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所属单位：航天学院

发表刊物：Zhongguo Guanxing Jishu Xuebao

摘要：With the increasing of spacecraft mission complexity, the attitude control system of the micro-satellite has higher demand for the fastness and stability of large-angle attitude maneuvering. By taking into account of the torque saturation and the angular velocity limitation in large-angle attitude maneuvering process, a FUZZY PD attitude control method based on eigenaxis rotations and cascade saturation is proposed. The jet thruster and the reaction flywheel are used as joint actuator to provide large and accurate control torque. Compared with traditional PD control law, the unknown parameters of FUZZY PD attitude control system can be automatically set online. Mathematical simulation results show that the proposed FUZZY PD attitude control method can realize large angle maneuver of 50.2° in 125 s, and the stability error can be controlled to within 0.002°. This method has higher accuracy and stability compared with traditional PD control law. © 2017, Editorial Department of Journal of Chinese Inertial Technology. All right reserved.

ISSN号：1005-6734

是否译文：否

发表时间：2017-12-01

合写作者：,吴云华

通讯作者：华冰