航空学报 > 2016, Vol. 37 Issue (8): 2417-2425   doi: 10.7527/S1000-6893.2016.0154

低速风洞双自由度大幅振荡试验技术

刘春明1, 赵志军2, 卜忱1, 王建锋1, 牟伟强1   

  1. 1. 中国航空工业空气动力研究院, 哈尔滨 150001;
    2. 中国空气动力研究与发展中心, 绵阳 621000
  • 收稿日期:2016-01-25 修回日期:2016-05-23 出版日期:2016-08-15 发布日期:2016-06-12
  • 通讯作者: 刘春明,Tel.:0451-87570255。E-mail:lcmqdy@163.com E-mail:lcmqdy@163.com
  • 作者简介:刘春明,男,硕士,高级工程师。主要研究方向:风洞动态试验技术。Tel.:0451-87570255。E-mail:lcmqdy@163.com;赵志军,男,硕士,高级工程师。主要研究方向:空气动力学试验。Tel.:010-62654599。E-mail:1943223664@qq.com
  • 基金资助:

    航空科学基金(20143203002)

Double degree-of-freedom large amplitude oscillation test technology in low speed wind tunnel

LIU Chunming1, ZHAO Zhijun2, BU Chen1, WANG Jianfeng1, MU Weiqiang1   

  1. 1. AVIC Aerodynamics Research Institute, Harbin 150001, China;
    2. China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2016-01-25 Revised:2016-05-23 Online:2016-08-15 Published:2016-06-12
  • Supported by:

    Aeronautical Science Foundation of China (20143203002)

摘要:

为满足国内战斗机型号研制对大迎角过失速机动过程中非定常气动力问题研究的需求,中国航空工业空气动力研究院在FL-8风洞开发了一套基于电液伺服马达和电机耦合驱动的双自由度大幅振荡试验技术。简单介绍了该系统的基本组成和试验原理,给出了FL-8风洞动态标准模型双自由度大幅振荡试验的典型结果,分析表明:该系统运行性能稳定,试验数据可靠,重复性精度较高,可以有效应用于飞行器双自由度耦合运动气动特性研究。

关键词: 大迎角, 大振幅, 双自由度, 非定常气动力, 风洞试验

Abstract:

AVIC Aerodynamics Research Institute developed a double degree-of-freedom large amplitude oscillation testing technique based on driving technology coupled hydraulic motor and servo motor in FL-8 wind tunnel in order to study the aircraft unsteady aerodynamics during post maneuver at high angle-of-attack. This paper presents the basic components and test principle, as well as the FL-8 wind tunnel test results of the standard model test. It is indicated that the system has high stability, reliability and repeatability precision. The technology can be effectively applied to studying and predicting the aerodynamic characteristics of double degree-of-freedom coupled motion.

Key words: high angle-of-attack, large amplitude oscillation, double degree-of-freedom, unsteady aerodynamics, wind tunnel test

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