Dynamic test technique with large amplitude in 2.4 m transonic wind tunnel

MA Shang; ZHAO Zhongliang; JIANG Minghua; YANG Haiyong; LIU Weiliang; LI Yuping; WANG Xiaobing

doi:10.7638/kqdlxxb-2018.0151

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Dynamic test technique with large amplitude in 2.4 m transonic wind tunnel

更新时间：2026-05-28

- Dynamic test technique with large amplitude in 2.4 m transonic wind tunnel
- Vol. 37, Issue 6, Pages: 998-1003(2019)
- 作者机构：
  
  中国空气动力研究与发展中心高速空气动力研究所,四川,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0151
  CLC： V211.7
- Published：2019
- 稿件说明：
移动端阅览
马上, 赵忠良, 蒋明华, 杨海泳, 刘维亮, 李玉平, 王晓冰. 2.4 m跨声速风洞大振幅动态试验技术[J]. 空气动力学学报, 2019, 37(6): 998-1003.

MA Shang, ZHAO Zhongliang, JIANG Minghua, et al. Dynamic test technique with large amplitude in 2.4 m transonic wind tunnel[J]. 2019, 37(6): 998-1003.
马上, 赵忠良, 蒋明华, 杨海泳, 刘维亮, 李玉平, 王晓冰. 2.4 m跨声速风洞大振幅动态试验技术[J]. 空气动力学学报, 2019, 37(6): 998-1003. DOI： 10.7638/kqdlxxb-2018.0151.

MA Shang, ZHAO Zhongliang, JIANG Minghua, et al. Dynamic test technique with large amplitude in 2.4 m transonic wind tunnel[J]. 2019, 37(6): 998-1003. DOI： 10.7638/kqdlxxb-2018.0151.

摘要

现代先进飞行器在高机动飞行过程中，容易诱发非指令的多自由度耦合运动，呈现出复杂的动态气动力及耦合运动现象。为满足先进飞行器多自由度动态气动特性研究与试验评估的需求，中国空气动力研究与发展中心高速空气动力研究所在2.4 m×2.4 m跨声速风洞建立了可以开展大迎角静态、单自由度俯仰振动、快速拉起、俯仰/滚转双自由度耦合运动等试验的模拟技术。通过典型的70°三角翼验证模型的试验研究，结果表明试验技术获取的试验数据合理可靠，变化规律正确，能够准确反映模型的动态气动力迟滞特性，实现了俯仰/滚转两自由度耦合大振幅运动的纵横向动态气动力测量，可以为飞行器的试验鉴定评估提供技术支撑。

Abstract

During high maneuvering flight conditions of modern advanced flight vehicles

the coupled motion of multi-degree-of-freedom would be induced. This behaviour presents the complex unsteady aerodynamic characteristics and multi-degree-of-freedom motion attitudes. A two-degree-of-freedom pitch/roll coupled motion test device

which could be used for investigating high angle of attack static test

pitch oscillation

pitch-up in high speed and pitch/roll coupled oscillation

has been established for investigating and evaluating multi-degree-of-freedom unsteady aerodynamic characteristics of advanced flight vehicles in FL-26 wind tunnel. The unsteady aerodynamic characteristics of one-degree-of-freedom motion and two-degree-of-freedom pitch/roll coupled oscillation for the typical 70-degree delta wing model are investigated based on the dynamic test devices. The results indicate that

the test data based on the dynamic test technique is reasonable and reliable which could represent the correct typical hysteresis characteristics of dynamic normal force and pitch moment. The test device is capable of measuring aerodynamic characteristics of two-degree-of-freedom pitch/roll coupled motion of advanced flight vehicles. This could provide technical support for the unsteady aerodynamic characteristics test evaluation and assessment of flight vehicles.

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Keywords

references

SOLTANI M R, BRAGG M B, BRANDON J M. Measurements on an oscillating 70-deg delta wing in subsonic flow[J]. Journal of Aircraft, 1990, 27(3): 211-217.

WEEKS T M, NAGARAJA K S. Unsteady aerodynamics for air force needs[R]. AIAA 93-3622, 1993.

CHAMBERS J R, HALL R M. Historical review of uncommanded lateral-directional motions at transonic conditions[J]. Journal of Aircraft, 2004, 41(3): 436-447.

ERICKSON G E. High angle-of-attack aerodynamic[J]. Annual Review of Fluid Mechanics, 1995, 27: 45-88.

BRANDON J M. Dynamicstall effects and application to high performance aircraft[R]. AGARD 1991-776, 1991.

ERICSSON L E. Critical issues in high-alpha vehicle dynamic[R]. AIAA 91-3221, 1991.

