Numerical analysis of high-temperature-gas wind tunnel thermal characteristics
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摘要: 提出了利用亚音速高温燃气流进行近空间高超飞行器热环境地面模拟的试验方案,在试验装置试验段,通过高温高速的燃气流引射低速的冷气流,达到仅使飞行器头锥驻点附近区域产生局部高温而其余头锥蒙皮表面低温的目的.对某型高超音速飞行器的头锥利用高温燃气进行加热并利用CFD(Computational Fluid Dynamics)方法对13种模拟工况进行了数值仿真分析.将数值模拟计算结果与飞行器在高超音速飞行状态下对应机体部位气动热的理论计算值进行了对比,证实了亚声速高温燃气热环境模拟方法的可行性,为高温燃气地面模拟设备技术方案论证提供了依据.Abstract: An experimental method using subsonic high-temperature gas flow to simulate aerodynamic thermal environment of near space hypersonic vehicle was introduced. In the test section of the experiment equipment, the room temperatwe air was ejected by the subsonic high-temperature gas flow to make the heat distribution of the experimental condition in line with that of the real flight condition on the cap. 13 experimental conditions were analyzed using computational fluid dynamics(CFD). The numerical analysis verifies the feasibility of the experimental method and provides basis for demonstration of the experiment facilities.
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Key words:
- near space /
- thermal environment /
- hypersonic aricraft /
- high-temperature-gas /
- numerical simulation
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[1] 王佩广,刘永绩,王浚.高超声速飞行器综合热管理系统方案探讨[J].中国工程科学,2007,9(2):44-48 Wang Peiguang,Liu Yongji,Wang Jun.Discussion on integrated environment control/thermal management system concepts for hypersonic vehicle[J].Engineering Science,2007,9(2):44-48(in Chinese) [2] 解发瑜,李刚,徐忠昌.高超声速飞行器概念及发展动态[J].飞航导弹,2004(5):27-31 Xie Fayu,Li Gang,Xu Zhongchang.The concept and development of hpersonic vehicle[J].Winged Missiles Journal,2004(5):27-31(in Chinese) [3] 周华,韩莹.高超音速地面模拟设备的研究进展[J].飞行力学,1999,17(4):6-10 Zhou Hua,Han Ying.The research progress of hypersonic ground simulation test facilities[J].Flight Dynamics,1999,17(4):6-10(in Chinese) [4] Bartheleme R.National aerospace plane program[R].AIAA-89-5001,1989 [5] Ho S Y,Paull A.Coupled thermal st ructural and vibrational analysis of a hypersonic engine for flight test[J].Aerospace Science and Technology,2006,10(5):420-426 [6] 王乐善,王庆盛.结构热试验技术的新发展[J].导弹与航天运载技术,2000(2):7-13 Wang Leshan,Wang Qingsheng.The recent trends of thermal-test technique of structure[J].Missiles and Space Vehicles,2000(2):7-13(in Chinese) [7] 姚峰,董素君,王浚.高温燃气热环境加热特性的试验方法研究[J].宇航学报,2010,31(5):1446-1451 Yao Feng,Dong Sujun,Wang Jun.Numerical analysis of thermal characteristics of high temperature-gas thermal environment[J].Journal of Astronautics,2010,31(5):1446-1451(in Chinese) [8] 姚峰,董素君,王浚.高温燃气热环境模拟方案仿真研究[J].航空动力学报,2010,25(4):768-773 Yao Feng,Dong Sujun,Wang Jun.Numerical analysis of subsonic high-temperature-gas thermal environment simulation[J].Journal of Aerospace Power,2010,25(4):768-773(in Chinese) [9] 王福军.计算流体动力学分析[M].北京:清华大学出版社,2004 Wang Fujun.Computational fluid dynamics analysis[M].Beijing:Tsinghua University Press,2004(in Chinese) [10] Kleb W L,Wood W A,Gnoffo P A,et al.Computational aeroheating predictions for X-34[R].AIAA 98-0879,1998 [11] Beesley W G.Space shuttle entry thermal testing techniques[R].AIAA 78-1628,1978 [12] Jang C M,Sato D,Fukano T.Experimental analysis on tip leakage and wake flow in an axial flow fan according to flow rates[J].Journal of Fluids Engineering,2005(3):322-329 [13] 陶文铨.计算传热学 [M].2版.西安:西安交通大学出版社,2003 Tao Wenquan.Numerical heat transfer[M].Second Edition.Xi-an Jiaotong University Press,2003(in Chinese) [14] Hogenauer E,Koelle D E.The German aerospace vehicle program[R].AIAA-89-5007,1989 [15] Cazin P.French space plane research,from Herms to transatomospheric vehicl[R].AIAA-89-5020,1989
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