Guidance and adaptive-robust attitude & orbit control of a maneuvering information satellite

Abstract

We consider a maneuvering information satellite which may be placed on an orbit with altitude from 600 up to 1000 km. The satellite attitude and orbit control system contains a strapdown inertial navigation system, cluster of four reaction wheels, magnetic driver and an  engine unit with eight electro-reaction engines. We study problems on design of algorithms for spatial guidance, in-flight identification and adaptive-robust control of the satellite motion on sun-synchronous orbit.