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首页> 外文期刊>Defence Science Journal >Design and Testing of Lab-scale Red Fuming Nitric Acid/Hydroxyl-terminated Polybutadiene Hybrid Rocket Motor for Studying Regression Rate
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Design and Testing of Lab-scale Red Fuming Nitric Acid/Hydroxyl-terminated Polybutadiene Hybrid Rocket Motor for Studying Regression Rate

机译:用于研究回归速率的实验室规模的红色发烟硝酸/羟基封端的聚丁二烯混合火箭发动机的设计和测试

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摘要

This paper presents the design of a hybrid rocket motor and the experiments carried out for investigation of hybrid combustion and regression rates for a combination of liquid oxidiser red fuming nitric acid with solid fuel hydroxyl-terminated Polybutadiene. The regression rate is enhanced with the addition of small quantity of solid oxidiser ammonium perchlorate in the fuel. The characteristics of the combustion products were calculated using the NASA CEA Code and were used in a ballistic code developed for predicting the performance of the hybrid rocket motor. A lab-scale motor was designed and the oxidiser mass flow requirements of the hybrid motor for the above combination of fuel and oxidiser have been calculated using the developed ballistic code. A static rocket motor testing facility has been realised for conducting the hybrid experiments. A series of tests were conducted and proper ignition with stable combustion in the hybrid mode has been established. The regression rate correlations were obtained as a function of the oxidiser mass flux and chamber pressure from the experiments for the various combinations.
机译:本文介绍了一种混合火箭发动机的设计,并进行了研究,以研究液体氧化剂红发烟硝酸与固体燃料羟基封端的聚丁二烯的混合燃烧和回归速率。通过在燃料中添加少量的固体氧化剂高氯酸铵,可以提高回归速度。燃烧产物的特性是使用NASA CEA编码计算的,并已在弹道编码中使用,用于预测混合火箭发动机的性能。设计了实验室规模的电动机,并使用开发的弹道代码计算了混合燃料对上述燃料和氧化剂组合的氧化剂质量流量要求。已经实现了用于进行混合实验的静态火箭发动机测试设备。进行了一系列测试,并在混合模式下建立了具有稳定燃烧的正确点火装置。从各种组合的实验中获得的回归速率相关性是氧化剂质量通量和腔室压力的函数。

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