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The design of a vacuum-swing adsorption process to remove metabolic water, metabolic carbon dioxide, and metabolic and equipment generated trace contaminant gases from the Orion Crew Exploration Vehicle (CEV) atmosphere is presented. For Orion, the approach is taken that all metabolic water must be removed by the Sorbent-Based Atmosphere Revitalization System (SBAR), a technology approach that has not been used in previous spacecraft life support systems. Design and development of a prototype SBAR, a facility test stand, and subsequent testing of the SBAR in late 2006 and early 2007 is discussed.

The design of a Vacuum-Swing Adsorption (VSA) system to remove metabolic water and metabolic carbon dioxide from the Orion Crew Exploration Vehicle (CEV) atmosphere is presented. The approach for Orion is a VSA system that removes not only 100 percent of the metabolic CO2 from the atmosphere, but also 100% of the metabolic water as well, a technology approach that has not been used in previous spacecraft life support systems. The design and development of the Sorbent Based Atmosphere Regeneration (SBAR) system, including test articles, a facility test stand, and full-scale testing in late 2007 and early 2008 is discussed.

As part of the Sustaining Engineering program for the International Space Station (ISS), a ground simulator of the Internal Thermal Control System (ITCS) in the Lab Module was designed and built at the Marshall Space Flight Center (MSFC). To predict ITCS performance and address flight issues, this facility is operationally and functionally similar to the flight system and flight-like components were used when available. Flight software algorithms, implemented using the LabVIEW® programming language, were used for monitoring performance and controlling operation. Validation testing of the low temperature loop was completed prior to activation of the Lab module in 2001. Assembly of the moderate temperature loop was completed in 2002 and it was validated in 2003. Even before complete validation the facility was used to address flight issues, successfully demonstrating the ability to add silver biocide and to adjust the pH of the coolant.

Since 1984 Eagle-Picher Ind., Inc. has provided hardware and technical support to the budding solar vehicle industry. The batteries are used in the solar vehicles to provide storage of the electrical energy from the solar cells for use during brief periods when the power requirements exceed the capability of the solar cells, such as hill climbing, passing, or low sun conditions. Though the early development of these vehicles has focused on races which place emphasis on both speed and endurance, the ultimate goal is a commercial vehicle which will reduce the consumption of fossil fuels for transportation. Eagle-Picher Industries silver-oxide zinc system has proven ideal for use in this development phase because of their high energy density and reliability.

Nickel and silver-metal hydride batteries are being developed for aerospace applications by Eagle-Picher. Metal hydride batteries offer a number of advantages over other aerospace battery systems. Nickel-metal hydride batteries have twice the gravimetric energy density of nickel-cadmium and twice the volumetric energy density of nickel-hydrogen. Silver-metal hydride batteries have the potential of three times the energy density of nickel-metal hydride and exhibit superior charge retention characteristics. Aerospace metal hydride batteries are hermetically sealed, operate at low pressure and are prismatic in geometry. They exhibit excellent overcharge and overdischarge capability. Preliminary calorimetry data indicates superior thermal performance as compared to nickel-cadmium and nickel-hydrogen batteries. Some initial AC impedance spectroscopy work has been completed on both metal-hydrogen and metal-hydride battery systems.