LAN C E. Experimental and analytical investigation of transonic limit-cycle oscillations of aflaperon[J]. Journal of Aircraft, 1995, 32(5): 905-910

GEBERT G, KELLY J, LOPEZ J. Wind tunnel based virtual flight testing[R]. AIAA 2000-0829.

GEBERT G, KELLY J, LOPEZ J. Virtual flight testing in a ground test facility[R]. AIAA 2000-4019.

ZHAO Z L, WU J Q, LI H, et al. Investigation of virtual flight testing technique based on 2.4 m transonic wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(2): 504-512. (in Chinese)

ZHAO Z L, WU J Q, LI H, et al. Wind tunnel based virtual flight testing of aerodynamics, flight dynamics and flight control for high maneuver missle[J]. Acta Aerodynamica Sinica, 2016, 34(1): 14-19. (in Chinese)

TAO Y, ZHAO Z L, YANG H Y. Investigation on wing rock of wing-body configuration at high speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(6): 45-48. (in Chinese)

TAO Y, ZHAO Z L, LI H, et al. Investigation on dynamic behavior forecast of 80°/65° double-delta wing in roll at high incidence[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(6): 43-46. (in Chinese)

DA X Y, ZHOU W Q, ZHAO Z L, et al. Research on the kinetics of rock motion for a missile model with strake wings[J]. Acta Aerodynamica Sinica, 2014, 32(2): 154-158. (in Chinese)

LI Q, ZHAO Z L, YE Y D, et al. Numerical and experimental investigation on aerodynamic characteristics for one typical near space vehicle[J]. Acta Aerodynamica Sinica, 2017, 35(4): 504-509. (in Chinese)

GREEN B E, OTT J D. FA-18C to E wing morphing study for the abrupt-wing-stall program[R]. AIAA-2003-0925, 2003.

IGNATYEV D I, ZARIPOV K G. Wind tunnel tests for validation of control algorithms at high angles of attack using autonomous aircraft model mounted in 3DOF gimbals[R]. AIAA-2016-3106, 2016.

BERGMANN A, HUEBNER A, LOESER T. Integrated experimental and numerical research on the aerodynamics of unsteady moving aircraft[J]. Progress in Aerospace Sciences, 2008, 44(2): 121-137.

ARAUJO-ESTRADA S A, LOWENBERG M H, NEILDS, et al. Evaluation of aircraft model upset behaviour using wind tunnel manoeuvre rig[R]. AIAA-2015-0750, 2015.

HUANG D, WU G X. Investigation of unsteady aerodynamic characteristics for a delta wing oscillating in large amplitude pitching-roll motion[J]. Acta Aeronautica et Astronautica Sinica, 1999, 20(6): 485-488. (in Chinese)

DENG X Y, ZHU J, WANG Y K, et al. THE progress of studies of uncommanded motion and its suppression of flying vehicle with high manueverability[J]. Mechanics and Practice, 2012, 34(3): 1-8. (in Chinese)

LIU C M, ZHAO Z J, BU C, et al. Double degree-of-freedom large amplitude oscillation test technology in low speed wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(8): 2417-2425. (in Chinese)

XIE Z J, SUN X Y, SUN H S, et al. Mechanism design and dynamics analysis of high speed parallel robot for dynamic test in low speed wind tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(3): 487-494. (in Chinese)

LI Q C, ZHAO Z L, YANG H Y, et al. Dynamic characteristics of hinged strake-wing and close-coupled wing-canard configuration fighter models[J]. Acta Aerodynamica Sinica, 2015, 33(2): 178-182. (in Chinese)

LI Q C, WU K Y, ZHENG S H, et al. Investigation of dynamic test technology for a model pitching oscillation with large amplitude in high speed wind tunnels[J]. Experiments and Measurements in Fluid Mechanics, 2004, 18(4): 67-71. (in Chinese)

LI Q C, ZHAO Z L, YANG H Y, et al. Analysis of dynamic performance and test data precision of models with high angle of attack[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(8): 2594-2602. (in Chinese)

LI Q C, WU K Y, ZHAO Z L, et al. Introduction of dynamic experimental system with large amplitude in the 1.2 m×1.2 m sub-transonic wind tunnel[J]. Acta Aerodynamica Sinica, 2005, 23(3): 378-381. (in Chinese)

XU Y C, ZHENG S H. Spectrum analysis and digital fil- tering to experimental data of dynamic stall test in wind tunnel[J]. Experiment and Measurements in Fluid Mechanics, 2000, 14(3): 79-82. (in Chinese)

ZHAO Z L, YANG H Y, MA S, et al. Unsteady aerodynamic characteristics of two-degree-of-freedom pitch/roll coupled motion for a typical flying vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(12): 122375-10. (in Chinese)

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