基于分叉理论的变体飞行器稳定性分析及控制器设计  

Stability analysis of morphing aircraft based on bifurcation methodology and controller design

作　　者：吴志琪[1] 董朝阳[1] 贾臻[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《沈阳航空航天大学学报》2015年第1期32-37,共6页Journal of Shenyang Aerospace University

基　　金：国家自然科学基金资助项目(项目编号:61273083;61074027)

摘　　要：研究了变体飞行器飞行过程中稳定性边界确定及控制器设计问题。运用虚位移原理推导出变体飞行器非线性动力学模型,并进行解耦得到纵向动力学方程;将其转化为以后掠角变形率为时变参数的系统,通过分叉原理讨论变体飞行器的稳定性边界。设计了一个分数阶PIλDμ稳定控制器,利用改进的粒子群算法优化控制器参数。仿真结果表明,与传统PID控制器相比,分数阶PIλDμ控制器具有更好的控制性能。The purpose of this paper is to explore the boundary determination of stability and the design of controller. Firstly, the nonlinear dynamic model of morphing aircraft is derived based on the principle of virtual displacement, and the longitudinal dynamic equation is obtained by the separation. Then it is changed to a system with the function of deformation. The stability boundary is discussed by the bifurcation methodology and a fractional order PI^λD^μ controller is designed. The parameters are optimized with the modified particle swarm optimization algorithm. The result of simulations shows that the fractional order PI^λD^μcontroller demonstrates a better performance than traditional PID controller.

关 键 词：分叉理论 稳定性分析 分数阶PI^ΛD^Μ控制器 

分 类 号：V249.121[航空宇航科学与技术—飞行器设计]