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氧化剂粒度对复合固体推进剂侵蚀燃烧的影响
引用本文:利凤祥 陈景惠. 氧化剂粒度对复合固体推进剂侵蚀燃烧的影响[J]. 宇航学报, 1990, 0(1): 105-112
作者姓名:利凤祥 陈景惠
作者单位:西北工业大学,西北工业大学
摘    要:本文阐述了利用透明窗发动机——高速摄影装置研究氧化剂粒度对复合固体推进剂侵蚀燃烧影响的方法。对基本配方相同,只是氧化剂粒度不同的三种复合固体推进剂进行了实验研究。经过测试、分析和计算,得出了不同氧化剂粒度推进剂的侵蚀效应对气流速度和压力的关系式,进而得出了氧化剂粒度的大小对复合固体推进剂侵蚀效应的影响关系。

关 键 词:固体推进剂 侵蚀 燃烧 氧化剂 粒度

THE EXPERIMENTAL STUDY OF EFFECTS OF OXIDIZER PARTICLE SIZE IN COMPOSITE SOLID PROPELLANTS ON EROSIVE BURNING
Li Fengxiang. THE EXPERIMENTAL STUDY OF EFFECTS OF OXIDIZER PARTICLE SIZE IN COMPOSITE SOLID PROPELLANTS ON EROSIVE BURNING[J]. Journal of Astronautics, 1990, 0(1): 105-112
Authors:Li Fengxiang
Affiliation:Li Fengxiang (P. O. Box 169 Xian Shanxi Province)Chen Jinghui Ji Chenwu (Northwestern Polytechnical University)
Abstract:This paper deiinenated the method to study the effects of oxidizer particle site on erosive burning of composite sclid propellants by transparent plexiglass window motor-high-speed motion picture equipment. For three composite solid probellants whichthe fundamental formulation parameters are identical. but the oxidizer partical size ore different complited experimental study. By determination, analysis and colculation, derive d the relations of erosive burning sensitivity of composite propellants contained different oxidizer particle size versus crossflow velocity and pressure, as a conseguence, derived the relations of the erosive burning sensitivity of composite solid propellants.
Keywords:Composite solid propellant   Solid rocket   Engine erosive burning  Solid rocket oxidizer.
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