固定推力和总冲约束的高空飞行器姿态控制

Spacecraft attitude control constrained by fixed thrust and total impulse

针对执行器为固定推力的喷气反作用装置的高空飞行器姿态控制问题,以推力总冲最小为约束,以Lyapunov稳定性和滑动模态可达性为要求,选择线性和指数函数复合的切换函数,设计了一个实例系统的控制器。系统姿态和姿态机动过程的仿真结果表明,该设计能消除系统参数变化以及干扰力矩的影响,并能准确调整姿态。

For the attitude control of the spacecraft using fixed-thrust jet reaction devices as actuator,a control design is detailed with respect to the constraint of minimized total thrust impulse,which can satisfy the Lyapunov stability and sliding mode reachability.Wherein,the switching function comprises linear and exponential functions.The simulation results of spacecraft attitude and maneuver show that the proposed design approach can effectively eliminate the influence of system parameter variations and disturbance torque,and tune the attitude precisely.