Abstract
Design, mechanization, and flight test results of the Mariner Mars 1969 navigation, guidance and control systems, are discussed. A trajectory design section describes near-earth launch trajectory, planetary targeting and constraints, as well as the tradeoffs made on the trajectory selection. Among the factors considered are reliability, direct ascent vs. parking orbit and higher spacecraft weight vs. extended launch window. Guidance and orbit determination factors are discussed, including earth-based radio and spacecraft optical navigation and the accuracy of orbit determination and maneuver execution. The control systems section identifies differences in the attitude control, midcourse maneuver, and science instrument scan pointing systems from those used in previous Mariner spacecraft. A description is given of the new Central Computer and Sequencer (CC&S) system, used for the first time on this mission, which allows extremely flexible spacecraft operation using in-flight reprogramming of the computer memory by radio command. Finally, reliability summaries and performance evaluations permit conclusions as to the effectiveness of the Mariner Mars 1969 navigation, guidance, and control systems to conduct near-term and more advanced planetary missions.
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