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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 667 records · Page 37
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Navy-developed life support systems for fully enclosed protective suits

The development and performance of an environmental control unit capable of supporting a man in an impermeable suit at ambient temperatures up to 140 F for periods of up to two hrs is reported. The basic suit operation consists of cooling by wet ice contained in a suitcase. The system is designed to circulate and cool the air within the suit, to remove excess moisture and carbon dioxide, and to maintain a safe oxygen level.

Orner, G. M.↗
NASA NTRS1972

Analysis of fungal type isolates taken from a 90-day manned test of an advanced regenerative life support system

Fungal-like cultures isolated before, during, and after the 90-day test from samples of space station simulator (SSS) atmosphere, surfaces, subsystem componets, and crew dermal sites were identified to genus. Out of the original 525 isolates, approximately 80% were classified as bacteria. Laboratory methods (culture media, moisturization, and incubation temperatures) favored the recovery of medically significant bacteria rather than fungi. Therefore, fungal isolates were mostly, nonfastidious types which are ubiquitous in soil and air and commonly contaminate laboratory cultures of pathogens. Predominant isolates were species of Aspergillus, Penicillium, Pullularia, Rhodotorula, and various yeasts. No instances of fungal proliferation were observed; test data reflect the survival of environmental types indigenous to the SSS pretests.

Sofios, M.↗
NASA NTRS1972

Life support system definition for a low cost shuttle launched space station.

Discussion of the tradeoffs and EC/LS definition for a low cost shuttle launched space station to be launched in the late 1970s for use as a long-term manned scientific laboratory. The space station consists of 14-ft-diam modules, clustered together to support a six-man crew at the initial space station (ISS) level and a 12-man crew at the growth space station (GSS) level. Key design guidelines specify low initial cost and low total program cost and require two separate pressurized habitable compartments with independent lift support capability. The methodology used to select the EC/LS design consisted of systematically reducing quantitative parameters to a common denominator of cost. This approach eliminates many of the inconsistencies that can occur in such decision making. The EC/LS system selected is a partially closed system which recovers urine, condensate, and wash water and concentrates crew expired CO2 for use in a low thrust resistojet propulsion system.

Nelson, W. G.↗
NASA NTRS1972

Progress in regenerative life support systems for a lunar laboratory.

Research and development work for application of Environmental and Thermal Control/Life Support System (ETC/LSS) on a lunar base mission is reviewed, covering lunar mission requirements and constraints, a Lunar Base ETC/LSS reliability assessment, food regeneration, the water and waste system, the atmosphere regeneration subsystem, and atmosphere contaminant control. The establishment of detailed system design criteria for the Lunar Surface Base LSS is considered to be premature at this phase of the project. Some recommendations are given instead for guidance in further R & D efforts.

Pecoraro, J. N.↗
NASA NTRS1972

The Space Station Prototype Program - The development of a regenerative life support system for extended-duration missions.

Design concepts and test philosophies which may contribute to the development of a low-cost maintainable environmental control/life support system are examined. It is shown that the concept of producing flight prototype equipment during a developmental program can reduce the eventual cost of a flight system by incorporating realistic flight-type design requirements without imposing exacting design features and stringent controls. A flight prototype design is one that can be converted readily into an actual flight design without any conceptual change. Modularity of subsystems provides the system and the program a degree of flexibility relative to the eventual vehicle configuration and technological improvements.

Willis, N. C., Jr.↗
NASA NTRS1973

Generalized environmental control and life support system computer program (G189A) configuration control

A G189A simulation of the shuttle orbiter EC/lSS was prepared and used to study payload support capabilities. Two master program libraries of the G189A computer program were prepared for the NASA/JSC computer system. Several new component subroutines were added to the G189A program library and many existing subroutines were revised to improve their capabilities. A number of special analyses were performed in support of a NASA/JSC shuttle orbiter EC/LSS payload support capability study.

Blakely, R. L.↗
NASA NTRS1974

Development status of solid polymer electrolyte water electrolysis for manned spacecraft life support systems

Details of the design and system verification test results are presented for a six-man-rated oxygen generation system. The system configuration incorporates components and instrumentation for computer-controlled operation with automatic start-up/shutdown sequencing, fault detection and isolation, and with self-contained sensors and controls for automatic safe emergency shutdown. All fluid and electrical components, sensors, and electronic controls are designed to be easily maintainable under zero-gravity conditions. On-board component spares are utilized in the system concept to sustain long-term operation (six months minimum) in a manned spacecraft application. The system is centered on a 27-cell solid polymer electrolyte water electrolysis module which, combined with the associated system components and controls, forms a total system envelope 40 in. high, 40 in. wide, and 30 in. deep.

Nuttall, L. J.↗
NASA NTRS1974

Generalized environmental control and life support system computer program (G189A) configuration control, phase 2

A method for updating and maintaining the G189A program library and documentation for all program users is provided. The effort also involves: (1) providing instruction and recommendations for the use and application of the program, (2) developing new subroutines and the logic required for new simulations, (3) supporting special analyses required by CSD, and (4) conduct studies to define and understand the interaction of the shuttle ECLSS and propose payload ECLSS and ECS designs.

Blakely, R. L.↗
NASA NTRS1975

Phase 1 engineering and technical data report for the thermal control extravehicular life support system

A shuttle EVLSS Thermal Control System (TCS) is defined. Thirteen heat rejection subsystems, thirteen water management subsystems, nine humidity control subsystems, three pressure control schemes and five temperature control schemes are evaluated. Sixteen integrated TCS systems are studied, and an optimum system is selected based on quantitative weighting of weight, volume, cost, complexity and other factors. The selected sybsystem contains a sublimator for heat rejection, a bubble expansion tank for water management, and a slurper and rotary separator for humidity control. Design of the selected subsystem prototype hardware is presented.

Source record↗
NASA NTRS1975

Improved thermal storage material for portable life support systems

The availability of thermal storage materials that have heat absorption capabilities substantially greater than water-ice in the same temperature range would permit significant improvements in performance of projected portable thermal storage cooling systems. A method for providing increased heat absorption by the combined use of the heat of solution of certain salts and the heat of fusion of water-ice was investigated. This work has indicated that a 30 percent solution of potassium bifluoride (KHF2) in water can absorb approximately 52 percent more heat than an equal weight of water-ice, and approximately 79 percent more heat than an equal volume of water-ice. The thermal storage material can be regenerated easily by freezing, however, a lower temperature must be used, 261 K as compared to 273 K for water-ice. This work was conducted by the United Aircraft Research Laboratories as part of a program at Hamilton Standard Division of United Aircraft Corporation under contract to NASA Ames Research Center.

Kellner, J. D.↗
NASA NTRS1977

Generalized environmental control and life support system computer program (G189A) configuration control, phase 2

The G189A simulation of the Shuttle Orbiter ECLSS was upgraded. All simulation library versions and simulation models were converted from the EXEC2 to the EXEC8 computer system and a new program, G189PL, was added to the combination master program library. The program permits the post-plotting of up to 100 frames of plot data over any time interval of a G189 simulation run. The overlay structure of the G189A simulations were restructured for the purpose of conserving computer core requirements and minimizing run time requirements.

Mcenulty, R. E.↗