柔性充气空间飞行器姿态控制系统设计

针对充气空间飞行器刚柔耦合影响下的高精度姿态控制问题，提出基于自抗扰控制理论的姿态控制系统设计方法。建立刚柔耦合动力学模型，综合采用线性自抗扰控制、姿态机动路径规划、脉冲调宽调频调制、滤波处理等控制策略进行柔性充气空间飞行器姿态控制系统设计。通过数值仿真实验对所设计系统进行验证，并与传统PID控制进行对比分析。仿真结果表明，采用新方法设计的柔性充气空间飞行器姿态控制系统可以适应大角度姿态机动，能够有效抑制充气囊体的柔性振动，在节省燃料消耗的同时实现高精度姿态控制。

Design of Attitude Control System for Flexible Inflatable Spacecraft

An attitude control method based on the theory of active disturbance rejection control is proposed to accurately control the attitude of flexible inflatable spacecraft. A rigid-flexible coupling dynamic model is established， and a coupling attitude control system is designed using the linear active disturbance rejection controller，attitude maneuver path planning algorithm，pulse-width pulse-frequency (PWPF) modulator and low-pass filter. The control system can be used to control the attitude and suppress the elastic vibration simultaneously. The numerical simulations are conducted to verify the effectiveness of the proposed system. In contrast to the traditional PID control，the simulated results show that the attitude control system for flexible inflatable spacecraft designed by the proposed attitude control method can adapt to large-angle attitude maneuver and effectively suppress the flexible vibration of inflatable capsule，improve the attitude accuracy of flexible spacecraft and avoid frequent on-off of the engine to save fuel.