面向控制的固冲发动机建模技术研究  

Research on Solid Ducted Rocket Modeling for Control

作　　者：宋少倩 陈新民[1] 卢鑫[1] 刘娟[1] 韩英宏[1] Song Shao-qian;Chen Xin-min;Lu Xin;Liu Juan;Han Ying-hong(China Academy of Launch Vehicle Technology, Beijing, 100076)

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《导弹与航天运载技术》2018年第6期38-42,共5页Missiles and Space Vehicles

摘　　要：为实现导弹速度的精确控制,从控制系统设计与仿真需求角度出发,提出了一种降低动力与导弹总体参数、环境耦合的稳态性能建模方法和利于工程设计用的固冲发动机动态特性建模方法,分析获得了其慢响应和非最小相位的特点。仿真对比表明:采用动态特性建模方法建立的模型可用于速度控制的设计、分析与仿真。In order to achieve precise control of missile speed,A steady state modeling method is proposed to reduce the coupling between rocket and environment and a dynamic modeling method for engineering use from the point of view of control system design and simulation requirements.The slow response and non-minimum phase characteristics of solid ramjet is pointed out.Finally the simulation results show that the method proposed in this paper is feasible.

关 键 词：固体冲压发动机 稳态性能 动态性能 线性变参数 

分 类 号：V434.34[航空宇航科学与技术—航空宇航推进理论与工程]