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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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Preliminary results from Mossbauer instrumental analysis of Apollo 12 lunar rock and soil samples
Carbon monoxide accumulator cell for spacecraft mass spectrometer atmospheric sensor system
Inlet leak analysis for spacecraft mass spectrometer atmospheric sensor system
Lunar base synthesis, mission analysis, shelter design, and cost and resource estimates - summary
Research methods for investigating infectious disease in manned space flight without human exposure
Preliminary research requirements analysis and design and cost synthesis of ground research facilities for hypersonic aircraft
Parameteric research requirements analysis and synthesis of ground research facilities for hypersonic aircraft
Analysis of ground research facilities for hypersonic aircraft
Summary of analyses on research requirements and research facilities for hypersonic aircraft
Analysis of heat transfer characteristics of venting cryogen tank - Vol. 3
For abstract, see N72-14799.
Computer systems program specifications are presented for the modular space station information management system. These are the computer program contract end item, data bus system, data bus breadboard, and display interface adapter specifications. The performance, design, tests, and qualification requirements are established for the implementation of the information management system. For Vol. 1, see N72-19972.
For abstract, see .
For abstract, see .
The overall feasibility of the technical requirements and concepts for a rotor system research aircraft (RSRA) was determined. The designs of two aircraft were then compared against the RSRA requirements. One of these is an all new aircraft specifically designed as an RSRA vehicle. A new main rotor, transmission, wings, and fuselage are included in this design. The second aircraft uses an existing Sikorsky S-61 main rotor, an S-61 roller gearbox, and a highly modified Sikorsky S-67 airframe. The wing for this aircraft is a new design. Both aircraft employ a fan-in-fin anti-torque/yaw control system, T58-GE-16 engines for rotor power, and TF34-GE-2 turbofans for auxiliary thrust. Each aircraft meets the basic requirements and goals of the program. The all new aircraft has inflight variable main rotor shaft tilt, a side-by-side cockpit seating arrangement, and is slightly faster in the compound mode. It is also somewhat lighter since it uses new dynamic components specifically designed for the RSRA. Preliminary development plans, including schedules and costs, were prepared for both of these aircraft.
The author has identified the following significant results. Analysis of U-2 imagery of CARETS site indicates smoke plumes can be easily detected. First look at selected ERTS-1 color composites demonstrates plumes from forest fires can be detected.
An analysis of the critical parameters involved in designing systems for spacecraft maneuvers involved in stationkeeping, docking, orbital assembly, satellite inspection and retrieval, and payload deployment is presented. The fixed base simulation was performed on a hybrid computer and includes a cathode ray tube display so that the maneuvers can be visually monitored by a pilot located in the active vehicle. Both automatic and manual control modes are included and the pilot can switch between the two modes as desired. A complete description of the hybrid simulation is provided and simulation results are described. Major digital subroutines, flow charts, and analog wiring diagrams are provided.
A comparison of the concepts of auxiliary propulsion systems proposed for the space shuttle vehicle is discussed. An evaluation of the potential of integration between the reaction control system and the orbit maneuvering system was conducted. Numerous methods of implementing the various levels of integration were evaluated. Preferred methods were selected and design points were developed for two fully integrated systems, one partially integrated system, and one separate system.