This report summarizes the results of five separate but related analytical investigations, into the engineering design of a calibration satellite. The suitability and adaptability of the MISTRAM, GLOTRAC, and AN/DPN-66 C-Band radar transponders, and xenon flash optical beacon, for use in a proposed calibration satellite is discussed. The overall results of a separate satellite integration study are likewise presented. Design specifications have been developed which allow initiation of transponder development. The electronic transponders required in a calibration satellite can be developed essentially from existing missile-rated designs. Some significant changes must be made however to meet the more stringent satellite requirements, such as extended operational life (specified at six months), high vacuum, space radiation, and extended temperature ranges. The detailed preliminary satellite design study has established that an adaptation of the RCA TIROS satellite will fulfill calibration satellite requirements. Design areas where advanced techniques are required include the attitude stabilization and the command/control subsystems. A recommended program for development of an austere calibration satellite "package" is also presented, in lieu of a full-scale satellite program.
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