导弹发射车主动油气悬架反馈线性化控制  

Feedback Linearization Control for Missile Launch Vehicle Active Hydropneumatic Suspension

作　　者：史俊武[1] 李小伟[1] 张建武[1] 

机构地区：[1]上海交通大学机械与动力工程学院,机械系统与振动国家重点试验室,上海200240

出　　处：《系统仿真学报》2009年第23期7617-7621,7639,共6页Journal of System Simulation

摘　　要：为满足导弹行进间发射的特殊工况要求,提出了导弹发射车主动油气悬架系统新型控制策略。从导弹发射车用油气弹簧模型建立与实验验证出发,建立了主动油气悬架系统非线性模型。应用微分几何理论,通过微分同胚的变换与非线性状态反馈将原非线性系统进行全局精确线性化,并针对其设计线性最优控制算法。仿真结果表明,这种针对非线性系统的控制策略具有算法设计简单、控制效果良好等特点。Missile mobile launching technology has become more and more important in development of advanced weapon system with more enhanced mobile and survival capabilities.To fulfill the special requirement of mobile launch,a new control strategy for the missile launch vehicle active hydropneumatic suspensions was proposed.After modeling and experimental validation of the hydropneumatic spring,a nonlinear dynamic system model of the missile launch vehicle active hydropneumatic suspension was established.Based on the differential geometry theory,the nonlinear system was transformed to a linear one by means of homeomorphic transformation and nonlinear state feedback.Furthermore,a linear optimal（LQG） control approach was applied for the solution to the system of equations.The simulation results indicate that the present nonlinear controller is characterized by its simple structure and good performance.

关 键 词：油气弹簧 微分几何 反馈线性化 线性最优控制 

分 类 号：U463[机械工程—车辆工程]