摘要
提出了一种新的膏体推进剂脉冲火箭发动机设计方案及其再点火装置的设计与实现，建立了膏体推进剂在再点火装置中二维流动模型和传热模型，得到了发动机可靠点火时再点火装置温度、长度、通道直径和挤压压强间应满足的关系，以及发动机熄火应满足的条件，还进行了原理性热试车，成功实现了多脉冲工作。
A new method for multi pulse pasty propellant rocket motor design was proposed by analyzing flow,heat transfer,ignition,combustion and extinction of a non Newtonian pasty propellant,in which the oxidizer and fuel were mixed uniformly.The key technology of the new method was the design of a re ignitable igniter.The two dimensional flow and heat transfer models of the propellant inside the re ignitable igniter were established and the control equations were solved numerically.The relationship among the igniter temperature,igniter length,diameter and drive pressure gradient for the reliable ignition and extinction were obtained.The variation of combustion chamber temperature was analyzed to determine time interval between two performances.A set of demonstration proto type test apparatus were also built for multi pulse firing.Some seven work pulses were obtained.Each pulse lasted about five seconds and the time interval of each pulse was about two seconds.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1999年第1期1-5,共5页
Journal of Propulsion Technology
基金
国家自然科学基金
关键词
脉冲式
火箭发动机
触变推进剂
胶凝推进剂
Impulse rocket motor,Thixotropic propellant rocket engine,Reignition,Gelled propellant
