航空学报 > 2016, Vol. 37 Issue (6): 1861-1875   doi: 10.7527/S1000-6893.2016.0075

1200℃高温环境下板结构热模态试验研究与数值模拟

吴大方, 王岳武, 商兰, 蒲颖, 王怀涛   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2015-11-17 修回日期:2016-03-10 出版日期:2016-06-15 发布日期:2016-03-16
  • 通讯作者: 吴大方 男,博士,教授,博士生导师。主要研究方向:高速飞行器结构热防护,结构振动主动控制,实验力学。Tel:010-82317507 E-mail:wdf1950@163.com E-mail:wdf1950@163.com
  • 作者简介:王岳武 男,博士研究生。主要研究方向:实验力学。Tel:010-82317507 E-mail:wangyuewu@buaa.edu.cn
  • 基金资助:

    国家自然科学基金(11427802)

Test research and numerical simulation on thermal modal of plate structure in 1200℃ high-temperature environments

WU Dafang, WANG Yuewu, SHANG Lan, PU Ying, WANG Huaitao   

  1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China
  • Received:2015-11-17 Revised:2016-03-10 Online:2016-06-15 Published:2016-03-16
  • Supported by:

    National Natural Science Foundation of China (11427802)

摘要:

高超声速飞行器高马赫数飞行时,翼、舵及垂尾等板形姿态控制结构将会面临极为严酷的高温环境,为了获得难于实测的结构在高温与振动复合环境下的热模态参数,本文将瞬态气动热试验模拟系统与振动试验系统相结合,建立了高温热/振联合试验测试系统,实现了高达1200℃热环境下矩形板结构的模态频率等关键振动参数的试验测试。同时,对矩形板结构的热模态特性进行了数值计算,并将试验结果与计算结果进行对比验证。试验中通过自行研制的耐高温陶瓷导杆引伸装置将结构上的振动信号传递至高温热场之外,使用常温加速度传感器对振动信号进行参数识别;并运用时-频联合分析技术对试验数据进行分析处理。本文所获得的高温环境(200~1100℃)下矩形板结构的模态频率的试验结果与数值计算结果取得了比较好的一致性,验证了本试验方法的可信性及可用性。本研究结果为高超声速飞行器翼舵结构在高温环境下的振动特性分析以及安全可靠性设计提供了重要的试验手段和参考依据。

关键词: 高超声速飞行器, 热模态试验, 数值计算, 高温环境, 振动特性

Abstract:

When the hypersonic aircraft flies at a high Mach number, the plate-like attitude control structures, such as the wings and rudders, will be exposed to an extremely high-temperature environment. In this paper, in order to obtain the thermal modal parameters of structure that are difficult to measure, high-temperature transient heating test system and vibration test system are combined to establish a thermal/vibration test system and the experimental measurement for key vibration characteristic parameters of structure in a thermal-vibration coupled environment up to 1200℃ (e.g. the modal frequency and modal vibration shape) is performed. Meanwhile, the numerical simulation on the thermal modal characteristics of rectangular plate is carried out and the test results are compared with the numerical results. In the test, a self-developed extension configuration of high-temperature-resistant ceramic pole is used to transfer the vibration signals of structure to nonhigh temperature zone, and the acceleration sensors are applied to identifying the vibration signals. Test data are analyzed by a time-frequency joint analysis technique. The tested modal frequencies of the plate in high temperature environments ranging from 200℃ to 1100℃ coincide favorably with calculated results, which verifies the credibility and effectiveness of the proposed experimental methods. The research results can provide an important basis for the dynamic performance analysis and safety design of structure under high-temperature thermal-vibration conditions for hypersonic aircraft.

Key words: hypersonic aircraft, thermal modal test, numerical calculation, high-temperature environments, vibration characteristics

中图分类号: