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Future space exploration missions will require a lightweight spacesuit that expends no consumables. This paper describes the design and performance of a prototype heat rejection system that weighs less than current systems and vents zero water. The system uses regenerable LiCl/water absorption cooling. Absorption cooling boosts the heat absorbed from the crew member to a high temperature for rejection to space from a compact, non-venting radiator. The system is regenerated by heating to 100°C for two hours. The system provides refrigeration at 17°C and rejects heat at temperatures greater than 50°C. The overall cooling capacity is over 100 W-hr/kg.

In order to provide effective cooling for astronauts during extravehicular activities (EVAs), a liquid cooling and ventilation garment (LCVG) is used to remove heat by a series of tubes through which cooling water is circulated. To better predict the effectiveness of the LCVG and determine possible modifications to improve performance, computer simulations dealing with the interaction of the cooling garment with the human body have been run using the Wissler Human Thermal Model. Simulations have been conducted to predict the heat removal rate for various liquid cooled garment configurations. The current LCVG uses 48 cooling tubes woven into a fabric with cooling water flowing through the tubes. The purpose of the current project is to decrease the overall weight of the LCVG system. In order to achieve this weight reduction, advances in the garment heat removal rates need to be obtained.

Lunar and martian materials can be processed and used at planetary outposts to reduce the need (and thus the cost) of transporting supplies from Earth. A variety of uses for indigenous, on-site materials have been suggested, including uses as rocket propellants, construction materials, and life support materials. Utilization of on-site resources will supplement Regenerative Life Support Systems (RLSS) that will be needed to regenerate air, water, and wastes, and to produce food (e.g., plants) for human consumption during long-duration space missions.

The thermal pretreatment of waste hygiene water was investigated as an approach to reduce the amount of energy required to maintain overall system microbial control. The study was conducted in two phases. The laboratory phase was a series of experiments to quantify the degree of microbial population reduction obtained when hygiene waste water and humidity condensate are heated through various thermal cycles. The laboratory phase also included inoculation of the combined wastewater with a thermophilic bacteria to provide a “worst-case” challenge of the thermal cycle being tested. The large scale system phase determined biofilm formation on the surfaces of a variety of materials with and without thermal cycling. Except for survival of the challenge thermophile and some naturally present thermophiles, thermal treatment above 85° C was successful in eradication of the microbial population in the combined hygiene wastewater and formed biofilms.

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 Sundstrand has developed a scalable evaporative heat rejection system called the Multi-Fluid Evaporator (MFE). It was designed to support the Orion Crew Module and to support future Constellation missions. The MFE would be used from Earth sea level conditions to the vacuum of space. This system combines the functions of the Space Shuttle flash evaporator and ammonia boiler into a single compact package with improved freeze-up protection. The heat exchanger core is designed so that radial flow of the evaporant provides increasing surface area to keep the back pressure low. The multiple layer construction of the core allows for efficient scale up to the desired heat rejection rate. A full-scale unit uses multiple core sections that, combined with a novel control scheme, manage the risk of freezing the heat exchanger cores. A four-core MFE prototype was built in 2007.

In a crewed spacecraft environment, atmospheric carbon dioxide (CO2) and moisture control are crucial. Hamilton Sundstrand has developed a stable and efficient amine-based CO2 and water vapor sorbent, SA9T, that is well suited for use in a spacecraft environment. The sorbent is efficiently packaged in pressure-swing regenerable beds that are thermally linked to improve removal efficiency and minimize vehicle thermal loads. Flows are all controlled with a single spool valve. This technology has been baselined for the new Orion spacecraft. However, more data was needed on the operational characteristics of the package in a simulated spacecraft environment. A unit was therefore tested with simulated metabolic loads in a closed chamber at Johnson Space Center during the last third of 2006. Tests were run at a variety of cabin temperatures and with a range of operating conditions varying cycle time, vacuum pressure, air flow rate, and crew activity levels.

Unibeds®* are multimedia layered sorption beds baselined for use in the Space Station Freedom (SSF) water reclamation system. Unibeds® must be sterilized prior to use to avoid the introduction of bacteria into the water reclamation system when the Unibeds® are routinely changed out. In the past, Unibeds® were autoclaved in an attempt to achieve sterility. Some sorbent media used in the Unibeds® decompose when exposed to high temperatures for extended periods. Although no significant sorbent decomposition occurs during the routine autoclave time of 30 minutes, it is uncertain whether sufficient sterilization temperatures are achieved at the Unibed® core. Gamma irradiation has been evaluated as a practical alternative method to achieve sterility and eliminate possible sorbent thermal degradation. Sorbent media were inoculated with irradiation resistant spores (106 CFU/ML) of bacterium Bacillus pumilus and subsequently exposed to radiation doses of 1.5, 2.0, and 2.5 megarads (Mrad).

