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针对飞行器再入飞行过程中存在的复杂气动环境和未知不确定干扰影响,在对扰动提出一定假设的基础上,提出一种基于自适应二阶非奇异终端滑模的控制方案,保证姿态跟踪误差在有限的时间内收敛于零的同时有效削弱控制舵机的抖振,提高系统控制精度。不需要内外扰的先验知识,通过在线自适应辨识扰动上界以消除其影响。最后以气动参数摄动50%作为扰动条件进行了飞行器再入姿态控制仿真,仿真结果表明控制系统消除了参数摄动影响及舵机抖振,因此具有较强鲁棒性。
Aiming at the complex aerodynamic environment and unknown uncertain interference in aircraft reentry flight, a control scheme based on adaptive second-order non-singular terminal sliding mode is proposed based on some assumptions on disturbance, to ensure the attitude tracking error In a limited time convergence to zero while effectively weaken the control servo buffeting and improve system control accuracy. Without the priori knowledge of internal and external disturbances, the disturbance upper bounds can be eliminated by online adaptive identification. Finally, the aerodynamic parameter perturbation of 50% is used as the disturbance condition to simulate the aircraft reentry attitude control. The simulation results show that the control system eliminates the influence of parameter perturbation and servo chattering, so it has strong robustness.