Attitude control electronics mechanization for communication satellites

After a general discussion of the requirements and constraints of an attitude control system electronics package for a long life synchronous satellite, the proposed design architecture and packaging, based on state-of-the-art technology, are discussed. The design is based on a special purpose computer architecture using large scale integrated CMOS components permitting the solution of complex control laws, with a minimum power and weight penalty. Long life, high reliability operation is obtained by low level functional cross-strapping and military approved manufacturing and screening techniques. Packaging using unclad LSI chips mounted on hybrid board substrates increases reliability and decreases cost by minimizing parts handling. Once the basic processor and memory units have been designed the system can be mated with various input/output electronics to perform the control functions for a wide variety of spacecraft.