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This project is a Phase III SBIR contract between NASA and Water Reuse Technology (WRT). It covers the redesign, modification, and construction of the Wiped-Film Rotating-Disk (WFRD) evaporator for use in microgravity and its integration into a Vapor Phase Catalytic Ammonia Removal (VPCAR) system. VPCAR is a water processor technology for long duration space exploration applications. The system is designed as an engineering development unit specifically aimed at being integrated into NASA Johnson Space Center's Bioregenerative Planetary Life Support Test Complex (BIO-Plex). The WFRD evaporator and the compressor are being designed and built by WRT. The balance of the VPCAR system and the integrated package are being designed and built by Hamilton Sundstrand Space Systems International, Inc. (HSSSI) under a subcontract with WRT. This paper provides a description of the VPCAR technology and the advances that are being incorporated into the unit.

The TIMES system was evaluated to determine its ability to process reverse osmosis (RO) brine as one of the Advanced Water Processor steps. Since preliminary testing performed in 1998 showed that the membrane typically used in the process (Nafion 117) offered a very poor ammonia rejection, a search for an alternate membrane exhibiting high ammonia rejection capability was initiated under NASA-JSC funding. This investigation has resulted in the selection of a PolyVinylAlcohol (PVA) composite membrane as a replacement. When processing RO brine and untreated human urine as feeds, the Pervap 2201 membrane showed a 96% ammonia rejection over a large range of ammonia concentration. The water permeation rates in both laboratory-scale and pilot scale testings were also similar to the Nafion. The water permeance of the Pervap 2201 was approximately 7.5 kg/h/m2/atm (1.1 lb/h/m2/psi).

The International Space Station Waste Collector Subsystem Risk Mitigation Experiment (ISS WCS RME) was flown as the primary (Shuttle) WCS on Space Shuttle flight STS-104 (ISS-7A) in July 2001, to validate new design enhancements. In general, the WCS is utilized for collecting, storing, and compacting fecal & associated personal hygiene waste, in a zero gravity environment. In addition, the WCS collects and transfers urine to the Shuttle waste storage tank. All functions are executed while controlling odors and providing crew comfort. The ISS WCS previously flew on three Shuttle flights as the Extended Duration Orbiter (EDO) WCS, as it was originally designed to support extended duration Space Shuttle flights up to 30 days in length. Soon after its third flight, the Space Shuttle Program decided to no longer require 30 day extended mission duration capability and provided the EDO WCS to the ISS Program.

Previous studies have shown that a multi-axis ankle joint accommodating abduction and adduction as well as ankle flexion/extension and rotation could be practically incorporated into a pressure suit. Several candidate configurations were manufactured and the performance of the enhanced ankle joints evaluated. Experience has suggested that these enhancements could be of significant benefit for planetary exploration missions requiring extensive walking over uneven terrain. During 1999, prototype pressure suit boots incorporating a multi-axis ankle joint configuration were manufactured. Their effect on balance stability and locomotion capabilities across slopes and over uneven surfaces in a pressurized spacesuit were evaluated in a series of 1-g experiments. This paper describes the enhanced test boots, the test procedure, and the results. Design refinements and further testing are recommended.

Enhancements to the Regenerable Carbon Dioxide Removal System (RCRS) have undergone full-scale, pre-prototype development and testing to demonstrate a redundant system within the volume allotted for the RCRS on the Space Shuttle Orbiter. The concept for a Redundant Regenerable Carbon Dioxide Removal System (RRCRS) utilizes the existing canister of the RCRS, but partitions it into two, independent, two-bed systems. This partitioning allows for two, fully capable RCRS units to be packaged within the original volume, thus reducing stowage volume and launch weight when compared to the flight RCRS plus the backup LiOH system. This paper presents the results of development and testing of a full-scale, pre-prototype RRCRS and includes an overview of the design concept for a redundant system that can be packaged within the existing envelope.