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.
出处
《上海航天》
2010年第2期61-64,共4页
Aerospace Shanghai
