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《Journal of Astronautics》 2001-01
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Li Yingtang Fei Congyu (Shanghai Institute of Satellite Engineering,Shanghai 200240)  
As rotating solar array wing about a satellite body,the control performance of satellite attitude will be deteriorated by the uncertainty of satellite inertia and the disturbance of solar array wing drive torque.In order to improve the attitude control accuracy,a robust control law of satellite attitude is developed based on a kind of nonlinear control method.The stability of the control law is assured according to the Lyapunov stability theory.A real simulation example also verifies that the nonlinear control law designed is more effective than traditional linear control law.
【CateGory Index】: V448.22
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