Considerations for optimization of ground system for reception of television from the apollo spacecraft at lunar distance
Ground system for reception of television from spacecraft at lunar distance
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Ground system for reception of television from spacecraft at lunar distance
Range coverage diagrams for CSM rendezvous radar transponder antenna raised 4 in. and tilted forward 15 deg
Similarities between experimentally measured power spectral density curves of landing radar signal returned from rough surface and computer simulated curves for sinusoidal surfaces
Lunar reflectivity, acquisition altitude, landing radar altimeter beam bandwidth, and Doppler equations verified for use in mathematical model
Flight test data analysis for rendezvous radar performance during simulated lunar mission
Preliminary lunar reflectivity graphs
Performance prediction for LM landing radar over rough terrain
Fixed-base visual simulation study for ability determination of onboard pilot during landing
Specific impulse of LM ascent and descent engines and SM engine
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This final volume of the chronology is divided into three parts: (1) preparation for flight, the accident, and investigation; (2) recovery, spacecraft redefinition, and the first manned flight; and (3) man circles the moon, the Eagle lands, and manned space exploration. Congressional documents, official correspondence, government and contractor reports, memoranda, working papers, and minutes of meetings were used as primary sources. A relatively few entries are based on press releases and newspaper and magazine articles.
A new method of reliability prediction for complex systems is defined. Calculation of both upper and lower bounds are involved, and a procedure for combining the two to yield an approximately true prediction value is presented. Both mission success and crew safety predictions can be calculated, and success probabilities can be obtained for individual mission phases or subsystems. Primary consideration is given to evaluating cases involving zero or one failure per subsystem, and the results of these evaluations are then used for analyzing multiple failure cases. Extensive development is provided for the overall mission success and crew safety equations for both the upper and lower bounds.
Containers, storage compartments, and weight and volume distributions of scientific payloads aboard Apollo spacecraft for lunar exploration
Experimental Apollo spacecraft interface with attached pallet configuration
Mechanical impact attenuation system for Apollo spacecraft provides stable land landing platform, noting deployed heat shields, extended legs, pneumatic bags, etc