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在执行机构饱和约束下,针对机动滑翔飞行器高空横侧向大机动姿态控制问题,研究了在保证系统稳定的同时提高响应快速性方法.在标准Antiwindup方法中,误差收敛速率往往被忽略,系统快速性常常达不到设计要求.为了提高加入补偿后系统的误差收敛速率,对现存的一种基于线性矩阵不等式的Antiwindup设计方法进行改进,并运用比较原理证明了改进后受控闭环系统稳定且李雅普诺夫函数收敛速率有确定的下界,从而保证了误差收敛速率下界.与以往方法相比,该方法保证了对系统快速性的最低要求,为解决饱和系统稳定性与快速性的矛盾提供了一条有效途径.较大侧滑角下的倾侧角机动仿真结果表明,所设计的抗饱和控制器可以在恶劣的飞行环境下稳定完成倾侧角大机动的任务,相比于标准Antiwindup设计方法,该方法快速性有所提高.
Under the constraint of actuator saturation, aiming at the maneuvering attitude control problem of maneuver gliding aircraft at high altitudes, this paper studies the method to improve the response fastness while ensuring the stability of the system.In the standard Antiwindup method, the error convergence rate is often neglected and the system is fast In order to improve the error convergence rate of the system after adding compensation, an existing Antiwindup design method based on linear matrix inequality is improved and the principle of comparison is used to prove that the improved closed-loop control system is stable and Lyapun The lower bound of the convergence rate of Novo function is guaranteed, which guarantees the lower bound of the rate of error convergence.Compared with the previous methods, the proposed method guarantees the minimum requirements for the rapidity of the system and provides a solution to the conflict between the stability and the rapidity of the saturated system The effective approach.The tilting angle maneuvering simulation results show that the designed anti-saturation controller can stably accomplish the maneuvering task of tilting angle in harsh flight environment. Compared with the standard Antiwindup design method, this method Speed has improved.