一种新型的固体火箭发动机体外点火器

推进技术 ›› 1994, Vol. 15 ›› Issue (5): 53-56.

一种新型的固体火箭发动机体外点火器

雷碧文,张为华,王荣祥

国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系

发布日期:2021-08-15

AN ADVANCED EXTERNAL IGNITER FOR SOLID ROCKET MOTORS

Department of Aerospace Technology, National University of Defense Technology, Changsha, 410073;Department of Aerospace Technology, National University of Defense Technology, Changsha, 410073;Department of Aerospace Technology, National University of Defense Technology, Changsha, 410073

Published:2021-08-15

摘要/Abstract

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。

关键词: Solid Propellant rocket engine;Rocket ignitor;Design requirement;ignition test

Abstract: 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.

Key words: Solid Propellant rocket engine;Rocket ignitor;Design requirement;ignition test

雷碧文,张为华,王荣祥. 一种新型的固体火箭发动机体外点火器[J]. 推进技术, 1994, 15(5): 53-56.