Logic and Numerical Methods of Spacecraft Attitude Control and Reconfiguration

Abstract The problem of programmed control of the spacecraft attitude, including in worstcase situations of on-board equipment failures, is considered. During a programmed reorientation (traditionally, by solving an inverse problem of dynamics) there arise singular states of the gyrosystem that interrupt the process and require additional resources to reconfigure the gyroscope frames. A technique is proposed, which is not subject to these drawbacks, does not need an a priori specification of the phase trajectory and is based on a sequential linearization and controllability of the system. To ensure fault-tolerance of the control, a new method of knowledge-based control is suggested, which relies on an original, high-performance logical formalism and an advanced architecture of logic-dynamic control. Example of the application of methods of fault-tolerance control is considered.