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根据高超声速滑翔飞行器的任务和特点,并考虑一阶执行器动态,建立了面向控制系统设计的飞行器姿态模型.针对模型的结构,结合分散控制和滑模变结构控制的思想设计了再入飞行段的分散鲁棒姿态控制器:采用Tornambe控制方法进行了分散鲁棒滑模面的设计,使得系统能够克服耦合及非匹配不确定性的影响实现性能优良的滑模运动;采用改进的时间次优控制方法实现了二阶滑模变结构控制律的设计,通过在线估计等效控制削弱了抖振.为验证控制器的设计,在Simulink中以某概念高超声速滑翔飞行器为对象,进行了分散鲁棒姿态控制系统和制导系统的联合仿真,仿真结果表明在存在大不确定性的情况下,可以实现对制导指令的鲁棒稳定跟踪.
According to the missions and characteristics of hypersonic gliding aircraft and considering the dynamics of the first order actuator, an attitude model of the aircraft facing the design of the control system is established.According to the structure of the model, combined with the idea of decentralized control and sliding mode variable structure control, The decentralized robust attitude controller of a segment is designed by using the Tornambe control method, which enables the system to overcome the influence of coupling and unmatched uncertainties to achieve excellent sliding mode motion. The improved time-series The optimal control method realizes the design of the second order sliding mode variable structure control law and weakens the chattering through the equivalent control of on-line estimation.In order to verify the design of the controller, some concept hypersonic gliding aircraft are distributed in Simulink Robust attitude control system and guidance system co-simulation, the simulation results show that in the presence of large uncertainties, it can achieve robust and stable guidance of guidance instructions.