环境温度对导弹发动机点火时机的影响及控制策略  

Influence of Ambient Temperature on Ignition Timing of Engine and Its Control Strategy

作　　者：肖沿海 

机构地区：[1]江南机电设计研究所,贵阳550009

出　　处：《火力与指挥控制》2017年第11期49-51,55,共4页Fire Control & Command Control

基　　金：国防装备预研基金资助项目(41101060103)

摘　　要：针对埋入式进气道在发动机点火时刻对导弹飞行攻角的严格限制,提出了攻角点火窗口的概念;以助推器在低温、常温和高温下的推力数据为基础,分别计算了导弹飞行攻角进入攻角点火窗口的时刻,并对时刻差异进行动力学分析;为消除环境温度变化对点火指令发出时机的影响,引入伪攻角信号,设计攻角控制律。半实物仿真结果表明,该控制方法能有效消除环境温度变化对导弹飞行攻角进入攻角点火窗口时刻的影响,且能够使导弹攻角在发动机点火过程中保持稳定,具有一定的工程实用价值。For the restrictions of attack angle on the ignition time of the submerged inlet of a engine, the concept of attack angle ignition window is presented. Based on the thrust data of the booster at low, normal and high temperature, the instant of the flight attack into the ignition window is calculated, and the dynamic analysis for the time difference is also performed. In order to eliminate the influence of environmental temperature on ignition timing, the pseudo angle signal is used to design the attack control law. The semi physical simulation results showed that this control method can effectively eliminate the influence of ambient temperature on the ignition time as the flight attack angle into the ignition window, and can make the attack angle remains stable in the ignition process, so it has a helpful engineering practical value.

关 键 词：埋入式进气道 伪攻角 攻角点火窗口 环境温度 

分 类 号：TJ414[兵器科学与技术—火炮、自动武器与弹药工程]