absorber be developed for the manned Extravehicular Mobility Unit (EMU). A concept which employs a solid amine resin to remove metabolic CCL and water vapor from the breathing air within the space suit is being developed by the Hamilton Standard Division of United Technologies Corporation under Contract NAS 9-17480 with the National Aeronautics and Space Administration (NASA) Johnson Space Center (JSC). The solid amine is packed within a water cooled metal foam matrix heat exchanger to remove the exothermic heat of chemical reaction. After completion of the EVA mission, the amine is regenerated on board the Space Station within the heat exchanger using a combination of heat and vacuum. This paper describes the concept design features, operational considerations and test results during simulated laboratory conditions.

A five hour regenerate, nonventing Humidity and CO2 Control Subsystem (HCCS) technology demonstration unit is being developed for potential use in an Advanced Extravehicular Mobility Unit (AEMU) for Space Station application. The HCCS incorporates a weak base anion exchange resin packed in a metal foam matrix heat exchanger. This system simultaneously removes CO2 and water vapor with the resulting exothermic heat of reaction rejected to the heat exchanger. The system has no moving parts resulting in a highly reliable, simple configuration. Regeneration may be accomplished via internal heating and vacuum.

Recent development of the solid amine/water desorbed (SAWD) CO2 control system technology has resulted in two preprototype systems. The SAWD I system was developed under NASA Contract NAS9-13624 and is currently under test in the NASA Johnson Space Center, Crew Systems Division Advanced Environmental Control Systems (ECS) Laboratory. The SAWD II system is being developed at Hamilton Standard Division of United Technologies (HSD) under NASA Contract NAS9-16978. This paper reviews the development history of solid amine CO2 control systems and describes the SAWD I and SAWD II systems. In the development of the SAWD II system, special attention was given to reducing its power requirements and to designing the system to be compatible with zero-gravity operation. Energy saving features are discussed, and the zero-gravity solid amine canister test program and selected design are described.