航空电连接器接触件疲劳寿命的可靠性分析

doi:10.7527/S1000-6893.2018.22123

固体力学与飞行器总体设计

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航空电连接器接触件疲劳寿命的可靠性分析

杨强^1,2, 闻聪聪¹, 孙志礼¹, 张孟君³

1. 东北大学机械工程与自动化学院, 沈阳 110819;
2. 东北大学航空动力装备振动及控制教育部重点实验室, 沈阳 110819;
3. 沈阳兴华航空电器有限责任公司, 沈阳 110144

收稿日期:2018-03-08 修回日期:2018-06-07 出版日期:2018-10-15 发布日期:2018-06-15
通讯作者: 杨强 E-mail:qiangyang@mail.neu.edu.cn
基金资助:
国家自然科学基金（51205052）；航空科学基金（20170250001）；中央高校基本科研业务费专项资金（N160304008）；中国博士后科学基金（2014M561244）

Reliability analysis of fatigue life of aviation electrical connector contact parts

YANG Qiang^1,2, WEN Congcong¹, SUN Zhili¹, ZHANG Mengjun³

1. College of Mechanical Engineering & Automation, Northeastern University, Shenyang 110819, China;
2. Key Laboratory of Aero Equipment Vibration and Control of Ministry of Education, Northeastern University, Shenyang 110819, China;
3. Shenyang Xinghua Aero-Electric Appliance Co., Ltd., Shenyang 110144, China

Received:2018-03-08 Revised:2018-06-07 Online:2018-10-15 Published:2018-06-15
Supported by:
National Natural Science Foundation of China (51205052); Aeronautical Science Foundation of China (20170250001),The Fundamental Research Funds for the Central Universities (N160304008); China Postdoctoral Science Foundation (2014M561244)

摘要/Abstract

摘要： 为研究电连接器接触件疲劳寿命的可靠性问题，以某型军用航空电连接器通用接触件插针插孔为研究对象，应用有限元软件ABAQUS计算了接触件单次插拔过程中的接触性能。基于断裂力学理论，根据受力状况建立了接触件疲劳失效物理模型，进而联合疲劳分析软件FE-SAFE建立了接触件疲劳寿命的仿真计算模型。考虑插孔关键结构尺寸制造误差和插孔插针配合误差的随机性，利用蒙特卡罗抽样法随机构造初始装配模型并仿真计算对应的疲劳寿命，进而统计得出了接触件疲劳寿命的分布类型和分布参数，建立了电连接器接触件疲劳寿命的可靠性分析模型。结果表明：所建模型可实现电连接器任意次插拔后疲劳寿命小于许用寿命的可靠度预测，能对电连接器在许用寿命条件下2种误差的许用极限进行有效限定，可为电连接器接触件的可靠性设计、制造和装配提供理论参考。

关键词: 电连接器, 接触件, 疲劳寿命, 可靠性, 有限元仿真

Abstract: To study the reliability problem of fatigue life of the electrical connector, the mechanical properties of the pin and jack of a military aviation electrical contact part in a single plugging-pulling process are calculated using the finite element analysis software ABAQUS. A physical model for the fatigue failure of the contact part is established according to the load case. Then, a simulation calculation model of fatigue life of the contact part is built by combining the fatigue analysis software FE-SAFE and the ABAQUS. The initial model is constructed utilizing the Monte Carlo sampling method while considering the randomness of the manufacture error of critical structural parameters of the jack and the mating error of the pin and the jack. In addition, the corresponding fatigue life is calculated by the simulation method, and then its distribution type and distributing parameters are obtained. Finally, the reliability analysis model for fatigue life of the contact part is established. Analysis result shows that the model established in this paper can realize reliability prediction of the electrical connector after arbitrary times of plugging-pulling when the fatigue life is less than the allowable life, and the two types of errors can be defined effectively utilizing the quantitative evaluation model of fatigue life of the electrical connector under the allowable life condition. The model proposed can provide some reference to reliability design, manufacture, and assembly of the electrical connector.

Key words: electrical connector, contact parts, fatigue life, reliability, finite element simulation

中图分类号:

V240.2
TH112

杨强, 闻聪聪, 孙志礼, 张孟君. 航空电连接器接触件疲劳寿命的可靠性分析[J]. 航空学报, 2018, 39(10): 222123-222123.

YANG Qiang, WEN Congcong, SUN Zhili, ZHANG Mengjun. Reliability analysis of fatigue life of aviation electrical connector contact parts[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(10): 222123-222123.

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E-mail：hkxb@buaa.edu.cn

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航空电连接器接触件疲劳寿命的可靠性分析

Reliability analysis of fatigue life of aviation electrical connector contact parts

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