DESIGN AND DEVELOPMENT OF A HYDROGEN-PEROXIDE ROCKET-ENGINE FACILITY
DESIGN AND DEVELOPMENT OF A HYDROGEN-PEROXIDE ROCKET-ENGINE FACILITY
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发表时间：
2002-10
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通讯作者：
S. Krishnan;Ahn Sang Hee;Lee Choong Won
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作者：
S. Krishnan;Ahn Sang Hee;Lee Choong Won
简要综述了过氧化氢在推进中的应用研究进展。对一台推力为100N的过氧化氢单组元发动机进行了详细的设计研究。为了制备浓缩双氧水，已经实现了蒸馏装置。给出了水模拟试验结果。最初使用浓缩过氧化氢的点火并不成功。认为环境温度低、催化剂组件接触面积小、过氧化氢污染等是造成该反应的原因。解决前两点问题导致火箭发动机成功发射。
The ongoing developmental studies on the application of hydrogen peroxide for propulsion are briefly reviewed. A detailed design-study of a laboratory scale hydrogen peroxide mono-propellant engine of 100 N thrust is presented. For the preparation of concentrated hydrogen peroxide, a distillation facility has been realised. Results of water analogy tests are presented. Initial firings using the concentrated hydrogen peroxide were not successful. Low environmental temperature, low contact area of the catalyst pack, and contamination in the hydrogen peroxide were considered to be the reasons. Addressing the first two points resulted in successful firing of the rocket engine.