Optimal control of a change in attitude of a gyrostat satellite

Details Optimal control of a change in attitude of a gyrostat satellite Optimal control of a change in attitude of a gyrostat satellite

Jan 1979

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1979kosis..17...18z&link_type=abstract

Kosmicheskie Issledovaniia, vol. 17, Jan.-Feb. 1979, p. 18-23. In Russian.

Computer Science

Attitude Gyros, Optimal Control, Satellite Attitude Control, Satellite Orbits, Circular Orbits, Control Theory, Gravitational Fields, Kinetic Theory, Lagrange Multipliers

Scientific paper

The present analysis deals with the problem of changing the attitude of a gyrostat satellite moving along a circular orbit in a Newtonian gravitational field. The optimal law of controling the kinetic moments of three rotors situated at the principal inertia axes of the satellite is synthesized, and the integral quadratic functional of the rotors' kinetic moment components is minimized.

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