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针对吸气式高超声速飞行器的飞行控制问题,提出一种新的预设性能模糊反演控制设计方法。通过构造一种新的预设性能函数,在初始误差正负未知的情况下,可以保证跟踪误差能够按照预定的收敛速度、超调量及稳态误差收敛至任意小的区域,同时实现了对跟踪误差稳态性能和瞬态性能的约束。为提高控制系统的鲁棒性,在反演控制的设计框架下,引入模糊控制器逼近动力学模型中的不确定项。为避免传统反演方法中存在的“微分膨胀”问题,引入滑模微分器对虚拟控制量的导数进行精确估计。最后,通过不同初始误差下的轨迹仿真验证所设计控制系统的有效性。
Aiming at the flight control of aspirated hypersonic vehicle, a new design method of fuzzy inversed control of preset performance is proposed. By constructing a new preset function, under the condition of positive and negative initial errors, it can be guaranteed that the tracking error can converge to any small area according to the predetermined convergence speed, overshoot and steady-state error, meanwhile, Tracking error steady-state performance and transient performance constraints. In order to improve the robustness of the control system, a fuzzy controller is introduced to approximate the uncertainties in the dynamic model under the framework of the design of the inversion control. In order to avoid the problem of “differential expansion ” existing in traditional inversion methods, a sliding mode differentiator is introduced to accurately estimate the derivative of the virtual control volume. Finally, the effectiveness of the designed control system is verified by trajectory simulations with different initial errors.