摘要
分析了固体发动机试验点火控制电路及其三个主要环节:交流继电器、电磁继电器及引线。后者为长约300m的导线,模拟研究表明,在点火瞬间及点火前预调点火电流时,引线会产生自感电压对线路产生干扰。研究了提高时序控制精度、点火可靠性及电路安全性的途径。
This paper analyzes the ignition control circuit for solid rocket motor ground tests and its three main parts: AC relay, electromagnetic relay and lead wire. The latter is about 300 m in length. Simulation shows that the lead wire could produce a self-reduction voltage to interfere the circuit during ignition and in pre-setting ignition current before firing. The measures for improving the sequence control accuracy, ignition reliability and circuit safety are researched.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2002年第4期67-70,共4页
Journal of Solid Rocket Technology
关键词
发动机
地面试验
时序控制
点火试验
solid propellant rocket engine
ground test
ignition circuit
sequential control
