考虑阶梯型接触应力分布的航空螺栓连接等效振动仿真模型

夏阳; 宋泽洋; 冯楚涵; 王友涛; 袁运博; 赵广

doi:10.13224/j.cnki.jasp.20250162

考虑阶梯型接触应力分布的航空螺栓连接等效振动仿真模型

doi: 10.13224/j.cnki.jasp.20250162

夏阳^{1, 2},
宋泽洋^{1, 2},
冯楚涵³,
王友涛⁴,
袁运博^5,*, ,,
赵广⁵

1.
大连理工大学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.
大连理工大学力学与航空航天学院辽宁大连 116024
3.
大连理工大学白俄罗斯国立大学联合学院辽宁大连 116024
4.
中国航发贵州黎阳航空动力有限公司贵阳 550014
5.
大连理工大学能源与动力学院辽宁大连 116024

基金项目: 国家自然科学基金（12572390，U2541288）

详细信息

作者简介:
夏阳（1987-），男，副教授，博士，研究领域为数值模拟方法

通讯作者:
袁运博（1993-），男，副教授，博士，主要从事传动系统动力学与故障诊断研究，E-mail：yuanyunbo@dlut.edu.cn

中图分类号: V214.41；TP391.99；TB115.1
计量
- 文章访问数: 26
- HTML浏览量: 21
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- 被引次数: 0
出版历程
- 收稿日期: 2025-04-03
- 网络出版日期: 2026-08-14

Equivalent vibration simulation model for aerospace bolted joints considering stepped contact stress distribution

Xia Yang^{1, 2},
Song Zeyang^{1, 2},
Feng Chuhan³,
Wang Youtao⁴,
Yuan Yunbo^{5,*
, ,},
Zhao Guang⁵

1.
State Key Laboratory of Structural Analysis，Optimization and CAE Software for Industrial Equipment，Dalian University of Technology，Dalian Liaoning 116024，China
2.
School of Mechanics and Aerospace Engineering，Dalian University of Technology，Dalian Liaoning 116024，China
3.
Dalian University of Technology and Belarusian State University Joint Institute，Dalian University of Technology，Dalian Liaoning 116024，China
4.
Guizhou Liyang Aviation Power Company，Limited，Aero Engine Corporation of China，Guiyang 550014，China
5.
School of Energy and Power Engineering，Dalian University of Technology，Dalian Liaoning 116024，China

摘要

摘要:
螺栓连接因其结构简洁和高可靠性，在航空设备装配中被广泛应用。螺栓连接的动态特性对装配结构的动力学行为有着显著影响，而采用详细有限元模型进行螺栓振动特性分析时计算量巨大，难以适用于复杂装配结构的分析。为解决这一问题，提出了一种阶梯型双环形薄层单元螺栓连接等效单元模型，以模拟螺栓连接面的应力分布状态。该模型由结合上部、双环形薄层单元和结合下部三部分组成，通过螺栓应力分布确定薄层单元尺寸，再通过赫兹接触理论，推导出圆环薄层单元的关键参数，包括厚度、弹性模量、泊松比和密度。随后，通过与典型航空工装的振动试验数据进行对比，验证了该模型在动力学特性仿真中的准确性。结果显示，与传统的虚拟材料法相比，提出的模型显著提高了仿真效率，且振动频率仿真误差控制在10%以内，表明该模型可有效用于螺栓连接结构的动力学仿真分析。
- 航空工装 /
- 螺栓连接 /
- 阶梯型薄层单元 /
- 振动仿真 /
- 扫频试验
Abstract:
Bolted connections are widely used in aerospace equipment assembly due to their structural simplicity and high reliability. The dynamic characteristics of bolted connections significantly influence the dynamic behavior of assembled structures. While detailed finite element models can analyze vibration characteristics, their computational cost is often prohibitively high, making them unsuitable for analyzing complex bolted assemblies. To address this issue, this study proposes an equivalent bolted connection unit model, which simplifies the bolted connection into a stepped double-ring thin-layer unit to simulate the stress distribution at the bolted interface. The model consists of three parts: the upper joint, the double-ring thin-layer unit, and the lower joint. The size of the thin-layer unit model is determined based on the bolt stress distribution, and key parameters of the ring-shaped thin-layer unit—including thickness, elastic modulus, Poisson’s ratio, and density—are derived using Hertzian contact theory. The accuracy of the proposed model in simulating dynamic characteristics is validated through comparison with vibration experimental data from a typical aerospace tooling structure. The results demonstrate that, compared to the traditional virtual material method, the proposed model significantly improves simulation efficiency while maintaining vibration frequency simulation errors within 10%. This indicates that the model is effective for dynamic simulation analysis of bolted connection structures .
- aviation tooling /
- bolted connections /
- stepped thin-layer element /
- vibration simulation /
- sweep frequency experiment

HTML

图 1 典型工装三维模型图

Figure 1. Three-dimensional model of typical tooling

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图 2 工装螺栓孔示意图（单位：mm）

Figure 2. Schematic diagram of bolt holes on the tooling （Unit: mm）

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图 3 螺栓连接处应力云图

Figure 3. Stress clouds in bolted joints

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图 4 应力分布示意图

Figure 4. Schematic of stress distribution

、

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图 5 阶梯型应力分布示意图

Figure 5. Schematic diagram of stepped stress distribution

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图 6 阶梯型圆环薄层单元

Figure 6. Stepped circular thin layer unit

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图 7 微观表面接触

Figure 7. Microscopic surface contact

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图 8 薄层单元厚度和工装第1、2阶模态的关系

Figure 8. First- and second-order modal frequencies of the tooling under different thin-layer element thicknesses

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图 9 工装振动试验

Figure 9. Vibration test setup for the tooling

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表 1 典型工装材料参数

Table 1. Material parameters of typical tooling

参数	数值
密度/（kg/m³ ）	2780
弹性模量/MPa	72000
泊松比	0.32

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表 2 工装前三阶固有频率

Table 2. First three natural frequencies of the tooling

阶数	固有频率/Hz
1阶	1289
2阶	1808
3阶	2305.5

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表 3 薄层单元不同区域特征参数

Table 3. Characterization parameters of different regions of the thin-layer unit

位置	弹性模量/Pa	等效密度/（kg/m³）	泊松比
内环	2.50	2778	0.322
外环	2.37	2769	0.319

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表 4 航空工装前三阶模态仿真振型

Table 4. Aerospace tooling front third-order modal simulation of vibration patterns

阶数	仿真振型
1阶频率为1 243 Hz
2阶频率为1 947.3 Hz
3阶频率为2 115.8 Hz

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表 5 前三阶频率结果对比

Table 5. Comparison of first three order frequency results

阶数	1阶	2阶	3阶
振动试验/Hz	1289	1 808	2305.5
阶梯型/Hz	1243	1947.3	2115.8
传统法/Hz	1475.9	2093.5	2715.6
阶梯型误差%	−3.49	7.70	−8.22
传统法误差%	14.49	15.79	17.78

下载: 导出CSV

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