跨声速风洞全模颤振试验技术

doi:10.7527/S1000-6893.2014.0249

Abstract

Abstract:

A review on the status of transonic wind tunnel technique for full-model flutter test is presented in this paper. The requirements on wind tunnel facility and supporting system are introduced. For wind tunnel, some special requirements on the size of wind tunnel and its quality of flow field for flutter test are analyzed. Taking example of the 2.4 m' transonic wind tunnel in the China Aerodynamic Research and Development Center, the demand control of flow states for flutter tests is introduced. As to the full-model support, the restrictions to design appropriate supporting system are emphasized from model rigid-body freedoms, stability and frequencies of the total system. Several full-model support systems are given and analyzed as examples for design reference. Then some measures to guarantee system security are presented, including static and dynamic stability of the system, emergency brake of the wind tunnel, and model protect. Finally, according to the requirements of vehicle development,several major orientation problems that we need to improve and develop in the future are discussed.

Key words: aeroelasticity, full-model flutter, floating suspension system, wind tunnel test, transonic

CLC Number:

V211.7

LU Bo, LYU Binbin, LUO Jianguo, YU Li, YANG Xinghua, GUO Hongtao, ZENG Kaichun. Wind tunnel technique for transonic full-model flutter test[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(4): 1086-1092.

References

[1] Garrick I E, Reed W H. Historical development of aircraft flutter[J]. Journal of Aircraft, 1981, 18(11):981-994.
[2] Chuck H. Accelerated flutter testing: a possible technique to expedite flutter testing for new aircraft, AIAA-2004-6822[R]. Reston: AIAA, 2004.
[3] Stanley R C, Jose A R, Nagaraja K S. Flutter study of an advanced composite wing with external stores, AIAA-1987-0880[R]. Reston: AIAA, 1987.
[4] Rivera J A, Florance J R. Contributions of transonic dynamics tunnel testing to airplane flutter clearance, AIAA-2000-1768[R]. Reston: AIAA, 2000.
[5] Livne E, Terrence A W. Aeroelasticity of nonconventional airplane configurations—past and future[J]. Journal of Aircraft, 2003, 40(6): 1047-1065.
[6] Stanley R C, Thomas E N, Boyd P. Transonic dynamics tunnel aeroelastic testing in support of aircraft development[J]. Journal of Aircraft, 2003, 40(5): 820-831.
[7] Yang C, Xiao Z P, Wang Z Q. A robust aeroelastic optimization method of structure and trim for air vehicle with multiple control surfaces [J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(1): 75-82 (in Chinese). 杨超, 肖志鹏, 万志强. 多控制面飞行器结构与配平鲁棒气动弹性优化方法.[J] 航空学报, 2011, 32(1): 75-82.
[8] Yang G W, Qian W. Numerical analyses of transonic flutter on an aircraft [J]. Chinese Journal of Theoretical and Applied Mechanics, 2005, 37(6): 769-776 (in Chinese). 杨国伟, 钱卫. 飞行器跨声速气动弹性数值分析[J]. 力学学报, 2005, 37(6): 769-776.
[9] Lu Z L, Guo T Q, Guan D. A study of calculation method for transonic flutter [J]. Acta Aeronautica et Astronautica Sinica, 2004, 25(3): 214-217 (in Chinese). 陆志良, 郭同庆, 管德. 跨音速颤振计算方法研究[J].航空学报, 2004, 25(3): 214-217.
[10] Wu Z G, Yang C. Aeroservoelastic design optimization of flexible wings [J]. Acta Aeronautica et Astronautica Sinica, 2006, 27(4): 570-573(in Chinese). 吴志刚, 杨超. 机翼的气动伺服弹性优化设计研究[J]. 航空学报, 2006, 27(4): 570-573.
[11] Cui P, Han J L. Investigation of nolinear aeroelastic analysis using CFD/CSD [J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(3): 480-486 (in Chinese). 崔鹏, 韩景龙. 基于CFD/CSD的非线性气动弹性分析方法[J].航空学报, 2010, 31(3): 480-486.
[12] Ricketts R H. Experimental aeroelasticity—history, status and future in brief, NASA/TM-102651[R]. Hampton: NASA Langley Research Center, 1990.
[13] Cole S R, Noll T E, Perry B. Transonic dynamics tunnel aeroelastic testing in support of aircraft development[J]. Journal of Aircraft. 2003, 40(5): 820-831.
[14] Reed W H. Aeroelasticity matters: some reflections on two decades of testing in the NASA Langley transonic dynamics tunnel, NASA/TM-83210[R]. Hampton: NASA Langley Research Center, 1981.
[15] Ricketts R H, Noll T E, Whitlow W Jr. An overview of aeroelasticity studies for the National AeroSpace plane, AIAA-1993-1313[R]. Reston: AIAA, 1993.
[16] Lu B, Yang X H, Luo J G, et al. Floating suspension system for full model flutter test in transonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2009, 23(3): 90-94 (in Chinese). 路波, 杨兴华, 罗建国, 等. 跨声速风洞全模颤振试验悬浮支撑系统[J].实验流体力学, 2009, 23(3): 90-94.
[17] Guo H T, Lu B, Yu L, et al. Investigation on full-model flutter of a certain fighter plane in high-speed wind tunnel test[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(10): 1765-1771 (in Chinese). 郭洪涛, 路波, 余立, 等. 某战斗机高速全模颤振风洞试验研究[J]. 航空学报, 2012 ,33(10): 1765-1771.
[18] Bennett R M, Farmer M G. A wind tunnel technique for determining stability derivatives from cable mounted aeroelastic models, AIAA-1977-1128[R]. Reston: AIAA, 1977.
[19] Thompson N, Farmer M. A stability analysis of an F/A-18 E/F cable mount model, NASA/TM-108989[R]. Hampton: NASA Langley Research Center, 1994.
[20] Chin J, Barbero P. User's guide for a revised computer program to analyze the LRC 16 foot transonic dynamics tunnel active cable mount system, NASA/CR-132692[R]. Hampton: NASA Langley Research Center, 1975.

