再入高超声速飞行器动力学建模与控制系统设计  

Research on Dynamic Modeling and Control System Design of Reentry Hypersonic Vehicles

作　　者：杨波[1] 李菁菁[1] 任章[1] 

机构地区：[1]北京航空航天大学,北京100191

出　　处：《系统仿真学报》2008年第S2期378-382,共5页Journal of System Simulation

摘　　要：为研究再入高超声速飞行器的特性,以某升力体再入高超声速飞行器为对象,建立了其再入段的六自由度动力学模型,并以风洞实验给出的气动数据,建立了气动数据查找模块,同时给出了模型不确定性分析。在仿真模型的基础上,给出了控制分配算法,并将对象划分为快慢回路,分别设计了动态逆控制器。最后,通过在Matlab/Simulink环境下对整个控制系统进行仿真。结果表明,动态逆控制器和控制分配算法组成的控制器基本实现了飞行器的姿态控制。To study the characteristics of reentry hypersonic vehicles,this paper establishes a six-degree-of-freedom dynamic model for its reentry phase basing on a lifting body reentry hypersonic vehicle;an aerodynamic coefficients look up module is also created with data from wind tunnel experiments.The model uncertainty is discussed thereafter.With such simulation model,a control allocation algorithm is introduced;dividing the plant into fast and slow loops,two dynamic inversion controller are designed separately.Finally,a simulation experiment is conducted for the whole control system under Matlab/Simulink.Result prove that the controller made up of dynamic inversion controller and control allocation algorithm meets the basic requirement of attitude control for the reentry hypersonic vehicle.

关 键 词：高超声速飞行器 再入 动力学建模 控制系统设计 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]