基于模糊策略的高速飞行器滑模控制律设计  

The Design of Sliding Mode Control Law Based on Fuzzy Strategy for Hypersonic Vehicle

作　　者：王健[1] 杜庆余[1] 

机构地区：[1]北京航天自动控制研究所,北京100854

出　　处：《航天控制》2011年第4期49-54,65,共7页Aerospace Control

基　　金：国家自然科学基金项目(91016004--近空间高超声速飞行器智能自主控制研究)资助

摘　　要：以通用高超声速飞行器GHV为研究对象,针对其俯仰通道设计了具有良好鲁棒性的飞行控制系统。为了便于应用滑模控制理论,对该模型进行了输入输出反馈线性化,将其转换成仿射型。鉴于鲁棒性与抖振的矛盾,基于指数趋近律完成了滑模控制律结构设计,进而采用了模糊控制理论改进指数趋近律。基于遗传算法完成了所有控制参数的设计,确定了模糊逻辑控制规则。通过仿真比较了指数趋近律和模糊趋近律,结果表明,该方法可以同时满足飞行控制系统鲁棒性和参数优化过程收敛性的要求。According to the six DOF nonlinear model of the pitching channel of the generic hypersonic vehicle GHV, two sliding mode control laws are presented, which are based on the index reaching law and the fuzzy reaching law respectively. By taking advantage of the sliding mode control theory, the six DOF model is transformed into an affine system through input-output feedback linearization. To make the com- promise between robustness and chattering, the structure of sliding mode control law based on the index reaching law is designed, which is improved by adopting fuzzy control theory. Then all of the control pa- rameters based on genetic algorithm are optimized, therefore the fuzzy logic control rules are confirmed. The performance of index reaching law and fuzzy reaching law are compared through simulation. The results show that the method is able to meet the requirements of both the robustness of flight control system and the convergence of parameter optimization process.

关 键 词：高超声速 反馈线性化 滑模控制 模糊控制 遗传算法 

分 类 号：TP273.4[自动化与计算机技术—检测技术与自动化装置]