航空学报 > 2022, Vol. 43 Issue (7): 426585-426585   doi: 10.7527/S1000-6893.2021.26585

振动疲劳载荷谱编制与试验验证

毛森鑫1, 时寒阳2, 李开响3, 张晓1, 朱云涛3, 杜娟1, 邹康庄1, 熊峻江3   

  1. 1. 航空工业陕西飞机工业有限责任公司, 汉中 723213;
    2. 西安航天动力研究所 液体火箭发动机技术重点实验室, 西安 710100;
    3. 北京航空航天大学 交通科学与工程学院, 北京 100083
  • 收稿日期:2021-10-28 修回日期:2021-12-03 发布日期:2021-12-01
  • 通讯作者: 朱云涛,E-mail:ytzhu@buaa.edu.cn E-mail:ytzhu@buaa.edu.cn
  • 基金资助:
    国家自然科学基金(51875021)

Vibration fatigue load spectrum compilation and test verification

MAO Senxin1, SHI Hanyang2, LI Kaixiang3, ZHANG Xiao1, ZHU Yuntao3, DU Juan1, ZOU Kangzhuang1, XIONG Junjiang3   

  1. 1. AVIC Shaanxi Aircraft Industry Corporation Ltd., Hanzhong 723213, China;
    2. Science and Technology on Liquid Rocket Engine Laboratory, Xi'an Aerospace Propulsion Institute, Xi'an 710100, China;
    3. School of Transportation Science and Engineering, Beihang University, Beijing 100083, China
  • Received:2021-10-28 Revised:2021-12-03 Published:2021-12-01
  • Supported by:
    National Natural Science Foundation of China (51875021)

摘要: 根据雨流计数法、快速傅里叶变换方法和Miner法则,提出了基于时域和频域概念的振动疲劳载荷谱编制原理,并进行了2种航空材料的时域和频域振动疲劳载荷原谱和加速谱对比试验,验证了编谱方法的有效性。建立了某型飞机平尾结构有限元分析模型,进行了振动疲劳载荷识别,再采用提出的振动疲劳编谱方法,编制了某型飞机平尾结构的振动疲劳载荷原谱和加速谱,用于全尺寸振动疲劳试验。平尾振动疲劳编谱结果表明:振动载荷原谱和加速谱下平尾疲劳损伤相对偏差小于5%,加速效率高达80%,可大幅降低试验成本。

关键词: 振动疲劳, 载荷谱, 时域, 频域, 加速试验

Abstract: Time-and frequency-domain methods are proposed to compile actual and accelerated vibration fatigue load spectrums by incorporating rain-flow counting algorithm, Fast Fourier Transform(FFT) and Miner rule. Comparative vibration fatigue tests(in axial and lateral direction) are conducted on two kinds of aeronautical metals under actual and accelerated time-and frequency-domain vibration fatigue load spectrums, demonstrating the practice and effective usage of compiling methods. After this, finite element model is generated to calculate the correlation between acceleration response and vibration loads of an aircraft horizontal tail, and the validity of finite element model is verified through modal analysis. Then, actual and accelerated vibration fatigue load spectrums of horizontal tail are compiled for full-scale vibration fatigue tests using the above compilation method. It is shown that the relative deviation between fatigue damage resulted from actual and accelerated vibration fatigue load spectrums is less than 5%, but accelerated efficiency is about 80%.

Key words: vibration fatigue, load spectrum, time-domain, frequency-domain, accelerated test

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