某低燃速推进剂侵蚀燃烧模型研究  

Erosive Burning Model Identification of a Propellant with Low Burning Rate

作　　者：杨瑄[1] 赵东民[1] 余贞勇[1] 

机构地区：[1]中国航天科技集团公司第四研究院第四十一所,西安710025

出　　处：《宇航学报》2008年第6期1932-1935,共4页Journal of Astronautics

摘　　要：推进剂的侵蚀燃烧对发动机的内弹道性能会产生不利影响,侵蚀燃烧的程度取决于药型设计的通气参数。设计了一种侵蚀燃烧试验发动机,并在不同通气参数情况下,进行了多发某低燃速推进剂侵蚀燃烧试验,通过对试验数据的数值分析,得到了该低燃速推进剂侵蚀燃烧的临界流速、侵蚀常数与燃通比之间的关系,并对此进行了试验验证,为类似推进剂药柱通气参数的选择提供参考。The erosive burning of the propellant is usually detrimental to the inner ballistic trajectory characteristic of the engine. The extension of the erosive burning is dominated by the ventilated parameters of the grain confignration designed. An engine is designed to fulfill erosive burning tests in this paper. For one target type of propellant, several erosive burning tests are carried out under conditions of different ventilated parameters. And based on the test results, the relationship between the parameters of the erosive burning, such as critical flow velocity, erosive burning constant, ratio of burning area and ventilated area, is simulated numerically. The relationship obtained numerically is verified in good agreement with that of practical test. The result analysis may probably provide some theoretical bases for the ventilated parameters design of the homologous propellants.

关 键 词：推进剂 侵蚀燃烧 模型 试验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]