固体火箭冲压发动机控制方案研究  

Research of Control Strategy for Ducted Rockets

作　　者：牛文玉[1] 刘顶新[1] 

机构地区：[1]北京动力机械研究所,北京100074

出　　处：《弹箭与制导学报》2016年第4期63-66,69,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：冲压发动机控制系统一般通过设置必要的限制函数来防止发动机出现不稳定工作状态,在尽可能大的范围内进行推力调节,从而使飞行器的性能较优。文中在分析固体火箭冲压发动机控制难点的基础上,对发动机转级之后的工作过程提出了4种控制方案,并进行了对比分析。文中研究内容可以为固体火箭冲压发动机控制方案的选择提供一定参考。By setting different margin limiting functions to prevent ramjet from operating in unacceptable regions, control system must permit thrust modulation in a range as wide as possible without exceeding these operating constraints so that overall vehicle performance can be optimized. In this article, control difficulties of ducted rocket were analyzed. Four control strategies for ducted rockets were presented and compared. The study can be used to provide reference for selecting control strategy of ducted rockets.

关 键 词：固体火箭冲压发动机 限制函数 控制方案 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]