2.4 m跨声速风洞大振幅动态试验技术

马上; 赵忠良; 蒋明华; 杨海泳; 刘维亮; 李玉平; 王晓冰

doi:10.7638/kqdlxxb-2018.0151

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2.4 m跨声速风洞大振幅动态试验技术

研究论文 | 更新时间：2026-05-28

- 2.4 m跨声速风洞大振幅动态试验技术
- Dynamic test technique with large amplitude in 2.4 m transonic wind tunnel
- 空气动力学学报 2019年37卷第6期页码：998-1003
- 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：
  
  马上(1985-), 男, 陕西户县人, 工程师, 研究方向:非定常空气动力学.E-mail:mashang693@163.com
  赵忠良(1964-), 男, 重庆人, 研究员, 主要研究方向:非定常空气动力学.E-mail:zzzhao_cardc@sina.com
- 基金信息：
  
  国家自然科学基金（11532016）
- DOI：10.7638/kqdlxxb-2018.0151
  中图分类号： V211.7
- 纸质出版：2019
- 稿件说明：
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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.

关键词

Keywords

references

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