Apollo spacecraft to test escape system in white sands test news release no. 64-299
Testing plans for Apollo spacecraft escape system under simulated catastrophic launch vehicle failure
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Testing plans for Apollo spacecraft escape system under simulated catastrophic launch vehicle failure
Thermodynamic performance test analyses for Apollo spacecraft ascent, descent, and service propulsion system engines to define hypergol engine restart limits
Insulated wire selections on Apollo spacecraft and lunar module
Effect of heat shield flexibility on water landing loads of Apollo spacecraft models
Quantitative analysis of microorganisms found on Apollo spacecraft
Qualification tests of tower jettison motors for Apollo spacecraft program launch escape systems
Theoretical and experimental data on Apollo command module /CM/ during water impact
Cold flow and hot firing test details for Apollo spacecraft ascent, descent, and service propulsion system engines to define hypergol engine restart limits
The applications of nonmetallic materials to the structures of Apollo spacecraft are discussed. The spacecraft components are examined and the rationale behind the use of specific nonmetallic materials is presented. The emphasis is on the compatibility of the materials with the oxygen enriched atmosphere of the spacecraft enclosures.
Apollo Manned Spacecraft Program systems design requirements, emphasizing instrumentation system and Phase I spacecraft
Response of the Apollo command module, service and lunar module airframe while in a docked configuration in the flight environment was measured in a frequency band encompassing the first two bending modes. Transfer characteristics from thrust-application point to control-system sensor were examined. The frequency and the stability margins of the first two predominant structural resonances were verified by the test. This report describes the flight test that was performed and the postflight data analysis.
The methods employed by NASA to establish configuration control of nonmetallic materials on Apollo spacecraft are described. A five step procedure for examining contractor materials for suitability and compatibility is presented. The compatibility of the materials with the oxygen enriched environment of the spacecraft enclosures is emphasized.
A chronology of the Apollo spacecraft development and production program is presented. The subjects discussed are: (1) defining contractural relations, (2) developing hardware distinctions, and (3) developing software ground rules. Illustrations, drawings, and photographs are used extensively to supplement the technical writing. Descriptions of life support systems, communication equipment, propulsion systems, control devices, and spacecraft components are provided.
The development of the Apollo spacecraft is traced along with that of Saturn V. Emphasis is placed on the detailed engineering design and exhaustive testing performed to qualify both the command and service modules and the lunar module for manned flight.
Theoretical and experimental data on Apollo command module during water impact
Elimination of spurs in Apollo spacecraft telemetry signal transmission
Warning time required by Apollo spacecraft to successfully abort in event of launch vehicle explosion
Failure analysis of flaw growth characteristics of 6Al-4V titanium forgings used in Apollo spacecraft propellant tanks