融合几何与网格信息的仿真模型快速重构方法

李红庆; 倪晨君; 王博; 蔡永明; 张音旋; 陈亮; 田阔

doi:10.21656/1000-0887.460030

融合几何与网格信息的仿真模型快速重构方法

doi: 10.21656/1000-0887.460030

李红庆^1,,
倪晨君¹,
王博^{1, 2},
蔡永明^{2, 3},
张音旋^{2, 3},
陈亮^{2, 3},
田阔^{1, 2, ,}

1.
大连理工大学工程力学系, 辽宁大连 116024
2.
辽宁省飞行器结构强度数字孪生重点实验室, 沈阳 110035
3.
航空工业沈阳飞机设计研究所, 沈阳 110035

基金项目:

国家自然科学基金 U21A20429

陕西省自然科学基础研究计划 2025SYS-SYSZD-102

辽宁省优秀青年基金 2024JH3/10200003

详细信息

作者简介:
李红庆(1997—)，男，博士生(E-mail: HongQ.Li@mail.dlut.edu.cn)

通讯作者:
田阔(1989—)，男，教授，博士生导师(通讯作者. E-mail: tiankuo@dlut.edu.cn)

中图分类号: O39
计量
- 文章访问数: 46
- HTML全文浏览量: 6
- PDF下载量: 9
- 被引次数: 0
出版历程
- 收稿日期: 2025-02-21
- 修回日期: 2025-03-09
- 刊出日期: 2025-08-01

A Fast Re-Modelling Method for Simulation Models by Fusing Geometric Information and Simulation Information

LI Hongqing^1
,,
NI Chenjun¹,
WANG Bo^{1, 2},
CAI Yongming^{2, 3},
ZHANG Yinxuan^{2, 3},
CHEN Liang^{2, 3},
TIAN Kuo^{1, 2
, ,}

1.
Department of Engineering Mechanics, Dalian University of Technology, Dalian, Liaoning 116024, P. R. China
2.
Liaoning Provincial Key Laboratory of Digital Twins for Aircraft Structural, Shenyang 110035, P. R. China
3.
AVIC Shenyang Aircraft Design and Research Institute, Shenyang 110035, P. R. China

摘要

摘要: 复杂结构的设计迭代过程中，往往涉及大量的重建模与重分析，导致计算成本较高且耗时较长. 针对这一挑战，该文提出了一种融合几何与网格信息的仿真模型快速重构方法. 该方法通过精确捕捉复杂几何模型的结构特征并进行数字化表达，进而训练几何模型的特征信息驱动仿真模型进行自动重构. 首先，引入拟共形映射技术对复杂曲面进行平面参数化，通过栅格采样技术获取平面控制点，根据映射前后对应关系生成曲面控制点，作为结构特征的数字化表达；其次，利用径向基函数算法，对修改前后几何模型的控制点进行训练，通过网格映射技术实现对仿真模型的自动化重构. 最后，为了验证所提出方法的有效性，以飞机隔框结构作为典型算例进行研究. 与传统的仿真模型重构方法相比，最大应力误差仅为0.87%. 所需的人机操作步数减少95.40%，模型重构耗时减少96.67%. 结果表明，所提出方法在保证仿真精度的同时，显著降低了仿真模型重构的时间，实现了基于几何与网格模型映射孪生的快速设计.
- 复杂结构 /
- 快速重构 /
- 拟共形映射 /
- 控制点生成 /
- 数字孪生
Abstract: In the design iteration process of complex structures, a large amount of re-modelling and re-analysis is often involved, leading to high computational costs and long processing periods. To address this challenge, a fast re-modelling method for simulation models was proposed by fusing geometric and mesh information. The method can accurately capture and digitally represent the structural features of the complex geometric model. Then, the feature information of the geometric model was trained to drive the automatic re-modelling of the simulation model. Firstly, the quasi-conformal mapping technique was introduced to parameterize the complex surfaces. A fixed number of control points were obtained through the voxel sampling, as a digital representation of the structural features. Secondly, the radial basis function algorithm was used to train the control points of the geometric model before and after modification. The automated re-modelling of the simulation model was realized with the mesh-mapping technique. Finally, to verify the effectiveness and practicality of the proposed method, an aircraft frame structure was used as a case study. Compared with the traditional re-modelling method, the proposed method has a simulation analysis error level of stress at only 0.87%. The number of required human-computer interaction steps decreases by 95.40% and the operation time reduces by 96.67%. The results show that, the proposed method significantly reduces the simulation model re-modelling time while ensuring the simulation accuracy, which achieves the rapid design based on the digital twin between geometric and mesh models.
- complex structure /
- fast re-modelling /
- quasi-conformal mapping /
- control point generation /
- digital twin

HTML全文

图 1 传统模型重构方法与所提出方法技术路线

Figure 1. Technology roadmaps of the traditional re-modelling method and the proposed method

下载: 全尺寸图片幻灯片

图 2 拟共形映射方法示意图

Figure 2. Schematic diagram of the quasi-conformal mapping method

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图 3 基于栅格采样的控制点生成方法示意图

Figure 3. Schematic diagram of the control point generation method based on the voxel sampling

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图 4 融合几何与网格信息的仿真模型快速重构方法示意图

Figure 4. Schematic of the fast re-modelling method for simulation models fusing geometric and mesh information

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图 5 飞机隔框结构示意图

Figure 5. Schematic diagram of the aircraft frame structure

下载: 全尺寸图片幻灯片

图 6 修改前后飞机隔框结构几何模型示意图

Figure 6. Schematic diagram of geometric model for the aircraft frame structure before and after modification

下载: 全尺寸图片幻灯片

图 7 几何模型修改前后的隔框结构局部面片组

注为了解释图中的颜色，读者可以参考本文的电子网页版本，后同.

Figure 7. Schematic diagram of the face groups for the aircraft frame structure before and after modification

下载: 全尺寸图片幻灯片

图 8 隔框结构修改前后局部面片组对应控制点

Figure 8. Schematic diagram of the control points for the aircraft frame structure before and after modification

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图 9 隔框结构修改前后网格模型

Figure 9. Schematic diagram of the mesh models for the aircraft frame structure before and after modification

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图 10 修改后隔框结构应力与位移云图

Figure 10. Stress and displacement distribution diagrams of the aircraft frame structure after modification

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表 1 不同模型重构方法对比

Table 1. Comparison of results for different re-modelling methods

	maximum displacement/mm	maximum stress/MPa	consumed time/h	steps number of human-computer interaction
traditional method	0.11	249.81	1.50	87
proposed method	0.11	247.65	0.05	4
comparison/%	0.00	-0.87	-96.67	-95.40

下载: 导出CSV

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