作　　者： ; ; ;

机构地区： 西北工业大学航天学院精确制导与控制研究所

出　　处： 《计算机仿真》 2012年第4期72-75,233,共5页

摘　　要： 关于飞行器稳定性优化控制问题,由于近空间无尾飞行器具有典型的通道间强耦合且多个操纵面介入单个通道控制,执行机构的复杂化和非线性导致控制系统设计实时性和响应性差,精度达不到要求。为提高姿态控制器控制精度,减小力矩分配误差,提出通过解耦控制系统和控制分配逻辑来分别解决对象的耦合和多操纵面的力矩分配问题。通过将动态逆设计方法与变结构控制理论相结合,设计了一种强鲁棒性的解耦控制律,并在加权伪逆算法的基础上,提出采用舵面偏角修正操纵面的效率矩阵,从而实现了强耦合非线性对象的高精度控制。仿真结果表明,控制器解耦效果良好且具有较强鲁棒性,控制分配算法减小了80%力矩分配误差,满足了飞行器的控制需求。 Compared with conventional aircraft,the tailless near-space vehicle has strong coupling between channels and multiple control surfaces involved in single channel,and the complication and nonlinearity of actuators make it difficult to design the control system.In order to improve the controlling accuracy and reduce the moment error of allocation,the coupling and allocation problems were solved with the decoupling control system and control allocation logic respectively.The robust decoupling control law was designed by applying dynamic inversion and variable structure theory,and base on the WPI,control surface deflection was used to modify the control efficiency matrix which achieved the high accuracy control of the strong coupling nonlinear object.The simulation indicates that the controller is qualified with excellent decoupling and better robustness and the control allocation algorithm achieves 80% error reduction,both of which effectively realize the vehicle＇s control requirement.

关 键 词： 无尾飞行器 解耦控制 控制分配 舵效修正

领　　域： [航空宇航科学与技术] [航空宇航科学技术]