Prediction of Riveting Deformation of Aircraft Panel Using Local-Global Mapping Approach

doi:10.7652/xjtuxb201801017

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Prediction of Riveting Deformation of Aircraft Panel Using Local-Global Mapping Approach

更新时间：2025-07-09

- Prediction of Riveting Deformation of Aircraft Panel Using Local-Global Mapping Approach
- Vol. 52, Issue 1, Pages: 115-122(2018)
- 作者机构：
  
  西北工业大学机电学院,西安,710072
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb201801017
  CLC： V262.4
- Online First：10 January 2018，
  
  Published：2018
- 稿件说明：
移动端阅览
Prediction of Riveting Deformation of Aircraft Panel Using Local-Global Mapping Approach[J]. 2018, 52(1): 115-122.
DOI：

Prediction of Riveting Deformation of Aircraft Panel Using Local-Global Mapping Approach[J]. 2018, 52(1): 115-122. DOI： 10.7652/xjtuxb201801017.

摘要

针对现有壁板铆接变形预测方法预测精度低、计算周期长的问题

提出了一种采用局部-整体映射模型的壁板铆接变形预测方法。依据壁板装配工艺流程分析

确定了引起壁板铆接变形的主要原因; 结合增扩自由度法

解决了壁板铆接体-壳连接建模中的应力不协调问题

并用于构建壁板铆接局部-整体映射模型; 基于局部-整体映射模型

将钉孔周围复杂的应力应变状态传递到壁板整体薄壳模型上

实现了壁板铆接变形预测。计算结果表明:在十钉铆接结构中

与全实体动态铆接模型相比

单钉的平均计算时间从55 min降为15 min

变形分布与大小基本相同; 某壁板变形预测结果与实验结果相比

测量点的最大变形值偏差为0.062 mm

平均偏差为0.01 mm

相关性系数为0.898。该模型显著提高了计算效率

且具有有效性

为进一步铆接变形的控制研究提供了理论依据。

Abstract

A novel prediction method of riveting deformation of aircraft panels is proposed to solve the problems of low prediction accuracy and long calculation time in existing prediction methods. Through the analysis on the panel assembly process

the major causes of the panel deformation are identified. Combining with the DOF expanding method

the additional stress arising in the normal connection method is avoided. Then the method is used to establish a local-global mapping model. Based on this model

the complex stress-strain state around the rivet hole is transferred to the thin shell model of panel in a relatively simple way. Finally

the prediction of riveting deformation of large panel is achieved. The results show that

compared with dynamic explicit finite element model

the average calculation time of a single rivet is decreased from 55 minutes to 15 minutes

and the deformation distribution and magnitude of ten-rivet structure are basically identical. Comparing the predicted results with experimental results of a aircraft panel

the deviation of maximum deformation values is 0.062 mm

the deviation of average deformation values is 0.01 mm

and the correlation coefficient between them is 0.898. The proposed method improves the computational efficiency and is proved effective. This study may provide a theoretical basis for the control of riveting deformation.

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Keywords

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