吸气式高超声速飞行器内外流同时测力试验

doi:10.7527/S1000-6893.2014.0123

Abstract

Abstract:

In order to investigate the new force test technique feasibility of the air-breathing hypersonic vehicle, a wind tunnel test is conducted at the simulated flight environment of Mach number Ma=6.0 and altitude H=27 km. The research subject is a simplified configuration without wings and fins of an axisymmetric air-breathing hypersonic vehicle. The internal and external flow decoupling crucial technology is settled by the rational test system design. The internal and external flow aerodynamic loads of the model in the same run are measured by a double ring type six-component balances. The test results show that the internal and external flow aerodynamic measurements and the total aerodynamic datum exactly reflect abundant physical phenomena, including decoupling and cross-flow between the internal and external flow, the inlet starting/un-starting, and the spillage influence. The internal and external flow decoupling is realized in physics. The internal aerodynamic forces make a great contribution to the hypersonic vehicle aerodynamic performance. Under the conditions of the internal and external flow decoupling, the aerodynamic data have high accuracy and good repeatability when the inlet starts. The forces from cross-flow are the internal forces. The results of the test indicate that it is feasible for this new force test technique to provide a valid method to solve the problem of internal and external flow aerodynamic data uncertainty from different tests.

Key words: hypersonic vehicle, wind tunnel test, aerodynamic, model design, inlet, internal and external flow decoupling

CLC Number:

WANG Zejiang, SUN Peng, LI Xuguo, TANG Xiaowei. Force test on internal and external flow simultaneous measurement of air-breathing hypersonic vehicle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(3): 797-803.

References

[1] Holland S D, Woods W C, Engelund W C. Hyper-X research vehicle experimental aerodynamics test program overview[J]. Journal of Spacecraft and Rockets, 2001, 38(6): 11-12

[2] Holden M S, Smolinski G J, Mundy E, et al. Experimental studies for hypersonic vehicle design and code validation of the unsteady flow characteristics associated with "free flight" shroud and stage separation, and mode switching, AIAA-2008-0642[R]. Reston: AIAA, 2008.

[3] Bai H C, Wang Z J. Discussion on force-accounting system for airbreathing hypersonic vehicle[J]. Journal of Propulsion Technology, 2012, 33(1): 1-6 (in Chinese). 白菡尘, 王泽江. 高超声速冲压发动机-飞行器计力体系讨论[J]. 推进技术, 2012, 33(1): 1-6.

[4] Voland R T. Methods for determining the internal thrust of Scramjet engine modules from experimental data, AIAA-1990-2340[R]. Reston: AIAA, 1990.

[5] Mitani T, Kobayashi K, Hiraiwa T, et al. Evaluation of internal aerodynamic performance in scramjet engines, AIAA-2001-1885[R]. Reston: AIAA, 2001.

[6] Tan H J, Guo R W. Design and wind tunnel study of a top-mounted diverterless inlet[J]. Chinese Journal of Aeronautics, 2004, 17(2): 72-78.

[7] Holden M S, Wadhams T P, MacLean M. Experimental studies in the LENS supersonic and hypersonic tunnels for hypervelocity vehicle performance and code validation, AIAA-2008-2505[R]. Reston: AIAA, 2008.

[8] Xu X B, Shu H F, Xie F, et al. Technique investigation on flow through model inner flow drag straightway measured by strain-gauge balance[J]. Journal of Propulsion Technology, 2013, 34(3): 311-315 (in Chinese). 许晓斌, 舒海峰, 谢飞, 等. 通气模型内流道阻力直接测量技术[J]. 推进技术, 2013, 34(3): 311-315.

[9] Bahm C, Baumann E, Martin J, et al. The X-43A hyper-X Mach 7 flight 2 guidance, navigation, and control overview and flight test results, AIAA-2005-3275[R]. Reston: AIAA, 2005.

[10] Nishizawa U, Kameda M. Computational simulation of shock oscillation around a supersonic air-inlet, AIAA-2006-3042[R]. Reston: AIAA, 2006.

[11] Timofeevg V, Tahir R B, Molder S. On recent development related to flow staring in hypersonic air intakes, AIAA-2008-2512[R]. Reston: AIAA, 2008.

[12] Sun S, Zhang H Y, Cheng K M, et al. The full flowpath analysis of a hypersonic vehicle[J]. Journal of Astronautics, 2007, 20(5): 385-393.

[13] Wang W X, Guo R W. Numerical study of unsteady starting characteristics of a hypersonic inlet[J]. Chinese Journal of Aeronautics, 2013, 26(3): 563-571.

[14] Cheng H M. Interference and correction on wind tunnel testing[M]. Beijing: National Defense Industry Press, 2003: 227-265 (in Chinese). 程厚梅. 风洞试验干扰与修正[M]. 北京:国防工业出版社, 2003: 227-265.

[15] Tang Z G. Hypersonic aerodynamic testing[M]. Beijing: National Defense Industry Press, 2004: 74-80 (in Chinese). 唐志共. 高超声速气动力试验[M]. 北京: 国防工业出版社, 2004: 74-80.

Force test on internal and external flow simultaneous measurement of air-breathing hypersonic vehicle

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