烧蚀防热是靠烧蚀材料受热分解和氧化燃烧带走热量的防热方法，是返回式航天器、再入导弹弹头和火箭发动机内壁常用的一种防热方法。
... ablative degradation 烧蚀破坏 ablative heat protection 烧蚀防热 ablative leading edge 烧蚀前缘 ...
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介绍弹道式再入航天器烧蚀防热结构设计，文中说明了方案、材料选择、设计和分析计算。
This paper introduces ablative thermal protection structure design of a return module of some satellites.
采用在防热套内层增加隔热功能层的方法，在保持传统防热套良好烧蚀性能的同时，其隔热性能得到了较大地提高。
A method that adding an insulating functional layer to the interior of the heatshield is adopted to improve its insulation performances while maintaining its original excellent ablative performances.
对航天飞行器防热部件在氧煤油发动机火焰喷吹下的烧蚀行为进行了有限元数值模拟。
The ablation behavior of spacecraft thermo-resistance components under blowing by oxygen-kerosene flame is investigated by means of finite element numerical simulation.
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