| 长时间气动加热飞行器的隔热机理 |
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| 引用本文： | 姜贵庆%俞继军.长时间气动加热飞行器的隔热机理[J].宇航材料工艺,2006,36(1):27-29. |
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| 作者姓名： | 姜贵庆%俞继军 |
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| 作者单位： | 中国航天空气动力技术研究院,北京,100074 |
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| 摘 要： | 主要论述长时间气动加热飞行器热防护系统隔热机理的新概念，提出传统的单相固体热传导由于其隔热机制的局限性，已不能解决新型高超声速式飞行器的隔热问题，代之以气-固的辐射-传导-对流复合传热机制。多相复合传热机理可解决长时间气动加热飞行器隔热的问题。
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| 关 键 词： | 隔热机理 辐射 传导 对流 |
| 收稿时间： | 2004-10-28 |
| 修稿时间： | 2004-10-282005-02-07 |
Insulation Mechanism of Spacecraft With Long Time Aero-Heating |
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| Jiang Guiqing,Yu Jijun.Insulation Mechanism of Spacecraft With Long Time Aero-Heating[J].Aerospace Materials & Technology,2006,36(1):27-29. |
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| Authors: | Jiang Guiqing Yu Jijun |
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| Institution: | China Academy of Aerospace Aerodynamics, Beijing 100074 |
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| Abstract: | The new concept of insulation mechanism of thermal protection system for spacecraft with long time aero-heating is presented.It is pointed out that traditional heat conduction of single phase solid can not solve the insulation problem of spacecraft with long time aero-heating because of limitation of its insulation.Therefore the new insulation mechanism is heat conduction mechanism with multi-phase(gas-solid) and complex(radiation-conduction-convection) instead of single phase solid heat conduction. |
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| Keywords: | Insulation mechanism Radiation Conduction Convection |
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