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The structure of embedded high thermal conductivity layer leading thermal protection is considered as thermal protection system to prevent hypersonic vehicle from the serious aerodynamic heating. By numerical method, we analyze the cooling effect of the leading thermal protection system under given conditions. The maximum outer surface temperature and the inner surface temperature are reduced by 9.1% and by 31.5% respectively. Both high temperature region and low temperature region are blocked in the external layer and the inner temperature distributions are more uniform. The transfer of heat from high temperature region to low one is achieved, the thermal load of the high temperature area is weakened, and the ability of leading thermal protection system is strengthened. The research shows that the cooling effect of leading system increases with the increases of aerodynamic flux ratio and the area ratio of radiative surfaces. The influences of structure parameters and materials properties on thermal protection are discussed, which provides some references for the design of the structure and the selection of materials.
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Keywords:
- high directional thermal conductivity layer /
- leading thermal protection /
- aerodynamic heating /
- heat radiation
[1] David E 2008 AIAA-2008-2068
[2] Wojcik C C, Clark L T 1991 AIAA-1991-1400-520
[3] David E 1998 NASA CR-1998-208962
[4] David E 1998 NASA CR-1998-207642
[5] Chen L Z, Ou D B, Liu D Y 2009 Frontier Sci. 2 41 (in Chinese) [陈连忠, 欧东斌, 刘德英 2009 前沿科学 2 41]
[6] Jiang G Q, Ai B C, Yu J J, Chen L Z 2008 11th Countrywide Heat Pipe Conference Weihai September 7-11 72 (in Chinese) [姜贵庆, 艾邦成, 俞继军, 陈连忠 2008第十一届全国热管会议 威海9月7---11日72]
[7] Li T Q, Hu Z J 2007 Aeros. Mater. Techn. 1 16 (in Chinese) [李同起, 胡子君 2007 航空材料工艺 1 16]
[8] Bao W X, Zhu C C 2006 Acta Phys. Sin. 55 3552 (in Chinese) [保文星, 朱长纯 2006 55 3552]
[9] Wang Z L, Liang J G, Tang D W, Zhu Y T 2008 Acta Phys. Sin. 57 3391 (in Chinese) [王照亮, 梁金国, 唐大伟, Zhu Y T 2008 57 3391]
[10] Hou Q W, Cao B Y, Guo Z Y 2009 Acta Phys. Sin. 58 7809 (in Chinese) [侯泉文, 曹炳阳, 过增元 2009 58 7809]
[11] Sun J, Liu W Q 2011 Acta Aeron. Astron. Sin. 32 1622 (in Chinese) [孙健, 刘伟强 2011 航空学报 32 1622]
[12] Guo Z Y, Cao B Y 2008 Acta Phys. Sin. 57 4273 (in Chinese) [过增元, 曹炳阳 2008 57 4273]
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[1] David E 2008 AIAA-2008-2068
[2] Wojcik C C, Clark L T 1991 AIAA-1991-1400-520
[3] David E 1998 NASA CR-1998-208962
[4] David E 1998 NASA CR-1998-207642
[5] Chen L Z, Ou D B, Liu D Y 2009 Frontier Sci. 2 41 (in Chinese) [陈连忠, 欧东斌, 刘德英 2009 前沿科学 2 41]
[6] Jiang G Q, Ai B C, Yu J J, Chen L Z 2008 11th Countrywide Heat Pipe Conference Weihai September 7-11 72 (in Chinese) [姜贵庆, 艾邦成, 俞继军, 陈连忠 2008第十一届全国热管会议 威海9月7---11日72]
[7] Li T Q, Hu Z J 2007 Aeros. Mater. Techn. 1 16 (in Chinese) [李同起, 胡子君 2007 航空材料工艺 1 16]
[8] Bao W X, Zhu C C 2006 Acta Phys. Sin. 55 3552 (in Chinese) [保文星, 朱长纯 2006 55 3552]
[9] Wang Z L, Liang J G, Tang D W, Zhu Y T 2008 Acta Phys. Sin. 57 3391 (in Chinese) [王照亮, 梁金国, 唐大伟, Zhu Y T 2008 57 3391]
[10] Hou Q W, Cao B Y, Guo Z Y 2009 Acta Phys. Sin. 58 7809 (in Chinese) [侯泉文, 曹炳阳, 过增元 2009 58 7809]
[11] Sun J, Liu W Q 2011 Acta Aeron. Astron. Sin. 32 1622 (in Chinese) [孙健, 刘伟强 2011 航空学报 32 1622]
[12] Guo Z Y, Cao B Y 2008 Acta Phys. Sin. 57 4273 (in Chinese) [过增元, 曹炳阳 2008 57 4273]
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