Calculation of Aerodynamic Heating and Ablation of Multi-layer Thermal Protection Material

doi:10.3969/j.issn.1000-1093.2015.10.017

Abstract

Abstract: It is inevitable to evaluate the aerodynamic heat and the ablation of thermal protection material for designing a hypersonic aircraft. A coupling method is presented for the calculation of aerodynamic heat, material ablation and transient temperature distribution. The method and program are validated by experimental data. The results indicate that the method has higher precision and efficiency. For a given trajectory, the aerodynamic heat, ablation performance of thermal protection layer and temperature filed are predicted by the coupling method. The proposed method can be used to calculate the ablation and temperature distribution in given operation conditions in design phase which is referable for the design of multi-layer thermal protection material for hypersonic aircrafts.

Key words: thermology, aerodynamic heat, ablation calculation, transient temperature field, multi-layer thermal protection

CLC Number:

V258

ZHANG Zhi-hao, SUN De-chuan. Calculation of Aerodynamic Heating and Ablation of Multi-layer Thermal Protection Material[J]. Acta Armamentarii, 2015, 36(10): 1949-1954.

References

［1］吕丽丽.高超声速气动热工程算法研究[D]. 西安：西北工业大学,2005.
LYU Li-li. Research for aerodynamic heat methods of hypersonic[D]. Xi’an:Northwestern Polytechnical University,2005.(in Chinese)
[2] 杨凯, 高效伟.高超声速气动热环境工程算法[J]. 导弹与载人航天运载技术， 2010(4):19-23.
YANG Kai, GAO Xiao-wei. Engineering algorithm for aeroheating environment of hypersonic aircrafts[J]. Missiles and Space Vehicles, 2010(4):19-23.（in Chinese）
[3] 薛鹏飞, 龚春林, 谷良贤.基于轴对称比拟的气动热计算方法研究[J]. 计算机仿真, 2012,29(6):97-100.
XUE Peng-fei, GONG Chun-lin, GU Liang-xian. Study of method for aerothermal heating calculating based on axisymmetric analogue[J]. Computer Simulation, 2012,29(6):97-100.（in Chinese）
[4] 李建林, 唐乾刚, 霍林,等.复杂外形高超声速飞行器气动热快速工程估算[J]. 国防科技大学学报, 2012,34(6):89-93.
LI Jian-lin, TANG Qian-gang, HUO Lin,et al. The rapid engineering aero-heating calculation method for complex shaped hypersonic vehicles[J]. Journal of National University of Defense Technology, 2012,34(6):89-93.（in Chinese）
[5] 欧东斌, 陈连忠, 陈海群,等.硅基复合材料烧蚀特性试验研究[J]. 宇航材料工艺, 2009(1):85-90.
OU Dong-bing, CHEN Lian-zhong, CHEN Hai-qun, et al. Ablation properties of silicon based coposites[J]. Aerospace Materials & Technology, 2009(1):85-90.（in Chinese）
[6] 孙冰, 林小树, 刘小勇，等. 硅基材料烧蚀模型研究[J]. 宇航学报, 2003，24(5):282-286.
SUN Bing, LIN Xiao-shu, LIU Xiao-yong, et al. Study on ablation model of silica-reinforced composites[J]. Journal of Astronautics, 2003，24(5):282-286.（in Chinese）
[7] 张俊华, 李锦文, 魏化震，等. 高性能酚醛树脂基烧蚀复合材料的研究[J]. 纤维复合材料, 2009(1):15-18.
ZHANG Jun-hua, LI Jin-wen, WEI Hua-zhen, et al. Research on high performance phenolic resin ablative composites[J]. Fiber Composites, 2009(1):15-18.（in Chinese）
[8] 易法军, 孟松鹤, 梁军,等. 防热复合材料高温体积烧蚀模型[J]. 哈尔滨工业大学学报, 2001.33(6):725-728.
YI Fa-jun, MENG Song-he, LIANG Jun, et al. A high-temperature volumetric ablation model for thermal protective composites[J]. Journal of Harbin Institute of Technology, 2001, 33(6):725-728. （in Chinese）
[9] Fay J A, Riddell F R. Theory of stagnation point heat transfer in dissociated air[J].Journal of Aeronautic Science,1958,25(2):73-85.
[10] Lees L. Laminar heat transfer over blunt nosed bodies at hypersonic flight speed[J]. Jet Propulsion,1956,26(4):259-269.
[11] 时圣波.高硅氧/酚醛复合材料的烧蚀性能与热力学行为研究[D]. 哈尔滨：哈尔滨工业大学，2013.
SHI Sheng-bo. Ablation properties and thermomechanical behavior of silica/phenolic composites[D].Harbin：Harbin Institute of Technology,2013.（in Chinese）
[12] Rose P H, Stark W I. Stagnation point heat transfer measurements in dissociated air[J]. Journal of Aerospace Science,1958,25(2):86-97.
[13] Kemp N H, Rose R H, Detra R W. Laminar heat transfer around blunt bodies in dissociated air[J]. Journal of the Aerospace Science, 1959,26(7):421-430.
[14] 姜贵庆，李仲平，俞继军. 硅基复合材料粘性系数的参数辨识[J]. 空气动力学学报，2008, 26(4):425-455.
JIANG Gui-qing, LI Zhong-ping, YU Ji-jun. Prarmeter identification of silicon based composites' viscous coefficient[J].Acta Aerodynamica Sinica, 2008, 26(4):425-455.（in Chinese）
[15] 姜贵庆，刘连元.高速气流传热与烧蚀热防护[M].北京:国防工业出版社，2003:52-66.
JIANG Gui-qing, LIU Lian-yuan.Heat transfer of hypersonic gas and ablation thermal protection[M]. Beijing:National Defense Industry Press, 2003:52-66.（in Chinese）
[16] 张志成，潘海林，刘初平，等.高超声速气动热和热防护[M].北京:国防工业出版社，2003:222-248.
ZHANG Zhi-cheng, PAN Hai-lin, LIU Chu-ping, et al. Hypersonic aerodynamic heat and thermal protection[M]. Beijing: National Defense Industry Press, 2003:222-248.（in Chinese）
[17] Henderson J B, Verma Y P, Tant M R, et al. Measurement of the thermal conductivity of polymer composites to high temperatures using the line source technique[J]. Polymer Composites,1983, 4(4): 219-224.
[18] Henderson J B, Tant M R. A study of the kinetics of high-temperature carbon-silica reactions in an ablative polymer composite[J]. Polymer Composites,1983, 4(4): 233-237.
[19] Bruneton E, Tallaron C, Gras-Naulin N,et al. Evolution of the structure and mechanical behaviour of a carbon foam at very high temperatures[J]. Carbon,2002,40(11):1919-1927.

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