摘要
提出了固体火箭发动机绝热层烧蚀性能的试验评估方法，建立了在不同燃气参数和绝热层材料有缺陷条件下的烧蚀模型及烧蚀率经验公式，并对绝热层烧蚀率影响程度进行了分析，为绝热层设计提供了依据。
An experimental evaluation method for the insulation ablation in the solid rocket motor was proposed. An insulation model and experimental formula under different gas paramcnters and materials defects are built up and used for analyzing the effects of the insulation ablation rate. It can be taken as a basis of design.
出处
《固体火箭技术》
EI
CAS
CSCD
1995年第2期70-76,共7页
Journal of Solid Rocket Technology
关键词
固体推进剂
火箭发动机
隔热材料
烧蚀试验
Solid propellant rocket engine Thermal insulating material Ablation test
