微型固体推进器阵列与磁力矩器联合姿态控制方法  

A Joint Attitude Control Algorithm Using MEMS Solid Propellant Thruster Array and Magnetic Torquer

作　　者：侯晓磊 周康博 刘勇[1] 潘泉[1] HOU Xiao-lei;ZHOU Kang-bo;LIU Yong;PAN Quan(Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]西北工业大学自动化学院,西安710072

出　　处：《宇航学报》2020年第3期343-352,共10页Journal of Astronautics

基　　金：国家自然科学基金(61703343,61503304);陕西省自然科学基金(2018JQ6070);中央高校基本科研业务费(3102018JCC003)

摘　　要：针对传统皮纳卫星姿态控制系统中磁力矩器输出力矩小、姿态控制响应慢等问题,提出一种微型固体推进器阵列与磁力矩器联合姿态控制方法,提高了控制精度,缩短了控制周期,并利用Lyapunov稳定性理论证明了算法的稳定性。首先建立微型固体推进器阵列优化点火模型,然后给出其补偿控制时间设置方法,并推导出大角速度阻尼控制律和辅助速度阻尼控制律,同时设计了基于混合系统模型的姿态捕获联合控制律,最后通过仿真验证了速度阻尼联合控制律和姿态捕获联合控制律的有效性。仿真结果表明,相较于传统的纯磁控方法,联合控制方法能够有效提高控制精度,大幅度缩短控制周期。This paper proposes a joint attitude control algorithm using MEMS solid propellant thruster array and magnetic torquer to tackle the issues of low torque outputs and slow attitude response in the conventional pico/nano-satellite attitude control systems. The novel approach improves the control accuracy and shortens the system response time. The stability of the proposed algorithm is proved by using the Lyapunov stability theory. An optimized ignition model of the MEMS solid propellant thruster array is established. The compensation time setting method is provided. Then, the control laws for large angular velocity damping and auxiliary velocity damping are proposed, as well as the joint control law for attitude acquisition based on the hybrid system model. Finally, the effectiveness of the velocity damping joint control law and joint control law for attitude acquisition is verified through simulation. The simulation results demonstrate that compared with the conventional magnetic torque control approaches, the proposed joint control scheme effectively improves the control accuracy and shortens the system response time.

关 键 词：微型固体推进器阵列 磁力矩器 姿态控制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]