Development of a two degrees of freedom support system for full model gust tests

TANG Jianping; WU Fuzhang; PU Lidong; ZENG Xian'ang; ZHANG Haiyou; ZHANG Lei

doi:10.11729/syltlx20200062

Volume 35 Issue 3

Jun. 2021

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TANG Jianping, WU Fuzhang, PU Lidong, et al. Development of a two degrees of freedom support system for full model gust tests[J]. Journal of Experiments in Fluid Mechanics, 2021, 35(3): 94-99. doi: 10.11729/syltlx20200062

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Development of a two degrees of freedom support system for full model gust tests

doi: 10.11729/syltlx20200062

1.
China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China
2.
The First Aircraft Institute, Aviation Industry Corporation of China, Xi'an 710089, China

Received Date: 2020-05-09
Rev Recd Date: 2020-06-19
Publish Date: 2021-06-25

Abstract

Abstract

This paper describes the development of a support system for free flying dynamically scaled full model. The free flying model requires plunge and pitch degrees of freedom(DOF) for the measurement of the gust response in the 8 m×6 m wind tunnel in LSAI of CARDC. The main part of the system consists of 2 slideways and a steel beam. The characteristics of the system include: its left and right structures are symmetrical, the range of free movement in the plunge direction is 2.8 m and the coefficient of friction is 0.006, the range of free movement in the pitch direction is ±10°, the lowest frequency of the system supporting a 50 kg model is not less than 12 Hz, and the structure changes in the test section can be ignored. By optimizing the structure and selecting the materials, the sliding carriage's mass is less than 6 kg. A gust load alleviation test for a full model was successfully completed by the use of the support system, which verifies the practical effect of the system.
- rigid body motion mode,
- full model,
- gust test,
- two DOFs,
- support system

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References(14)

References

[1]	胡海岩, 赵永辉, 黄锐. 飞机结构气动弹性分析与控制研究[J]. 力学学报, 2016, 48(1): 1-27. doi: 10.6052/0459-1879-15-423 HU H Y, ZHAO Y H, HUANG R. Studies on aeroelastic analysis and control of aircraft structures[J]. Chinese Journal of Theoretical and Applied Mechanics, 2016, 48(1): 1-27. doi: 10.6052/0459-1879-15-423
[2]	SILVA W, VARTIO E, SHIMKO A, et al. Development of aeroservoelastic analytical models and gust load alleviation control laws of a SensorCraft wind-tunnel model using measured data[R]. AIAA-2006-1935, 2006. doi: 10.2514/6.2006-1935
[3]	SCOTT R C, VETTER T K, PENNING K B, et al. Aeroservo-elastic testing of a sidewall mounted free flying wind-tunnel model[R]. AIAA-2008-7186, 2008. doi: 10.2514/6.2008-7186
[4]	REICHENBACH E Y. Aeroservoelastic design and test validation of the Joined-Wing Sensorcraft[R]. AIAA-2008-7189, 2008. doi: 10.2514/6.2008-7189
[5]	REICHENBACH E, CASTELLUCCIO M, SEXTON B. Joined-Wing Sensorcraft aeroservoelastic wind tunnel test program[R]. AIAA-2011-1956, 2011. doi: 10.2514/6.2011-1956
[6]	SHARMA V, REICHENBACH E. Development of an innovative support system for Sensor Craft model[R]. AIAA-2011-1958, 2011. doi: 10.2514/6.2011-1958
[7]	SCOTT R C, CASTELLUCCIO M A, COULSON D A, et al. Aeroservoelastic wind-tunnel tests of a free-flying, Joined-Wing SensorCraft model for gust load alleviation[R]. AIAA-2011-1960, 2011. doi: 10.2514/6.2011-1960
[8]	SCOTT R C, VETTER T K, PENNING K B, et al. Aeroservoelastic testing of free flying wind tunnel models Part 1: A sidewall supported semispan model tested for gust load alleviation and flutter suppression[R]. NASA/TP-2013-218051, 2013.
[9]	SCOTT R C, VETTER T K, PENNING K B, et al. Aeroservo-elastic testing of free flying wind tunnel models Part 2: A centerline supported fullspan model tested for gust load alleviation[R]. NASA/TP-2014-218170, 2014.
[10]	金华, 王辉, 张海酉, 等. FL-13风洞突风发生装置研究[J]. 空气动力学学报, 2016, 34(1): 40-46. doi: 10.7638/kqdlxxb-2015.0134 JIN H, WANG H, ZHANG H Y, et al. Investigation on gust response test apparatus in FL-13 wind tunnel[J]. Acta Aerodynamica Sinica, 2016, 34(1): 40-46. doi: 10.7638/kqdlxxb-2015.0134
[11]	陈磊, 吴志刚, 杨超, 等. 多控制面机翼阵风减缓主动控制与风洞试验验证[J]. 航空学报, 2009, 30(12): 2250-2256. doi: 10.3321/j.issn:1000-6893.2009.12.002 CHEN L, WU Z G, YANG C, et al. Active control and wind tunnel test verification of multi-control surfaces wing for gust alleviation[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(12): 2250-2256. doi: 10.3321/j.issn:1000-6893.2009.12.002
[12]	杨俊斌, 吴志刚, 戴玉婷, 等. 飞翼布局飞机阵风减缓主动控制风洞试验[J]. 北京航空航天大学学报, 2017, 43(1): 184-192. doi: 10.13700/j.bh.1001-5965.2016.0079 YANG J B, WU Z G, DAI Y T, et al. Wind tunnel test of gust alleviation active control for flying wing configuration aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(1): 184-192. doi: 10.13700/j.bh.1001-5965.2016.0079
[13]	唐建平, 杨远志, 梁鉴. 低速全模颤振试验悬挂支撑系统[J]. 实验流体力学, 2014, 28(4): 65-69. doi: 10.11729/syltlx20130014 TANG J P, YANG Y Z, LIANG J. Floating suspension system for full model flutter tests at low speed[J]. Journal of Experiments in Fluid Mechanics, 2014, 28(4): 65-69. doi: 10.11729/syltlx20130014
[14]	杨希明, 刘南, 郭承鹏, 等. 飞行器气动弹性风洞试验技术综述[J]. 空气动力学学报, 2018, 36(6): 995-1008. doi: 10.7638/kqdlxxb-2018.0039 YANG X M, LIU N, GUO C P, et al. A survey of aeroelastic wind tunnel testtechnology of flight vehicles[J]. Acta Aerodynamica Sinica, 2018, 36(6): 995-1008. doi: 10.7638/kqdlxxb-2018.0039