摘要
利用N2O催化分解原理，设计了一个用于启动N2O混合火箭发动机的催化点火器。试验表明，在催化剂被加热到400-600℃左右后，该点火器可以成功启动N2O／有机玻璃（PMMA）混合火箭发动机。在切断氧化剂供给，节流关闭发动机后，可以通过再次加热催化室重新实现发动机的启动，在节流时间较短的情况下也可以直接打开氧化剂阀门，利用催化室余热多次启动发动机。
An innovative igniter based on catalytic decomposition of N2O was designed and manufactured. A hybrid rocket motor using this igniter was tested. The experiment results demonstrated that this new igniter can successfully start the N2O/PMMA hybrid motor. The motor can be restarted either through re-heating the catalytic bed after shut off and cooling down or re-opening the oxidizer valve after throttling for a short time.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2007年第1期1-3,85,共4页
Journal of Propulsion Technology
