文章摘要
引用本文:吴大方, 王峰, 任浩源, 朱芳卉.航天器热防护材料不同边界条件下的隔热性能试验研究[J].航天器环境工程,2018,35(4):315-322 本文二维码信息
二维码(扫一下试试看!)
航天器热防护材料不同边界条件下的隔热性能试验研究
Experimental research of thermal insulation performance of thermal protection materials for spacecraft under different boundary conditions
投稿时间:2018-05-28  修订日期:2018-07-30
DOI:10.3969/j.issn.1673-1379.2018.04.002
中文关键词:  高超声速飞行器  高温  轻质陶瓷材料  隔热性能  试验测试  数值模拟
English Keywords:hypersonic vehicles  high temperature  light-weight ceramic material  thermal insulation  experimental test  numerical simulation
基金项目:
作者单位
吴大方, 王峰, 任浩源, 朱芳卉 北京航空航天大学 航空科学与工程学院, 北京 100191 
摘要点击次数: 607
全文下载次数: 816
中文摘要:
      通过试验检测热防护材料或结构的隔热能力是航天器与高超声速飞行器安全可靠性设计中不可缺少的重要环节。为获知隔热性能试验中3种不同边界条件下(试验件竖直放置,水平放置散热面向下,水平放置散热面向上)平板试验件散热面温度的差异,建立3种热试验装置,对轻质隔热材料进行不同温度条件下的隔热性能试验测试(散热面敞开)。试验结果表明:试验件水平放置散热面向下时的散热面温度最高;水平放置散热面向上时的散热面温度最低。当热面温度为1000℃时,1800 s后,水平放置散热面向下比水平放置散热面向上时的散热面温度高19.7%;试验件竖直放置比水平放置散热面向下时的散热面温度低2.3%。数值模拟结果与试验结果一致性良好,验证了试验结果的可信性和正确性。研究结果可为航天器与高速飞行器热防护系统设计及试验方案的确定提供重要参考依据。
English Summary:
      The thermal insulation performance of thermal protection materials or structures is an indispensable and important factor in the safety and reliability design of spacecraft and high speed flight vehicles. To obtain the temperature difference of the radiating surface for plate specimens under three different boundary conditions in heat insulation experiments (with the specimens placed either vertically or horizontally with respect to the radiating surface facing down or horizontally with respect to the radiating surface facing up), three thermal test setups are established to test the thermal insulation performance of light-weight ceramic specimens at different temperatures (with the radiating surface open). It is shown that the radiating surface temperature is the highest when the specimen is placed horizontally with the radiating surface facing down, while it is the lowest when the specimen is placed horizontally with respect to the radiating surface facing up. When the heating surface temperature is 1000℃ and the time is 1800 s, the radiating surface temperature of the horizontally placed specimen with the radiating surface facing down was 19.7% higher than that of the specimen horizontally placed with respect to the radiating surface facing up; The radiating surface temperature of the vertically placed specimen is 2.3% lower than that of the horizontally placed specimen with respect to the radiating surface facing down. In addition, the numerical calculation results agree very well with the experimental ones, confirming the credibility and the accuracy of the experimental results. The results provide an important reference for the design of thermal protection systems and determination of the experiment scheme for spacecraft and hypersonic vehicles
查看全文  查看/发表评论  下载PDF阅读器