Optimization Problem in Control over a Programmed Turn of a Spacecraft

Details Optimization Problem in Control over a Programmed Turn of a Spacecraft Optimization Problem in Control over a Programmed Turn of a Spacecraft

Sep 2002

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002cosre..40..479l&link_type=abstract

Cosmic Research, v. 40, Issue 5, p. 479-489 (2002).

Mathematics

Scientific paper

The problem of spacecraft reorientation from its initial angular position into a desired final position within a given time interval with a minimum value of the angular moment is considered and solved analytically in this work. It is shown that the control over the spacecraft reorientation, optimal in this sense, might be defined in the class of a regular precession performed by the spacecraft. The moment of the start of deceleration is determined from the principles of the terminal control by using real kinematic parameters of apparatus motion, which increases significantly the accuracy of reorientation. The results of mathematical modeling are presented, showing a high efficiency of the proposed way of reorientation.

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