基于QFT+DI的高超声速飞行器控制研究  

Control of Hypersonic Vehicle Based on QFT+DI

作　　者：王飞[1] 史震[1] 马文桥[1] 

机构地区：[1]哈尔滨工程大学自动化学院,黑龙江哈尔滨150001

出　　处：《计算机仿真》2013年第6期59-62,161,共5页Computer Simulation

基　　金：第二炮兵装备部预研:飞行性能仿真技术(103020101)

摘　　要：在高超声速飞行器控制研究中,大空域大马赫数飞行造成的强耦合、高度非线性,影响控制系统的稳定性。为解决上述问题,在传统定量反馈控制理论的基础上,提出定量反馈和动态逆相结合的鲁棒控制方法,对高超声速飞行器纵向模态进行控制器设计。利用动态逆对系统非线性模型进行反馈线性化,将得到的线性模型作为控制的内环和定量反馈设计模板,设计外环系统的控制器和前置滤波器。通过计算机对设计的控制器进行仿真验证,结果表明,控制设计方法具有较好的控制效果,且比传统的设计方法在高频段具有更好的噪声抑制能力。In order to resolve the control of hypersonic vehicle problem, there are strong coupling and highly non- linear problems because of large mach. A new control theory combination of quantitative feedback and dynamic inver- sion was proposed based on the traditional quantitative feedback control theory, and was used for controller design in the short - period vertical mode movement. The nonlinear model of hypersonic was linearized by dynamic inversion, the linear model as the inner loop and design templates was used for design of controller and prefilter. Simulation shows that the control design method is of better adaptability and robustness, and specially better suppression at high frequency than the traditional design methods.

关 键 词：定量反馈 动态逆 高超声速飞行器 非线性 

分 类 号：V411.8[航空宇航科学与技术—航空宇航推进理论与工程]