Wind tunnel technique for transonic full-model flutter test

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Shanjie XU, Hongqiang LYU, Zhongchen LIU, Yan LENG, Xuejun LIU. Data analysis of sonic boom test based on probability model [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626269-626269.
[2]	Zhongchen LIU, Zhansen QIAN, Xuefei LI, Yan LENG, Dapeng GUO. Wind tunnel test techniques for exhaust nozzle plume effects on near-field sonic boom [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626952-626952.
[3]	Jun SHU, Dongguang XU, Zhirong HAN, Si LI, Xiong HUANG. Hybrid wing design of icing wind tunnel supercooled large droplet icing test [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(1): 627182-627182.
[4]	AN Liping, WANG Hao, WANG Yangang, ZHU Zihuan. Wet compression performance and flow characteristics of transonic compressor [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 126024-126024.
[5]	LIU Chuanzhen, MENG Xufei, LIU Rongjian, BAI Peng. Experimental and numerical investigation of hypersonic performance of double swept waverider [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 126015-126015.
[6]	LIU Jun, LUO Xinfu, WANG Xiansheng. Experiment on influence of leading-edge shape on aerodynamic characteristics of cavity model [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125235-125235.
[7]	ZHOU Yitao, YANG Yang, WU Zhigang, YANG Chao. Flight test for gust alleviation on a high aspect ratio UAV platform [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 526126-526126.
[8]	HOU Yingyu, LI Qi, JI Chen, LIU Ziqiang. Experimental design of aeroelastic load with supersonic low frequency and large buffeting [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 626454-626454.
[9]	ZHANG Zhenkai, JIA Sijia, SONG Chen, YANG Chao. Optimum design of wind tunnel test model for compliant morphing trailing edge [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 226071-226071.
[10]	ZENG Kaichun, KOU Xiping, YANG Xinghua, YU Li, ZHA Jun. Optimization of active vibration damping structure for transonic wind tunnel test model [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(2): 224944-224944.
[11]	ZHANG Shenghua, DENG Feng, QIN Ning, LIU Xueqiang. Numerical study on impact of shock control bump on transonic buffet [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526806-526806.
[12]	ZHOU Zhenyao, LYU Fei, ZHOU Bin, YANG Zhao. Verification method for natural laminar flow drag reduction and layout design of test section [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526751-526751.
[13]	JIANG Youxu, LI Jie, YANG Zhao. Data correction method of wind tunnel test for verification aircraft with laminar wing section [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526814-526814.
[14]	WANG Meng, LI Yujun, ZHAO Ronghuan, ZHONG Hongjie. Transition detection technique for wide speed range by means of on-line heating coating [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526820-526820.
[15]	YI Bingli, LIU Boyu, WANG Zhengqu, ZHANG Tiejun, LU Dan, ZHAO Yan. Test technology of twin-sting supports in 1.2 m high speed wind tunnel [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526794-526794.