Damage distribution of composite structures of a certain type aircraft

被引：0
|
作者：
Deng J. [1 ]
Chen L. [2 ]
Lu S. [2 ]
Hou Y. [2 ]
Huang W. [3 ]
Cheng X. [1 ,4 ]
机构：
[1] School of Aeronautic Science and Engineering, Beihang University, Beijing
[2] Dalian Changfeng Industrial Corporation, Dalian
[3] China Helicopter Research and Development Institute, Jingdezhen
[4] Ningbo Institute of Technology, Beihang University, Ningbo
来源：
Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2024年 / 50卷 / 03期
关键词：
aircraft; composite structure; distribution; geometric parameters; hypothesis testing; structural damage;
D O I：
10.13700/j.bh.1001-5965.2022.0379
中图分类号：
学科分类号：
摘要：
To address the damage and repair of aircraft composite structures, the applications and damage of composite structures in a certain type of aircraft, including the wing, fuselage and other components, were statistically analyzed. Structural damage distribution models with time variable were established, and then the damage distributions of the structures were fitted and tested by statistical methods. The results show that the quantitative proportions of structural damage are 75% for skin delamination, 20% for stringer delamination and 4% for stringer debonding. Lognormal distribution, Weibull distribution and Gamma distribution can all be used to fit the geometric parameter distributions of the three types of structural damage, in which the Lognormal distribution model has the best fitting effect. The distribution of structural damage geometric parameters of one aircraft does not vary with time, and the distributions of geometric parameters of the structural damage between the same type of aircraft are also highly similar, which can be expressed in a unified function form. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.
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页码：920 / 930
页数：10
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