超高燃速多孔推进剂发动机的点火特性

推进技术 ›› 1996, Vol. 17 ›› Issue (1): 54-57.

超高燃速多孔推进剂发动机的点火特性

李兆民,周生国,王春利,张训文,刘玉群

北京理工大学飞行器工程系;北京理工大学飞行器工程系;北京理工大学飞行器工程系;北京理工大学飞行器工程系;北京理工大学飞行器工程系

发布日期:2021-08-15

IGNITION CHARACTERISTICS OF SOLD ROCKET MOTORS WITH ULTRA-HIGH BURNNING RATE POROUS PROPELLANTS

Dept. of Flight Vehicle Engineering, Beijing Inst. of Technology, Beijing, 100081;Dept. of Flight Vehicle Engineering, Beijing Inst. of Technology, Beijing, 100081;Dept. of Flight Vehicle Engineering, Beijing Inst. of Technology, Beijing, 100081;Dept. of Flight Vehicle Engineering, Beijing Inst. of Technology, Beijing, 100081;Dept. of Flight Vehicle Engineering, Beijing Inst. of Technology, Beijing, 100081

Published:2021-08-15

摘要/Abstract

摘要： 超高燃烧多孔推进剂比常规推进剂点火困难，需要合理调整影响点火性能的参数。研究了推进剂密度、点火空间、喷喉尺寸、喷管堵盖材料和厚度、点火药量和种类对超高燃速推进剂发动机点火特性的影响，并确定了关键因素，得到了良好的综合点火性能。

关键词: 固体推进剂火箭发动机;高燃速推进剂;点火试验

Abstract: n solid propellants,the porous solid propellants with ultra-high burning rate are greatly different from general solid propellants in burning mechanism. The ignition of porous solid propellants with ultra-high burning rate are more difficult than that of general solid propellants. So long asthe parameters concerning igniting performance should be selected properly. When propellant density,ignition space and nozzle throat size are determined, the key factors to affect ignition are the weightand the type of igniter’s charges, the material and the thickness of nozzle closures. The concerned experimental results for igniting research on porous solid propellants with ultra-high burning rate are also given in this paper.

Key words: Solid propellant rocket engine;High burning rate propellant;Ignition test

李兆民,周生国,王春利,张训文,刘玉群. 超高燃速多孔推进剂发动机的点火特性[J]. 推进技术, 1996, 17(1): 54-57.