基于弹性边界的多墙式盒段结构复合材料壁板屈曲分析方法

赵北; 熊斯浚; 陈亮; 王成波; 李锐

doi:10.21656/1000-0887.440283

基于弹性边界的多墙式盒段结构复合材料壁板屈曲分析方法

doi: 10.21656/1000-0887.440283

赵北^1,2,
熊斯浚^1,3,
陈亮^3,4,
王成波^3,4,
李锐^1,4, ,

1. 大连理工大学工程力学系工业装备结构分析优化与CAE软件全国重点实验室，辽宁大连 116024;
2. 中国航空工业集团公司成都飞机设计研究所强度部，成都 610091;
3. 中国航空工业集团公司沈阳飞机设计研究所综合强度部，沈阳 110035;
4. 辽宁省飞行器结构强度数字孪生重点实验室，沈阳 110035

基金项目:

国家自然科学基金（12372067；12022209）

详细信息

作者简介:
赵北（1998—），男，助理工程师（E-mail: zhaobei1998@163.com）；熊斯浚（1994—），男，工程师（E-mail: xiongsijun@mail.dlut.edu.cn）；陈亮（1977—），男，研究员（E-mail: liangchen110035@163.com）；王成波（1977—），男，正高级工程师（E-mail: chengbowang110035@163.com）；李锐（1985—），男，教授，博士，博士生导师(通讯作者. E-mail: ruili@dlut.edu.cn).

通讯作者:
李锐（1985—），男，教授，博士，博士生导师(通讯作者. E-mail: ruili@dlut.edu.cn).

中图分类号: O343.9
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出版历程
- 收稿日期: 2023-09-20
- 修回日期: 2024-05-27
- 网络出版日期: 2024-09-30

A Buckling Analysis Method for Composite Panels in Multiweb Box Structures Based on Elastic Boundaries

ZHAO Bei^1,2,
XIONG Sijun^1,3,
CHEN Liang^3,4,
WANG Chengbo^3,4,
LI Rui^{1,4
, ,}

1. State Key Laboratory of Structural Analysis, Optimization and CAE Software for Industrial Equipment, Department of Engineering Mechanics, Dalian University of Technology, Dalian, Liaoning 116024, P.R.China;
2. Department of Strength, AVIC Chengdu Aircraft Design and Research Institute, Chengdu 610091, P.R.China;
3. Department of Strength, AVIC Shenyang Aircraft Design and Research Institute, Shenyang 110035, P.R.China;
4. Key Laboratory of Digital Twin for Aircraft Structural Strength, Liaoning Province, Shenyang 110035, P.R.China

Funds:

The National Science Foundation of China(12372067；12022209)

摘要

摘要: 机翼中的多墙式盒段结构是飞机结构设计的重点关注区域之一.盒段结构主要由蒙皮以及支撑件组合而成，其中蒙皮被支撑件近似分隔为多个矩形壁板.在飞机服役过程中，机翼主要承受弯曲、扭转或者弯扭耦合载荷等作用，导致盒段结构中矩形壁板容易产生失稳.在传统复合材料壁板屈曲分析中，往往将边界简化为固支或简支，所得结果与试验差距较大，而采用有限元方法进行全面模拟往往效率较低.针对上述问题，该文提出了一种结合单胞模型以及微分求积法的复合材料壁板快速屈曲分析方法.首先，建立了单胞模型计算矩形壁板的弹性边界刚度系数；然后，通过微分求积法求解控制方程，获得了壁板的屈曲载荷；最后，计算了不同类型盒段结构中复合材料壁板的屈曲载荷，并与有限元结果进行对比，验证了该文屈曲分析方法的准确性.
- 复合材料壁板 /
- 弹性边界 /
- 屈曲 /
- 微分求积法
Abstract: The multiweb box structures in the wings are paid special attention in aircrafts’ structural design. The multiweb box is mainly composed of skins and stiffeners. The skins are approximately divided into many rectangular panels by stiffeners. During the service of an aircraft, the wing majorly bears bending, torsion, and bending-torsion coupling loads, etc., so the panels in box structures are susceptible to instability. In traditional buckling analysis of composite panels, the boundary conditions were typically simplified as either clamped or simply supported boundaries, with significant deviations from experimental results. On the other hand, comprehensive simulations with the finite element method are generally inefficient. Aimed at the above issues, a rapid buckling analysis method combining the unit cell model with the differential quadrature method for composite panels was proposed. Firstly, the unit cell model was established to calculate the stiffness coefficients of elastic boundaries of rectangular panels. The governing equations were then solved with the differential quadrature method to obtain the buckling loads on the panels. Finally, the buckling loads on composite panels in different types of box structures were calculated and compared to the results obtained with the finite element method to verify the accuracy of the presented buckling analysis method.
- composite panel /
- elastic boundary /
- buckling /
- differential quadrature method

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