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Hamilton Standard Space Systems International, Inc. is currently under contract to NASA for the development and certification of an advanced technology regenerable carbon dioxide removal system for the International Space Station Extravehicular Mobility Unit (EMU), or “space suit.” This new metal-oxide-based system (“Metox”) will replace the existing non-regenerable lithium hydroxide (LiOH) carbon dioxide (CO2) removal system located in the EMU's Primary Life Support System (PLSS). The Metox canister is designed to replace the current LiOH Contamination Control Canister (CCC) with no modification to existing EMU interfaces. The metal oxide sorbent is “regenerable” and can be restored to its original condition permitting the Metox canisters to be used over and over again on-orbit. Once a Metox canister becomes “loaded” with CO2, it will be placed in the “Regenerator,” where the system will circulate hot air through the canister to drive off, or desorb, the CO2.

Membrane technology for all types of separation processes is developing rapidly. Application of this technology in zero-gravity life support areas such as air revitalization and water reclamation presents special challenges not present in other systems. Design of life support systems for applications such as long duration space missions requires minimization of membrane surface areas as well as system weight and volume. In addition, high membrane selectivity in separating very similar components is required in both gas and water systems. This means that membrane materials for most space life support applications must have both extremely high flux rates and extremely selective permeability characteristics. Programs directed toward developing new materials specifically for space life support systems will be discussed. Specific applications for these new membranes including use of volatile rejection membranes(VRMs) for water reclamation will be given.

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.