Spacecraft Attitude Control Design with Adaptive Bounded Controllers
نویسنده
چکیده
This paper presents the development of a control system design to keep the spacecraft attitude at a prescribed sun vector. A bounded controller is proposed which utilizes the measured sun vector and spacecraft spin rates, and the control gains are model independent and can be tuned for individual axis. An adaptive control scheme is developed for control parameters to ensure closed-loop performance. To demonstrate the effectiveness of proposed controller, a spacecraft engaging the sun safe-hold is simulated.
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