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.
Guidance and economical digital attitude control of a land-survey satellite
2017-06-01
409768 byte
Conference paper
Electronic Resource
English
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