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N_2O混合火箭发动机的催化点火研究 被引量：2

Experimental investigation on catalytic ignition of N_2O hybrid rocket motor
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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.
作者 万科 李路明 韦迪 霍雪亮
机构地区 清华大学宇航中心
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
关键词 混合推进剂火箭发动机 催化点火 再启动 Hybrid propellant rocket engine Catalytic ignition Restart
分类号 V436 [航空宇航科学与技术—航空宇航推进理论与工程]
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参考文献8

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二级参考文献13

  • 1Zakirov V A. Investigation into nitrous oxide propulsion option for small satellite applications [ D ]. Ph. D. Thesis, University of Surrey, England,2001.
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共引文献9

同被引文献14

引证文献2

二级引证文献7

推进技术
2007年 第1期

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