基于不同模型的固体火箭发动机喷射物熔渣特性分析  

Characteristic analysis of slags based on different solid rocket motor firing models

作　　者：彭科科[1] 庞宝君[1] 肖伟科[1] 韩志阳[1] 鞠芳菲[1] 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150080

出　　处：《航天器环境工程》2012年第6期616-620,共5页Spacecraft Environment Engineering

基　　金：国防科工局空间碎片专题项目(编号:KJSP08202;K020410-1/2);哈尔滨工业大学微小型航天器技术国防重点学科实验室开放基金(项目编号:HIT.KLOF.2009098)

摘　　要：固体火箭发动机喷射物中的熔渣是航天器防护和空间碎片风险评估关注的对象之一。文章首先介绍国外熔渣建模试验数据及理论模型,主要有NASA熔渣模型、MASTER2005熔渣子模型(以下简称MASTER模型)和麻省理工大学林肯实验室的MIT/LL熔渣模型;再利用NASA和MASTER模型分析熔渣尺寸-数量和质量特性。MASTER模型给出的熔渣数量和质量均低于NASA模型;且MASTER模型认为约91.8%的熔渣尺寸处于25～200 m区间;尺寸大于250 m的熔渣质量占熔渣总质量的88%,但其数量只占熔渣总数量的6.3%。以上研究结果为进一步分析熔渣对空间碎片环境的影响奠定了基础,对我国自主开展熔渣模型研究也有一定的参考价值。Ejected particles, especially slags, from solid rocket motors （SRMs） are an important issue in the risk assessment and the structural protection design of spacecraft. This paper reviews the development of SRM slag models： NASA Approach, MIT/LL Laboratory Approach, and MASTER2005 Slag Model. The number and the mass of slags obtained by the MASTER model are both lower than those of the NASA model, and according to the MASTER model, about 91.8% of the slags have a diameter in the range of 25～200 μm, but those with diameter larger than 250 μm account for 88% of the total mass and only 6.3% of the total number. According to these models, the number and mass distributions of slag debris can be analyzed to serve as a technical basis for further research on the space debris environment.

关 键 词：固体火箭发动机 喷射物 熔渣 空间碎片 数值分析 

分 类 号：TB24[一般工业技术—工程设计测绘] V411.8[航空宇航科学与技术—航空宇航推进理论与工程]