逆系统方法在飞行器直接侧力控制中的应用  

An Application of Inverse System Method to Direct Side Force Control

作　　者：陈检根 杨军[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《西北工业大学学报》2000年第1期152-155,共4页Journal of Northwestern Polytechnical University

摘　　要：根据逆系统的多输入多输出控制理论 ,包括多输入多输出系统逆的算法、反馈线性化控制律设计、状态可解耦条件 ,设计某飞行器直接侧力控制系统。计算机仿真表明 ,逆系统方法解耦能精确地实现运动模式 ,为解决直接侧力控制问题提供一种新的技术途径。A certain type of advanced vehicle requires decoupling control of flight altitude and flight trajectory. We adopted the decoupling control theory of inverse system to solve this problem. We first add a control rudder to provide direct side force. Eqs (14) and (15) give the dynamic model at Ma =0.82, h =3 000 m. Then we derived eqs.(16) and (17) as the decoupling control algorithm. Simulation results are given in Fig.1. the dotted curve is the results by linearized static decoupling (LSD) algorithm, and the solid curve, those by inverse system decoupling (ISD) algorithm. Fig.1(a), (b) and (c) show that the flight altitude and the flight trajectory are completely decoupled by the control system using ISD algorithm, and ISD algorithm is much better than LSD algorithm.

关 键 词：逆系统方法 解耦 直接侧力控制 飞行器 

分 类 号：V249.121[航空宇航科学与技术—飞行器设计] TJ765.2[兵器科学与技术—武器系统与运用工程]