执行器部分失效的微纳卫星姿态自适应终端滑模控制方法研究

Research on the sliding mode control method for an adaptive terminal of microsatellites attitude with partial loss of actuator effectiveness

针对微纳卫星中存在多源干扰和执行器部分失效的问题,提出了一种基于自适应控制的非奇异终端滑模控制方法。该方法无需假设已知执行器部分失效故障的最小值,首先通过设计干扰观测器实时估计,并抵消飞轮转动引起的可建模振动干扰,提高了卫星姿态控制系统的控制精度。然后通过设计非奇异终端滑模控制器消除能量有界干扰并使姿态控制系统能在有限时间内收敛。最后,通过数值仿真验证了该方法的有效性。

It proposes a singular terminal sliding mode controller based on an adaptive control for attitude control system(ACS)of microsatellites with partial loss of actuator effectiveness and multiple disturbances simultaneously.This method does not require the minimum value of partial loss of actuator effectiveness.Aiming at improving the control accuracy of ACS,it designs a disturbance observer to estimate and reject the vibration disturbance caused by flywheel,and eliminates the norm-bounded disturbance based on a non-singular terminal sliding mode controller.The attitude control system can be convergence in finite time.Finally,the effectiveness of the proposed approach is verified by numerical simulations.