返地航天器烧蚀炭和地面模拟烧蚀炭热物性和显微组织的对比研究  

A CONTRAST STUDIES ON OF THERMOPHYSICAL PROPERTIES AND MICROSTRUCTURE FOR THE ABLATION CARBON AT ENTRY SMCECRAFT AND THE CARBON ABLATED SIMULATIVELY IN LABORATORY

作　　者：奚同庚[1] 王圣妹[1] 章宗德[1] 陆燕静[1] 谢华清[1] 李明华[1] 吴清仁 

机构地区：[1]中国科学院上海硅酸盐研究所,华南理工大学无机材料系

出　　处：《空间科学学报》1996年第S1期47-52,共6页Chinese Journal of Space Science

基　　金：国家自然科学基金;上海自然科学基金

摘　　要：本文应用计算机运控的激光热导仪，对返地航天器烧蚀炭和地面模拟烧蚀炭的热物性和显微组织进行了对比分析和研究，从而提出了一个由地面模拟烧蚀炭层的热物性预测航天器烧蚀炭层热物性的新方法．Using a computerized Laser thermal conductivity measurement apparatus, a contrast analysis of thermophysical properties and microstructure for the ablation carbon at re-entry spacecraft and the carbon ablated simulatively in laboratory are studied, and consequently the new method for prediction of the thermophysical properties of ablation carbon at re-entry spacecraft from the thermophysical properties of carbon ablated in the laboratory is provided.

关 键 词：返地航天器 烧蚀炭 热物性 

分 类 号：P173.2[天文地球—天文学]