| 高燃速丁羟推进剂配方研究 |
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| 引用本文： | 谈景煜,杨可喜.高燃速丁羟推进剂配方研究[J].固体火箭技术,1993(3):59-64. |
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| 作者姓名： | 谈景煜 杨可喜 |
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| 作者单位： | 上海航天局806研究所，上海航天局806研究所，上海航天局806研究所，上海航天局806研究所 浙江湖州 313002，浙江湖州 313002，浙江湖州 313002，浙江湖州 313002 |
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| 摘 要： | 通过多种途径的试验,对高燃速丁羟推进剂配方进行了研究.试验结果表明,采用超细防结块氧化剂和液固组合燃速催化剂能使推进剂的燃速达到70mm/s以上(在6.864Mpa压强下);采用组合工艺助剂可改善推进剂工艺性能.本推进剂燃烧稳定,压强指数和温度敏感系数较低,力学性能良好,为高燃速推进剂的研制奠定了良好的基础.
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| 关 键 词： | 推进剂 燃烧催化剂 增塑剂 |
A Study of High Burning Rate HTPB Propellant Formulations |
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| Tan Jingyu Yang Kexi Dai Xianya Ding Faxiang.A Study of High Burning Rate HTPB Propellant Formulations[J].Journal of Solid Rocket Technology,1993(3):59-64. |
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| Authors: | Tan Jingyu Yang Kexi Dai Xianya Ding Faxiang |
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| Abstract: | High burning rate HTPB propellant formulations have been studied by means of various tests. The test results have shown that a propellant burning rate can reach more than 70mm/s (at a 6.864MPa pressure) by using a blocking proof ultrafine oxidizcr and a liquid-solid combined burning rate catalyst. In addition, a combined processing aid is adopted for improvement of processing properties. The propcllanl formulation developed features a stable combustion, low pressure exponent and temperature sensitivity coefficient and excellant mechanical properties, and has laid a good foundation for development of high burning rate propcllants. |
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| Keywords: | Subject Terms HTPB propcllant Burning rate catalyst Oxidizer Plasticizer |
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