Long-term manned operation of NASA's Space Station will dictate use of regenerative processes for the revitalization of the Spacecraft atmosphere. An alkaline Static Feed Water Electrolysis System (SFWES) is being developed by Life Systems, Inc. and NASA to generate metabolic oxygen (O2) for the crew, provide hydrogen (H2) for reduction of concentrated carbon dioxide (CO2) and compensate for O2 lost overboard due to Space Station leakage. The SFWES employs highly efficient electrodes with rugged unitized cell construction. Integrated mechanical components and advanced automated Control/Monitor Instrumentation (C/M I) are used to reduce system complexity while enhancing overall reliability and maintainability. Crew size and the unique environment of space drive the system design.

The Static Feed Electrolyzer (SFE) is being developed by the National Aeronautics and Space Administration (NASA) through Life Systems, Inc. (Life Systems) as part of NASA's effort to mature water electrolysis technology for application in the Space Station Environmental Control/Life Support System (ECLSS), Propulsion and Reboost System, Extravehicular Activity (EVA) and Electric Power System (EPS). The water electrolysis process generates metabolic oxygen (O2) for the crew cabin, EVA backpacks and air lock, and provides reactants for carbon dioxide (CO2) removal, CO2 reduction, propulsion/reboost systems and fuel cell electric power generation. The use within all of these applications will make water electrolysis a fundamental utilitylike technology for the Space Station.

The baseline hygiene water reclamation system for Space Station Freedom has been changed from Reverse Osmosis with Multifiltration post-treatment to stand-alone Multifiltration. The Multifiltration concept offers increased system reliability, a decrease in power consumption, and essentially 100% water recovery. Multifiltration is based on well documented sorption technology for removal of contaminant species. System complexity is minimal. Moving parts are limited to one pump and simple valving. Reliable microbial control is obtained by heat sterilization and by the use of iodine as a bactericide. Iodine addition is accomplished in the Unibeds with an iodinated resin which is also used in the Microbial Check Valve (MCV). Microbial Check Valves have proven reliable and effective on board the Space Shuttle since the beginning of the Shuttle program. Power consumption is primarily attributed to heat sterilization. The energy required for the pump and controls is relatively low.

The NASA Johnson Space Center has plans to integrate a Solid Amine Water Desorbed (SAWD II) carbon dioxide removal subsystem into the Variable Pressure Growth Chamber (VPGC). The SAWD II subsystem will be used to remove any excess carbon dioxide (CO2) input into the VPGC which is not assimilated by the plants growing in the chamber. An analysis of the integrated VPGC-SAWD II system was performed using a mathematical model of the system implemented in the Computer-Aided System Engineering and Analysis (CASE/A) package. The analysis consisted of an evaluation of the SAWD II subsystem configuration within the VPGC, the planned operations for the subsystem, and the overall performance of the subsystem and other VPGC subsystems. Based on the model runs, recommendations were made concerning the SAWD II subsystem configuration and operations, and the chambers' automatic CO2 injection control subsystem.

A key component of an Advanced Life Support (ALS) system is the solid waste handling system. One of the most important data sets for determining what solid waste handling technologies are needed is a solid waste model. A preliminary solid waste model based on a six-person crew was developed prior to the 2000 Solid Waste Processing and Resource Recovery (SWPRR) workshop. After the workshop, comments from the ALS community helped refine the model. Refinements included better estimates of both inedible plant biomass and packaging materials. Estimates for Extravehicular Mobility Unit (EMU) waste, water processor brine solution, as well as the water contents for various solid wastes were included in the model refinement efforts. The wastes were re-categorized and the dry wastes were separated from wet wastes. This paper details the revised model as of the end of 2001. The packaging materials, as well as the biomass wastes, vary significantly between different proposed Mars missions.

Poly (vinyl chloride) (PVC) matrix membranes which incorporate the ionophore nonactin have been evaluated as cation exchange membranes for ammonium ion transport in an electrolytic cell configuration. Interest exists for the development of cation selective membranes for removal of low levels (<200ppm) of ammonium ions commonly found in recycled effluent streams in such diverse applications as expected in a Space Station and commercial fisheries. Ammonium ions are generated as a decomposition product of urea and over time build up in concentration, thus rendering the water unsuitable for human consumption. Nonactin is commonly used in a PVC matrix for ion-selective electrodes.

