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A porous plate sublimator (an existing Lunar Module design) is being evaluated as the heat sink for the X-38 vehicle due to its simplicity, reliability, and flight readiness. It is ideally suited for the X-38/CRV as it requires no active control, has no moving parts, has 100 % water usage efficiency, and is a well-proven technology. This paper presents sublimator performance, including ground test data at CRV conditions, at both a component and system level. Potential sublimator modifications which could allow significant CRV ECLSS system simplification, reliability enhancement, and cost reduction are also discussed.

A porous plate sublimator (based on an existing Lunar Module LM-209 design) is baselined as a heat rejection device for the X-38 vehicle due to its simplicity, reliability, and flight readiness. The sublimator is a passive device used for rejecting heat to the vacuum of space by sublimating water to obtain efficient heat rejection in excess of 1,000 Btu/lb of water. It is ideally suited for the X-38/CRV mission as it requires no active control, has no moving parts, has 100% water usage efficiency, and is a well-proven technology. Two sublimators have been built and tested for the X-38 program, one of which will fly on the NASA V-201 space flight demonstrator vehicle in 2001. The units satisfied all X-38 requirements with margin and have demonstrated excellent performance. Minor design changes were made to the LM-209 design for improved manufacturability and parts obsolescence.

Hamilton Standard Space Systems International, Inc. (HSSSI) has obtained and is currently testing a variety of Russian life support hardware. These units have been or are contemplated for use on Mir I and II space stations. This paper presents the current status of performance testing of a Sabatier Carbon Dioxide Processing Unit (CDPU) and components of a Potable Water Processing System (PWP). These systems were fabricated by NIICHIMMASH, the supplier of these units to the Russian space program. It is the intent of this testing program to obtain a data base for technology comparisons to support planned and future international missions. For the CDPU, reactant conversion efficiencies in excess of 99 percent have been noted for the variation in test conditions with 2 to 6 man processing (flows) tested. The CDPU's effluent water has been produced at anticipated rates and is relatively contaminant free.

A distributed avionics air architecture provides air cooling and air circulation in non-habitable Space Station zones utilizing dedicated hardware to support the zone-specific needs. That dedicated hardware, the Avionics Air Assembly (AAA), includes a selectable speed fan and heat exchanger used in racks for active avionics air cooling to reject the airborne heat load directly to the moderate temperature Internal Thermal Control System (ITCS). This paper addresses the design impacts resulting from the International Space Station Alpha (ISSA) restructure effort. It defines the service provided by the avionics air assembly, the design requirements and the integrated system performance. Detailed package configuration and interfaces, hardware design and off-design performance are included to define the full range of operating capability.

Based on the high volume of Extravehicular Activity (EVA) needed for assembly and operation of the International Space Station (1792 hrs through GFY2005), a large number of new crewmembers will be trained in the use of the Extravehicular Mobility Unit (EMU). In addition, the crewmembers will require on-orbit refresher training in the use of an EMU given their extended duration on-orbit of 90-180 days. Currently, there is a single hardware based training unit at Johnson Spaceflight Center (JSC) (the MALF II Simulator). This paper reports on the development of a software based training simulator (EMU Malfunction Training Simulator [EMTS]) which will run on any PC under Microsoft Windows and will be used to supplement MALF II.

Hamilton Standard’s subsidiaries, Microtecnica/Italy and Hamilton Standard Space Systems International/USA, have collaborated to design and fabricate a Water Pump Package (WPP) for the International Space Station (ISS) Multi-Purpose Logistics Module (MPLM). MPLM active payloads (Refrigerator/Freezer Racks (R/FR)) supply cold volume for food and scientific sample storage. The MPLM Active Thermal Control Subsystem (ATCS) maintains specific structural and equipment temperatures for the active payloads. The active thermal control is provided via a low temperature water loop whose flow rate is created by the WPP during MPLM pre-launch and MPLM pre-ISS attach and post-ISS detach mission phases. The WPP also provides compensation for water loop volume variations. This paper will provide a detailed overview of the MPLM Water Pump Package design, as well as providing system performance data.

The International Space Station Alpha Electrical Power System has a thermal control system to remove heat from the batteries and power distribution electronics. A major subsystem of this thermal loop is the Pump and Flow Control Subassembly (PFCS) which functions as an ammonia fluid distribution and control subsystem. This paper will detail the development, construction and operational performances of the PFCS hydraulic elements operating with an ammonia fluid. These elements include flow meter, accumulator, flow control valve, and pumps. The electronics which are utilized to operate these hydraulic elements will also be described. The combination of these hydraulic and electronic elements form a subassembly to safely control a hazardous, low viscosity fluid.