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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 91 records · Page 5
All sourcesNASA NTRSDOE OSTI
NASA NTRS1971

Final Environmental Impact Statement for Langley

The Langley Research Center is described, together with the nature of its activities, from which it can be seen that the Center is basically not a major pollution source. Geographical, geological, and climatic charateristics of the site are also described. inasmuch as they influence both the choice of disposal methods and the environmental effects of the pollutants. The known or probable pollution sources at the Center are described. Where the intensities of these sources might exceed the recommended guide-lines, the corrective actions that have been taken or are being taken are described. The entire inventory of pollution sources and control methods is summarized in an appendix.

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NASA NTRS1971

Final environmental impact statement for Ames Research Center

The NASA-Ames Research Center is described. together with the nature of its activities, from which it can be seen that the center is basically not a major pollution source. Geographical, and climatic characteristics of the site are described. inasmuch as they influence both the choice of disposal methods and the environmental effects of the pollutants. The known or probable pollution sources at the center are described. Where the intensities of these sources might exceed the recommended guidelines, the corrective actions that have been taken are described.

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NASA NTRS1972

An On Board Processor (OBP) for OAO C

A stored program computer and its application on OAO is considered. The parallel computer has a memory capacity of 16,384 words of 18 bits each, one central processor unit, two 4096 word memory units, and one input/output unit. The I/O has no direct data connection with the CPU so that all data flow between these two units must pass through memory by way of the memory data bus. The primary functions of the onboard computer are auxiliary command storage, spacecraft monitoring and malfunction reporting, data compression and status summary, and possible performance of emergency corrective action.

Hartenstein, R. G.↗
NASA NTRS1971

Apollo 15 mission main parachute failure

The failure of one of the three main parachutes of the Apollo 15 spacecraft was investigated by studying malfunctions in the forward heat shield, broken riser, and firing the fuel expelled from the command module reaction control system. It is concluded that the most probable cause was the burning of raw fuel being expelled during the latter portion of depletion firing. Recommended corrective actions are included.

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NASA NTRS1972

Application of an onboard processor to the OAO C spacecraft

The design of a stored program computer for spacecraft use and its application on the fourth Orbiting Astronomical Observatory (OAO) is reported. The computer is a medium scale, parallel machine with a memory capacity of 16384 words of 18 bits each. It possesses a comprehensive instruction repertoire and operates on 45 W of power (including the dc-to-dc converter). The machine operates at a 500-kHz rate and executes an add instruction in 10 microseconds. Its primary functions on OAO C will be auxiliary command storage, spacecraft monitoring and malfunction reporting, data compression and status summary, and possible performance of emergency corrective action for certain anomalous situations.

Stewart, W. N.↗
NASA NTRS1971

Apollo 14 mission circuit breaker anomaly

Continuity through the circuit breaker in the mechanically closed condition was prevented by a foreign substance on the contact surface onboard Apollo 14. It was concluded that this was the only failure of this type in over 3400 units that were flown, and since no circuit breaker is a single-point failure for crew safety or mission success, no corrective action was taken.

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NASA NTRS1971

Disaster warning satellite study

The Disaster Warning Satellite System is described. It will provide NOAA with an independent, mass communication system for the purpose of warning the public of impending disaster and issuing bulletins for corrective action to protect lives and property. The system consists of three major segments. The first segment is the network of state or regional offices that communicate with the central ground station; the second segment is the satellite that relays information from ground stations to home receivers; the third segment is composed of the home receivers that receive information from the satellite and provide an audio output to the public. The ground stations required in this system are linked together by two, separate, voice bandwidth communication channels on the Disaster Warning Satellites so that a communications link would be available in the event of disruption of land line service.

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NASA NTRS1972

Apollo experience report: Lunar module communications system

The development of the lunar module communications system is traced from the initial concept to the operational system used on manned lunar missions. The problems encountered during the development, the corrective actions taken, and recommendations for similar equipment in future programs are included. The system was designed to provide communications between the lunar module and the manned space flight network, between the lunar module and the command and service module, and between the lunar module and the extravehicular crewmen. The system provided the equipment necessary for voice, telemetry, and television communications; ranging information; and various communications links.