Biological wastewater processing has been under investigation by AlliedSignal Aerospace and NASA Johnson Space Center (JSC) for future use in space. Testing at JSC in the Hybrid Regenerative Water Recovery System (HRWRS) in preparation for future closed human testing has been performed. Computer models have been developed to aid in the design of a new four-person immobilized cell bioreactor. The design of the reactor and validation of the computer model is presented. In addition, the total organic carbon (TOC) computer model has been expanded to begin investigation of nitrification. This model is being developed to identify the key parameters of the nitrification process, and to improve the design and operating conditions of nitrifying bioreactors. In addition, the model can be used as a design tool to rapidly predict the effects of changes in operational conditions and reactor design, significantly reducing the number and duration of experiments required.

Two crops of lettuce (Lactuca sativa cv. Waldmann's Green) were grown in the Regenerative Life Support Systems (RLSS) Test Bed at NASA's Johnson Space Center. The RLSS Test Bed is an atmospherically closed, controlled environment facility for the evaluation of regenerative life support systems using higher plants. The chamber encloses 10.6 m2 of growth area under cool-white fluorescent lamps. Lettuce was double seeded in 480 pots, each containing about 250 cm3 of calcined-clay substrate. Each pot was irrigated with half-strength Hoagland's nutrient solution at an average total applied amount of 2.5 and 1.8 liters pot-1, respectively, over each of the two 30-day crop tests. Average environmental and cultural conditions during both tests were 23°C air temperature, 72% relative humidity, 1000 ppm carbon dioxide (CO2), 16h light/8h dark photoperiod, and 356 μmol m-2s-1 photosynthetic photon flux.

The Microbial Check Valve (MCV) is a canister containing an iodinated ion exchange resin and is used on the Shuttle Orbiter to provide microbial control of potable water. The MCV provides a significant contact kill, and imparts a biocidal iodine residual to the water. The Orbiter MCV has a design life of 30 days. For longer duration applications, such as Space Station Freedom, an extended life is desirable to avoid resupply penalties. A method of in situ MCV regeneration with elemental iodine is being developed. During regeneration water en route to the MCV first passes through a crystalline iodine bed where a concentration between 200 - 300 mg/L I2 is attained. When introduced into the MCV, this high concentration causes an equilibrium shift towards iodine loading, effecting regeneration of the resin. After regeneration normal flow is re-established. Life cycle regeneration testing is currently in progress.

The Microbial Check Valve (MCV) is used on the Space Shuttle to impart an iodine residual to the drinking water to maintain microbial control. Approximately twenty MCV locations have been identified in the Space Station Freedom design, each with a 90 day life. This translates to 2400 replacement units in 30 years of operation. An in situ regeneration concept has been demonstrated that will reduce this replacement requirement to less than 300 units based on data to date and potentially fewer as further regenerations are accomplished. A totally automated system will result in significant savings in crew time, resupply requirements and replacement costs. An additional feature of the device is the ability to provide a concentrated biocide source (200 mg/liter of I2) that can be used to superiodinate systems routinely or after a microbial upset. This program was accomplished under NASA Contract Number NAS9-18113.

The Orion crew module (CM) is being designed to perform survivable land and water landings. There are many issues associated with post-landing crew survival. In general, the most challenging of the realistic Orion landing scenarios from an environmental control standpoint is the off-nominal water landing. Available power and other consumables will be very limited after landing, and it may not be possible to provide full environmental control within the crew cabin for very long after splashdown. Given the bulk and thermal insulation characteristics of the crew-worn pressure suits, landing in a warm tropical ocean area would pose a risk to crew survival from elevated core body temperatures, if for some reason the crewmembers were not able to remove their suits and/or exit the vehicle. This paper summarizes the analyses performed and conclusions reached regarding post-landing crew survival following a water landing, from the standpoint of the crew's core body temperatures.

To date, 59 man-EVA's have been conducted in the Shuttle Program with minimum physiological problems or limitations. The physiological requirements for life support in the Shuttle EVA include pressure, gas composition, inspired CO2 pressure, heat- removal capability, in-suit water replacement, and caloric replacement. These requirements and their basis in verification testing or analysis are reviewed. The operational measures are identified. The suit pressure in combination with a gas composition of at least 92 percent assures that sufficient O2 pressure is available to the crewmember. The nominal suit pressure of 4.3 psi±0.1 psi was maintained during all 59 man-EVA's. The contingency suit pressure was never required to be used. The suit pressure in combination with the cabin pressure and pre-EVA denitrogenation procedures minimize the risk of altitude decompression sickness. There has been no incidence of decompression sickness during Shuttle EVA.