摘要
针对无喷管发动机的工作特点,采用二维片型装药实验方案,对高燃速含铝丁羟复合推进剂做了相当数量的试验来研究其燃速特性.试验参数的选择应用正交设计法.在此试验的基础上,参照有关的燃烧理论,得出了适合无喷管发动机工作特点的固体推进剂的实际燃速表达式.
Concerned with the dynamic characteristic of nozzleless solid pro-pellant rocket motors,the two-dimensional grain plate was adopted in the experiment.The combustion characteristic of composite propellant HTPB/AP in a nozzleless rocket motor was investigated through amount of experiments.The experimental parameters were determined by orthogonal mothed.On the basis of these experiments and concerned combustion theories. An empiric formula of buring rate available to nozzleless rocket motor was obtained.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1990年第6期23-28,18,共7页
Journal of Propulsion Technology
关键词
无喷管
火箭发动机
推进剂
燃烧速度
Nozzleless rocket engine Propellant buring rate,Test Research
