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在近空间飞行器加速爬升模态下,传统的滑模控制方法在处理不确定性问题时,存在收敛速度慢、鲁棒性不强和抖振严重等不足。针对这些问题,本文提出双幂次趋近律滑模控制方法来设计飞行控制器,从而实现飞行器爬升段轨迹的精确跟踪。将飞行器非线性模型进行精确反馈线性化处理,并利用李雅普诺夫稳定性理论进行稳定性分析。仿真分析了双幂次趋近律滑模控制方法和传统滑模控制方法的控制效果。结果表明:在处理具有参数不确定性和外界干扰的非线性系统时,双幂次趋近律滑模控制方法能够精确地跟踪指令信号,并且具有较强的稳定性和鲁棒性。
In the near-space vehicle accelerating and climbing mode, the traditional sliding mode control method has some shortcomings such as slow convergence rate, poor robustness and serious buffeting when dealing with uncertainties. In order to solve these problems, this paper proposes a bimodulus approach law sliding mode control method to design a flight controller, so as to achieve accurate tracking of the trajectory of the climb section. The nonlinear model of the aircraft is accurately fed back to linearization, and the stability analysis is performed by using Lyapunov stability theory. The control effect of the bimodulus approach law sliding mode control method and the traditional sliding mode control method is simulated and analyzed. The results show that when dealing with nonlinear systems with parameter uncertainty and external disturbance, the bilinear approach law sliding mode control method can precisely track the command signal with strong stability and robustness.