固体火箭冲压发动机补燃室梯度热防护体系研究  

Research on Thermal Protecting of Afterburning Chamber for Integral Solid Rocket-ramjet

作　　者：刘亚东[1] 孙振华[1] 周磊[1] 王希亮[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《弹箭与制导学报》2009年第2期166-168,173,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了解决固体火箭冲压发动机补燃室长时间热防护问题,展开了补燃室梯度热防护系统研究,建立了梯度隔热的热防护方案,计算了各项热流密度。计算考虑以下传热过程:燃气通过辐射、对流的方式将热量传给硬质层,硬质层通过热传导的形式传给柔性梯度隔热层、壳体,最后以自由对流和辐射换热的方式将热量传递给周围空气和环境。分析了各隔热层厚度分配对于壁面温度的影响,设计了梯度隔热燃烧室,并进行了直连式试验,测试结果满足发动机总体要求。试验和计算结果证明梯度隔热方案满足热防护要求。The graded protecting system was researched to resolve the problem of long-playing heat protecting of the afterhurning chamber for integral solid roeket-ramjet, the protecting project was founded and the heat flux was calculated. The calculate considered the process of the heat transfer： from the gas to the rigid tier by radiation and convection, and than to the flexible graded insulation tier, to the ease, and ultimately to air with radiation and convection. The effect of the insulation tier thickness distribution on the ease temperature was investigated. The combustor with graded insulation tier were designed and the direct-connect testing was carried out, the result shown that the design met the requirement of the ramjet. The experiment and the result approved that the protecting project is content the requirment.

关 键 词：固体火箭冲压发动机 传热 梯度隔热 直连式试验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]