Study on Ignition and Burning Propagation of Rocket-Engine of Extended Range Projectiles
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摘要:为使增程炮弹火箭发动机可靠、平稳工作，提出了一种后置射流点火具（锆系药）点燃前置射流点火具（锆系药）的点传火技术，进行了点传火系统总体、前置射流点火具、后置射流点火具、点火、传火及装药设计，进行了点火具射流长度、射流时间、射流流量、静态、动态及点传火系统P——t曲线等对比测试。试验结果表明：射流点火具（锆系药）具有输出性能稳定、射流流量较大的射流点火特性，在点传火系统中能使前置射流点火具（锆系药）迅速稳定建压，输出较大、稳定的射流流量，使火箭发动机稳定工作。
Abstract:Aimed at the reliable and steady function of rocket engine, a kind of ignition and burning propagation technology based on jet igniter(charged Zr powder) was proposed, the whole system, propositive jet igniter, postpositive jet igniter, ignition, burning propagation and charge were designed, the tests of jet length, jet time, jet flow, static, dynamic, and P——t curves were also carried out. The results showed that the output performance of jet igniter(charged Zr powder) is stable, and has large jet flow, in the ignition and burning propogation system, the pressure of propositive jet igniter(charged Zr powder) can be established quickly, and has stable large jet flow, which would make the rocket engine work steadily.
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