摘要
针对一种自由装填固体火箭发动机的快烤响应特性进行了试验研究,搭建了固体火箭发动机的快烤试验平台,进行了自由装填固体火箭发动机的快烤试验,并对被试发动机的快烤试验过程和试验结果进行了分析。通过被试发动机快烤试验过程的分析,获得了被试发动机的分阶响应特性和各阶段的响应时间。结果表明,被试发动机的响应过程可划分为两次响应和三个阶段,两次响应分别为发动机点火和发动机解体,三个阶段依次为温度建立阶段、第一响应阶段和第二响应阶段。通过对被试发动机的解体过程和剩余装药残骸的分析,获得被试发动机的解体机理。结果表明,在外部加热的持续作用下,装药头部的推进剂来不及燃烧,在自分解作用下发生了装药结构破坏并点燃,导致装药燃面增大,发动机压强上升,最终导致发动机解体。
In order to obtain the response characteristics of a free loading solid rocket motor to fast cook off,an experimental study was carried out.A fast cook off test platform was first built,based on which the fast cook off test of free loading solid rocket motor was carried out.The test processes and results of these fast cook off tests have been analyzed.Through the analysis of fast cook off test,step by step response characteristics of the tested motor and response time of each phase were obtained.The results show that response process of a charged motor can be divided into two step responses with three phases.Two step responses are identified as ignition and disintegration,respectively.Three phases are the temperature establishment phase,the first response phase and the sec ond response phase,respectively.Through the analysis of disintegration process,remaining charge and wreckage,the fast cook off fail ure mechanism of tested motor has been obtained.The results show that,under the continuous action of external heating,propellant first underwent pyrolysis,resulting in charge collapse and ignition,which leads to an increase in burning surface.Then pressure of tested motor rises,which eventually causes the tested motor to disintegrate.
作者
颜密
田小涛
王绍增
陈俊屹
汤祥
黄萌
YAN Mi;TIAN Xiaotao;WANG Shaozeng;CHEN Junyi;TANG Xiang;HUANG Meng(Xi’an Modern Control Technology Research Institute,Xi’an 710065,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2020年第1期95-100,共6页
Journal of Solid Rocket Technology
关键词
自由装填固体火箭发动机
快烤试验
响应特性
失效机制
free loading solid rocket motor
fast cook off test
response characteristics
failure mechanism
