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Design and Robust Analysis for Spacecraft Attitude Controller

Zhou Fengqi Han Yanhua Zhou Jun (School of Astronautics,Northwestern Polytechnical University,Xi'an 710072)   

  • Published:2007-04-25

Abstract: The spacecraft's attitude control system was divided into the outer loop that was angle loop and the inner loop that was angle velocity loop based on their time scales.Then the control law of each loop was designed independently using exact linearization method.In the inner loop,robust stability was analysed using small-gain theorem considering the existence of perturbation of spacecraft moment inertia.