摘要
为了提高固体发动机工作可靠性，增加装药质量，同时实现二级点火和级间分离，应用体外点火器是一种成功的方法。本文给出了此种点火器的设计方法。其设计特点为：点火器装于喷喉之后，喷焰长度由经验公式预估，装药设计和内弹道计算一并完成。实践证明本文提供的方法能满足工程设计需要。
In order to improve working reliability, increase grain mass, and achieve ignition and stage separation at the same time, a successful method is to apply an external igniter to solid rocket motor. In this paper, the design method of the igniter is described. its features are as follows: the igniter is positioned at divergent section of the nozzle and out of the solid rocket motor. The flame length is predicted by semi-empirical formula. The grain configuration and grain mass are determined by internal ballistic prediction program. It is shown that the design method is satisfied for engineering design and has greater spreading value. The igniter has been used in real rocket motor. Compared with normal igniter, the external igniter is safer and more reliable.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1994年第5期53-56,共4页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
点火器
点火试验
Solid Propellant rocket engine
Rocket ignitor
Design requirement
ignition test
