Ablative thermal protection systems
Ablative thermal protection systems
复制标题
烧蚀热防护系统
DOI：
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发表时间：
1983
期刊：
影响因子：
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通讯作者：
W. Dean
中科院分区：
文献类型：
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作者：
J. Vaniman;R. Fisher;C. Wojciechowski;W. Dean
讨论了航天飞机固体火箭助推器（SRB）部件热防护系统（TPS）的设计方法。对这种设计的适当性的最后评估将根据从头五次航天飞机飞行中获得的数据进行。温度传感器安装在TPS覆盖的SRB结构上的选定位置，提供整个飞行过程中随时间变化的信息。应调查异常情况，并在必要时调整计算机设计热模型。此外，在每次飞行后，要测量实际TPS烧蚀材料损失，并与分析确定的损失进行比较。综述了烧蚀材料性能预测的分析方法。
The procedures used to establish the TPS (thermal protection system) design of the SRB (solid rocket booster) element of the Space Shuttle vehicle are discussed. A final evaluation of the adequacy of this design will be made from data obtained from the first five Shuttle flights. Temperature sensors installed at selected locations on the SRB structure covered by the TPS give information as a function of time throughout the flight. Anomalies are to be investigated and computer design thermal models adjusted if required. In addition, the actual TPS ablator material loss is to be measured after each flight and compared with analytically determined losses. The analytical methods of predicting ablator performance are surveyed.