摘要
一、实验装置与方法 实验发动机采用分段式,段与段之间用法蓝盘连接(见图1)。用四个压力传感器测量各截面和头部的压力时间曲线。装药形状为内孔管状并带有后扩张锥。中止燃烧机构采用向发动机喷水的方法,在需要中止燃烧时,由微机控制时间,接通点火电源,点燃喷水装置的药包,燃气压力使活塞将水推入燃烧室,当水进入装药通道时,装药燃烧立即停止。 装药尺寸测量,采用测量显微镜.装药初始尺寸见表1。
A new apparatus for investigating the erosive characteristics of the nozzleless
solid propellant rocket motor by interruption of burning is presented. The erosive characteristics of HTPB composite propellant are obtained. The curves p-t computed with the erosive characterisitcs are compared with the experimental data. The experimental results show that the erosive characteristics of nozzleless rocket motors are similar to those of the rocket motor witha nozzle.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1989年第2期158-160,共3页
Journal of Aerospace Power
