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The structure of embedded high thermal conductivity carbon material leading thermal protection is considered as thermal protection system to prevent hypersonic vehicle nosetip which requires sharp figure during hypersonic flying, from being seriously aerodynamically heated. By fluid structure interaction method, we analyze leading thermal protection of nosetip and validate that embedded high thermal conductivity carbon material structure has a good effect on thermal protection. The maximal temperature of the nosetip which uses leading thermal protection structure is reduced by 21.9% and the lowest temperature of aft is increased by 15.2% when Mach number is 9. The transfer of heat from head to after-body is achieved, the thermal load of the front head is weakened and the ability of leading-edge thermal protection is strengthened. The influences of structure parameter and material attributes of coating and thermal conductivity of high conductivity carbon material on thermal protection are discussed. The highest temperature of the nosetip decreases with thermal conductivity of coating increasing to a steady value and descends with blackness level of coating ascending and increases with the thickness of coating increasing, and it descends in parabola form as thermal conductivity of carbon materials increases.
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Keywords:
- leading thermal protection /
- nosetip /
- fluid structure interaction /
- high thermal conductivity carbon materials
[1] Yan C, Yu J J, Li J Z 2006 Acta Aero. Sin. 24 125 (in Chinese) [阎超, 禹建军, 李君哲 2006 空气动力学学报 24 125]
[2] Li P F, Wu S P 2010 J. Aero. Power 25 1705 (in Chinese) [李鹏飞, 吴颂平 2010 航空动力学报 25 1705]
[3] 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]
[4] David E 1998 NASA CR-1998-208962
[5] David E 1998 NASA CR-1998-207642
[6] 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]
[7] 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]
[8] 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, Y. T. Zhu 2008 57 3391]
[9] 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]
[10] Li J W, Liu Y 2005 J. Propulsion Techn. 26 111 (in Chinese) [李军伟, 刘玉 2005 推进技术 26 111]
[11] Tao W Q 2001 Numerical Heat Transfer (Xi' an: Xi' an Jiaotong University Press) p176 (in Chinese) [陶文铨 2001 数值传热学 (西安:西安交通大学出版社) 第176页]
[12] Dechaumphi P, Thornton P E, Wieting A R 1989 AIAA-26055-793
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[1] Yan C, Yu J J, Li J Z 2006 Acta Aero. Sin. 24 125 (in Chinese) [阎超, 禹建军, 李君哲 2006 空气动力学学报 24 125]
[2] Li P F, Wu S P 2010 J. Aero. Power 25 1705 (in Chinese) [李鹏飞, 吴颂平 2010 航空动力学报 25 1705]
[3] 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]
[4] David E 1998 NASA CR-1998-208962
[5] David E 1998 NASA CR-1998-207642
[6] 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]
[7] 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]
[8] 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, Y. T. Zhu 2008 57 3391]
[9] 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]
[10] Li J W, Liu Y 2005 J. Propulsion Techn. 26 111 (in Chinese) [李军伟, 刘玉 2005 推进技术 26 111]
[11] Tao W Q 2001 Numerical Heat Transfer (Xi' an: Xi' an Jiaotong University Press) p176 (in Chinese) [陶文铨 2001 数值传热学 (西安:西安交通大学出版社) 第176页]
[12] Dechaumphi P, Thornton P E, Wieting A R 1989 AIAA-26055-793
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