Attitude control of a rigid spacecraft with two momentum wheel actuators using genetic algorithm

Abstract The control problem of the spacecraft attitude using two momentum wheel actuators is investigated. It is well-known that attitude of a rigid spacecraft can be controlled by using three momentum wheels. If one of the momentum wheels is failure, the complete spacecraft equations are not controllable. When the total angular momentum of the system is zero, the control problem of the spacecraft attitude becomes a steering problem for a drift free control system. In this paper, based on the optimal control theory, a genetic algorithm for steering a rigid spacecraft with two momentum wheels is proposed. The genetic algorithm provide the results of a numerical simulation to prove its efficiency and stability.

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