冲压发动机导弹协调控制与总体设计一体化研究  

Research on the Integrated Control and System Design of Ramjet Missile

作　　者：郑书娥[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《战术导弹控制技术》2006年第4期50-52,共3页

摘　　要：分析了冲压发动机导弹设计过程中遇到的两个主要问题，通过分析原因确定了解决思路。最后，经过一体化设计，采用BTT＋STT的协调控制，将攻角限幅融入协调控制过程中，并采取剩余飞行时间门限强制进行协调控制。这样不仅解决了导弹飞行过程中的稳定与控制问题。确保冲压发动机正常工作，并解决了导弹飞行末端的快速性和机动性要求，可以使导弹获得最佳的总体性能。Two major questions confronted in the design of ramjet missile are researched and the method is found. At last, by means of integrated design of control and system, BTT/STT control is adopted in which the angle of attack is limited or unlimited on principle. Besides, a time-to-go valve is used to ensure BTT control into STT control. In this way, stable control is insured in missile flight and the ramjet can work well-balanced. And also short response time and high maneuver are insured so that the ramjet missile has the best system performance.

关 键 词：倾斜转弯控制 侧滑转弯控制 冲压发动机导弹 一体化 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]