北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (9): 1927-1935.doi: 10.13700/j.bh.1001-5965.2015.0586

• 论文 • 上一篇    下一篇

直升机行星架疲劳裂纹扩展寿命预测

范磊1,2, 王少萍1, 张超1, 孔德贺2, 毛阳3   

  1. 1. 北京航空航天大学 自动化科学与电气工程学院, 北京 100083;
    2. 中国人民解放军61267部队, 北京 101114;
    3. 中国人民解放军总参谋部陆航部军事代表局, 北京 100050
  • 收稿日期:2015-09-09 出版日期:2016-09-20 发布日期:2016-09-29
  • 通讯作者: 王少萍,Tel.:010-82338933,E-mail:shaopingwang@vip.sina.com E-mail:shaopingwang@vip.sina.com
  • 作者简介:范磊,男,博士研究生。主要研究方向:机电系统可靠性、故障诊断及寿命预测。Tel.:010-82338917,E-mail:leifan@buaa.edu.cn;王少萍,女,博士,教授,博士生导师。主要研究方向:机电系统故障诊断、容错与可靠性、加速寿命试验、机电系统控制与仿真。Tel.:010-82338933,E-mail:shaopingwang@vip.sina.com
  • 基金资助:
    国家“973”计划(2014CB046402);国家自然科学基金(51175014)

Life prediction of helicopter planetary carrier plate fatigue crack propagation

FAN Lei1,2, WANG Shaoping1, ZHANG Chao1, KONG Dehe2, MAO Yang3   

  1. 1. School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
    2. Troop 61267 of People's Liberation Army, Beijing 101114, China;
    3. Army Aviation Military Representative Bureau of PLA General Staff, Beijing 100050, China
  • Received:2015-09-09 Online:2016-09-20 Published:2016-09-29
  • Supported by:
    National Basic Research Program of China (2014CB046402); National Natural Science Foundation of China (51175014)

摘要: 直升机行星齿轮保持架(简称行星架)是传动系统的重要部件,其可靠性对于直升机的飞行安全至关重要。行星架疲劳裂纹故障的发生、发展受多种因素影响,其故障诊断和寿命预测都有难度。为准确预测行星架疲劳裂纹寿命,研究了其裂纹故障发生、发展规律,提出了基于对数线性的方法,将裂纹扩展过程离散化处理,采用Paris公式,定量描述裂纹扩展速率,结合Miner准则,累积其疲劳损伤过程,最终得到随裂纹长度变化的行星架剩余使用寿命数值。利用有限元软件ANSYS Workbench的疲劳寿命模块对计算得到的数值结果进行了仿真对比,验证了方法的精确性和有效性。

关键词: 直升机行星架, 疲劳裂纹扩展, 剩余寿命预测, 对数线性, Miner准则, 累积损伤, Paris公式

Abstract: Planetary carrier plate (referred to as the carrier) is one of the most important components of a helicopter transmission system, and its reliability is critical for the helicopter flight safety. Subjected to a variety of factors, the development of the carrier fatigue crack fault is difficult to be diagnosed or prognosed. In order to predict the fatigue crack life of the carrier, crack fault mechanism is studied and a log-linear method is developed in this paper. The crack propagation process is discretized by combining the Paris law with Miner rule, then the fatigue crack damage is accumulated. And the value of the cracked carrier remaining service life corresponding to different crack length is obtained. Calculated numerical results are compared with simulation data using the commercial finite element software ANSYS Workbench fatigue life calculation module, which validates good accuracy and effectiveness of the developed method in predicting the remaining life of a cracked carrier.

Key words: helicopter planetary carrier plate, fatigue crack propagation, remaining life prediction, log-linear, Miner rule, cumulative damage, Paris law

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