Guidance and economical digital attitude control of a land-survey satellite

We consider a maneuvering land-survey satellite with a digital attitude control system equipped by a strapdown inertial navigation system with astronomical correction, a cluster of four reaction wheels and a magnetic driver. The matrices of optoelectronic converters work in the mode of time delay and integration during optoelectronic observation of the Earth surface parts by a set of routes for their scanning. We study the problems on analytical synthesis of the vector spline attitude guidance laws for the scanning land-survey routes and the spacecraft rotational maneuvers, and also the problems on synthesis of the satellite economical attitude control laws for fulfillment of the guidance laws.