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针对于吸气式高超声速飞行器开环不稳定的动力学特性,研究了控制信号存在饱和约束及带宽限制条件下的闭环稳定边界.首先,简要介绍了吸气式高超声速飞行器的建模方法与动力学特性的主要问题.考虑到飞行器控制信号的幅值限制及带宽约束,综合高超声速飞行器的开环不稳定特性,定量地分析了系统的闭环稳定边界:与系统不稳定极点的位置,其对应的左特征向量及控制信号的幅值约束有关;执行器的带宽限制在此基础上进一步缩小了反馈控制系统的稳定边界.根据高超声速飞行器短周期不稳定特性,解析地给出了闭环稳定边界的计算公式.采用蒙特卡洛分析方法对闭环系统的稳定边界及滑模变结构控制器作用下的稳定区域进行验证.仿真结果与理论分析具有一致性,验证了系统开环特性对于闭环稳定性的限制及控制信号带宽约束对稳定性的影响.
In view of the dynamic characteristics of the open-loop instability of the aspirated hypersonic vehicle, the closed-loop stability boundary of the control signal under the saturation constraint and the bandwidth constraint is studied.Firstly, the modeling methods of the aspirated hypersonic vehicle are briefly introduced. Considering the amplitude control and bandwidth constraints of the aircraft control signals, the open-loop instability characteristics of the hypersonic vehicle are analyzed, and the closed-loop stability boundary of the system is quantitatively analyzed: the position of the unstable poles of the system and its position And the corresponding left eigenvector is related to the amplitude control of the control signal.On the basis of the limit of the actuator’s bandwidth, the stability boundary of the feedback control system is further reduced.According to the short-period instability characteristics of the hypersonic vehicle, the closed-loop stability The boundary of which is calculated.The Monte Carlo method is used to verify the stability of the closed-loop system and the stability of the system under the sliding mode variable structure controller.The simulation results are consistent with the theoretical analysis to verify that the open- The impact of constraints and control signal bandwidth constraints on stability.