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The ability to remove semi-volatile organic compounds such as alcohol from waste water streams has challenged the design of the International Space Station (ISS) water processor. The current ISS water processor utilizes an aqueous phase catalytic oxidation system to convert these organic compounds to their corresponding organic acids, and to some extent carbon dioxide, which are then easily removed via ion exchange resin. This oxidation system also provides a microbiological control function within the water processor. This paper summarizes testing conducted utilizing both simulated and real waste water on a development catalytic oxidizer. In addition, information is presented on the system schematic and reactor configuration planned for the upcoming Volatile Removal Apparatus flight experiment scheduled for STS 84 to be flown in May 1997.

The Space Station Temperature and Humidity Control Condensing Heat Exchangers will be utilized to collect and remove atmospheric water vapor generated by the metabolic and hygienic activity of crew members. The porous hydrophilic coating within the heat exchangers will always be wet. Cabin air will continuously flow through the heat exchangers during system operation which makes them a potential site for microbial colonization. This paper summarizes the findings from an ongoing study which evaluates biofilm formation on wet hydrophilic coated panels compared to panels to which microbial control measures have been applied. The control measures evaluated are an antimicrobial agent within the coating and periodic drying.

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.

The Shuttle Extravehicular Mobility Unit (EMU) is an integral component in successful satellite salvaging operations. FMU evolution to its current operational status has occurred through implementation of carefully analyzed and thoroughly tested changes. The net result of these changes is known as the Block II FMU. This paper discusses the basic FMU system requirements, the philosophy used in the design of the Block I EMU, and the operation of the Life Support System (LSS); outlines the evolution of the Block II configuration; and briefly discusses future progression of the LSS. The Block II LSS configuration has improved serviceability between flights, simplified user operation, improved performance, decreased maintenance (by extending component life), and, most importantly, improved mean time between failures by a factor of fourteen.

The Shuttle Orbiter Design Test Objective (DTO) test effort of the Extended Duration Orbiter (EDO) Urinal Subassembly and the EDO Waste Collector Subsystem (WCS) has been conducted on STS–52 and STS–54 flights respectively. The objective of these DTO test flights was to prove out the new waste collection concepts and hardware including convenient and safe in–flight servicing, human factor enhancements, natural biodegradation, and hardware configuration. Actual DTO testing included real time zero gravity collection of liquid and solid human waste as well as special on–board set–ups for performance evaluation of the commode. The results of the hardware operation on these Orbiter flights along with post flight test evaluation are contained and discussed in this report. Any improvements resulting from this evaluation can be considered for use on the similar Space Station Waste Management Design.

The benefits and penalties associated with the generation of high pressure gases using the SPE® water electrolysis subsystem are presented. The Space Station has a number of requirements for oxygen and hydrogen generation at very high pressures (between 1000 and 6000 psia) including emergency pressurization and repressurization of habitability and laboratory modules, recharge of the Extravehicular Mobility Unit (EMU) oxygen tanks, and propulsion capability for Station reboost and attitude control. The traditional trade study parameters of weight, volume, power, and heat rejection are considered. The ramifications of the use of a high pressure, solid polymer electrolyte-based system are discussed with respect to Space Station safety and maintenance.

With the advent of manned spacecraft opportunities requiring routine and complex extravehicular activities (EVA), a new concept for heat rejection is mandatory in order to realize maximum mission productivity. An optimum extravehicular mobility unit (EMU) thermal control subsystem must be capable of successful operation without requiring expendables or introducing contaminants into the environment, conform to reasonable size limitations, and be readily regenerable. This paper describes the development of two thermal control subsystems, one capable of being integrated with the existing Shuttle Orbiter EMU to provide a three hour non-venting heat rejection capacity within the EMU mission profile, and a second capable of providing the entire heat rejection capacity required for a potential eight hour Space Station EVA.

Recent advances in SPE® electrochemical systems have addressed risk areas identified early in the space station program and now support applications that can provide significant potential benefit to ISS in the areas of life support, propulsion and energy storage. Advanced high-pressure systems now under development for navy and aircraft applications can generate oxygen at pressures up to 2000 psi (13.8 MPa) with no moving parts on the oxygen side of the generating system. Zero gravity static phase separators have been developed and are being tested in component and system tests. Cyclic operation of complete systems has been demonstrated.

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 Space Station Temperature and Humidity Control Condensing Heat Exchangers will be utilized to remove and collect atmospheric water vapor generated by the metabolic and hygienic activity of crew members. The porous hydrophilic coating within the heat exchangers will be continually moist and in contact with a steady flow of cabin air which makes them susceptible to microbial growth. This paper summarizes the findings from an ongoing study to evaluate biofilm formation characteristics and microbial control techniques for the Space Station Condensing Heat Exchangers (CHX). This ongoing study examines whether the CHX's are susceptible to performance degrading microbial colonization with microbial challenge testing under simulated system environmental conditions. Furthermore, the three candidate microbial control approaches of periodic heating, periodic drying and incorporation of an antimicrobial agent, into the hydrophilic coating are evaluated.