嵌金属丝端燃装药方案绝热层设计方法  

Method of Ablation Heat Shield Design of End-Burning Grain with Embedded Wire

作　　者：肖志斌[1] 王家鑫 王继 

机构地区：[1]中国人民解放军海军驻南京地区航天机电系统军事代表室,南京210006 [2]中华人民解放军海军驻上海地区航天系统军事代表室,上海201109 [3]上海航天动力技术研究所,上海201109

出　　处：《上海航天》2010年第2期61-64,共4页Aerospace Shanghai

摘　　要：根据固体火箭发动机绝热防护模型,提出了一种嵌金属丝端燃装药绝热层设计方法。用该法对某特定发动机燃烧室绝热层的设计结果表明:与动机原绝热层烧蚀相比,用本方法设计的绝热层可在绝热防护达到安全要求的同时,最大化地降低发动机消极质量。According to the thermal shielding model of solid rocket motor, an approach of ablation heat shield design of end-burning grain with embedded wire was put forward in this paper. The application of the method on the insulation of a certain SRM. Compared with the insulation erosion of the ablation heat shield designed previously, the results showed that the new insulation designed would mostly decrease the inert weight effectively while the safety protection wa ensured.

关 键 词：固体火箭发动机 绝热层 端面燃烧 嵌金属丝 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程]