Dietz, R. H.↗
NASA NTRS1973

Apollo experience report: Ascent propulsion system

The development of the Apollo lunar module ascent propulsion subsystem is documented. The ascent propulsion subsystem was designed, built, and tested to provide propulsive power for launching the ascent stage of the lunar module from the surface of the moon into lunar orbit for rendezvous with the orbiting command and service module. Because total redundancy was prohibitive in this subsystem, special emphasis had to be placed on reliability in design with adequate demonstration short of an extensive flight-demonstration program. The significant technical problems encountered during all phases of the program are identified and the corrective actions are discussed. Based on this experience, several recommendations are made for any future program with similar subsystem requirements.

Humphries, C. E.↗
NASA NTRS1973

Apollo experience report: Lunar module structural subsystem

In the Apollo Program, the lunar-orbit rendezvous mode was used for the lunar-landing mission. To accomplish the lunar landing, a lunar module spacecraft was built. A description of the design requirements for the structural subsystem and of the structural configuration and the method of design verification are given. A discussion is presented of several problems encountered and the corrective actions taken during the designing, manufacturing, and testing of the lunar module.

Weiss, S. P.↗
NASA NTRS1973

Apollo experience report: Power generation system

A comprehensive review of the design philosophy and experience of the Apollo electrical power generation system is presented. The review of the system covers a period of 8 years, from conception through the Apollo 12 lunar-landing mission. The program progressed from the definition phase to hardware design, system development and qualification, and, ultimately, to the flight phase. Several problems were encountered; however, a technology evolved that enabled resolution of the problems and resulted in a fully manrated power generation system. These problems are defined and examined, and the corrective action taken is discussed. Several recommendations are made to preclude similar occurrences and to provide a more reliable fuel-cell power system.

Bell, D., III↗
NASA NTRS1973

Apollo experience report: The problem of stress-corrosion cracking

Stress-corrosion cracking has been the most common cause of structural-material failures in the Apollo Program. The frequency of stress-corrosion cracking has been high and the magnitude of the problem, in terms of hardware lost and time and money expended, has been significant. In this report, the significant Apollo Program experiences with stress-corrosion cracking are discussed. The causes of stress-corrosion cracking and the corrective actions are discussed, in terminology familiar to design engineers and management personnel, to show how stress-corrosion cracking can be prevented.

Johnson, R. E.↗
NASA NTRS1973

Apollo experience report: The cryogenic storage system

A review of the design, development, and flight history of the Apollo cryogenic storage system and of selected components within the system is presented. Discussions are presented on the development history of the pressure vessels, heaters, insulation, and selected components. Flight experience and operational difficulties are reported in detail to provide definition of the problems and applicable corrective actions.

Chandler, W. A.↗
NASA NTRS1970

Apollo 11 mission: Glycol temperature control valve

An analysis was made of the cause or causes of malfunctions in the glycol temperature control valve during the Apollo 11 mission. The valve was designed to control inlet temperatures at 45 (+ or - 3) F. Test results show malfunctions were caused by a bearing failure on the worm gear shaft in the actuator. It was concluded that no corrective action was needed because an existing procedure allows manual setting of the value at a position which will meet system requirements.

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NASA NTRS1973

Monitoring and control of fuel-cell system by digital computer

The computer was programmed to handle data, perform limit checks, control normal operation, take corrective actions, and initiate shutdown for a fuel-cell system. The system was operated under computer control for periods up to 30 hr. The adequacy of the programming and interfacing techniques used was verified.

Hagedorn, N. H.↗
NASA NTRS1971

Saturn 5 Launch Vehicle Flight Evaluation Report, AS-510, Apollo 15 Mission

A postflight analysis of the Apollo 15 flight is presented. The performance of the launch vehicle, spacecraft, and lunar roving vehicle are discussed. The objective of the evaluation is to acquire, reduce, analyze, and report on flight data to the extent required to assure future mission success and vehicle reliability. Actual flight problems are identified, their causes are determined, and recommendations are made for corrective actions. Summaries of launch operations and spacecraft performance are included. Significant events for all phases of the flight are tabulated.

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NASA NTRS1973

Saturn 1B launch vehicle flight evaluation report, SA-206, Skylab-2

The performance evaluation of the SA-206 launch vehicle for the Skylab 2 launch is presented. Flight problems are identified, the causes are determined, and recommendations are made for appropriate corrective action. Summaries of launch operations and spacecraft performance are included. The significant events, failures, and anomalies are tabulated.

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