微小卫星联合执行机构的递阶饱和姿态控制方法  

Cascade-saturation attitude control of micro-satellite based on combination actuator

作　　者：华冰[1] 陈林[1] 吴云华[1] HUA Bing1, CHEN Lin1, WU Yun-hua1(Nanjing University of Aeronautics and Astronautics, Nanjing 210016, Chin)

机构地区：[1]南京航空航天大学,南京210016

出　　处：《中国惯性技术学报》2017年第6期821-827,共7页Journal of Chinese Inertial Technology

基　　金：国家自然科学基金(61673208;61403197);江苏省自然科学基金(BK20140830)

摘　　要：随着航天飞行任务复杂程度的提高,微小卫星姿态控制系统对实现大角度姿态机动的快速性及稳定性有着较高的要求。考虑到在实际大角度姿态机动过程中力矩饱和及角速度限制的因素,提出了基于欧拉轴转动的递阶饱和模糊PD姿态控制律,同时采用喷气推力器和反作用飞轮作为联合执行机构为微小卫星姿态机动提供大且精确的控制力矩。与传统PD控制律相比,模糊PD姿态控制系统的未知参数可在线自动整定。数学仿真结果表明,基于欧拉轴转动的递阶饱和模糊PD姿态控制系统能够在125 s内实现50.2°的大角度机动,稳定误差能够控制在0.002°之内。与传统PD控制律相比,此方法具有更高的精度及稳定性。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.

关 键 词：大角度机动 递阶饱和 联合执行机构 模糊PD控制 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]