波纹点阵夹芯平板高温压缩行为的多尺度模拟与试验验证

张龙; 廖文林; 陈晓光; 范钧滔

doi:10.13224/j.cnki.jasp.20250296

波纹点阵夹芯平板高温压缩行为的多尺度模拟与试验验证

doi: 10.13224/j.cnki.jasp.20250296

中国空气动力研究与发展中心，四川绵阳 621000

基金项目: 四川省自然科学基金（2024NSFSC1349）

详细信息

作者简介:
张龙（1991-），男，工程师，博士，研究领域为飞行器结构设计。E-mail：zhanglong@buaa.edu.cn

通讯作者:
廖文林（1984-），男，正高级工程师，博士，研究领域为飞行器结构设计。E-mail：liaowenlin_work@163.com

中图分类号: V41；O342
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出版历程
- 收稿日期: 2025-06-20
- 网络出版日期: 2026-09-30

Multi-scale simulation and test verification for the high-temperature compression behavior of corrugated lattice sandwich panel

China Aerodynamics Research and Development Center，Mianyang 621000，China

摘要

摘要:
为了掌握高超声速飞行器防隔热/承载一体化点阵夹芯平板结构的宏细观力学响应规律，本文开展了波纹点阵夹芯平板高温压缩行为的多尺度模拟与试验验证。首先介绍了通用单胞方法（general method of cells, GMC）的基本理论；然后根据波纹点阵夹芯平板的周期性结构特征，提取其代表性体积元开展了基于通用单胞方法的多尺度模拟与宏观等效力学性能参数预测；最后，设计了高温压缩试验对本文方法进行验证。试验结果表明，本文方法预测的宏观应力应变曲线、内部细观应力分布与试验结果基本吻合，所预测的弹性模量与试验测试结果最大相对误差不超过5.0%。
- 波纹点阵夹芯平板 /
- 高温压缩 /
- 多尺度模拟 /
- 试验验证 /
- 通用单胞方法
Abstract:
In order to master the macroscopic mechanical response rules of the integrated thermal insulation and load bearing lattice sandwich panel structure of hypersonic aircraft, this paper carried out multi-scale simulation and test verification of the high-temperature compression behavior of corrugated lattice sandwich panels. First, the basic theory of general method of cells (GMC) is introduced. Then, on the basis of the periodic structural characteristics of corrugated lattice sandwich panels, the representative volume element is extracted to carry out multi-scale simulation and macroscopic effective mechanical parameters prediction based on the GMC method. In the end, a high-temperature compression test is designed to verify this developed method. It shows that the macroscopic stress strain curve and interior mesoscopic stress distribution predicted by this method are basically consistent with the test results, and the maximum relative error between the predicted elastic modulus and the test results is within 5.0%.
- corrugated lattice sandwich panel /
- high-temperature compression /
- multi-scale simulation /
- test verification /
- general method of cells

HTML

图 1 纤维增强复合材料通用单胞模型示意图

Figure 1. Sketch of GMC model for fiber reinforced composites

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图 2 波纹点阵夹芯平板的单胞提取示意图

Figure 2. Sketch of extracting RUC for corrugated lattice sandwich panel

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图 3 将原始单胞分解为单胞1和单胞2

Figure 3. Dividing original RUC into RUC1and RUC2

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图 4 单胞1的子胞划分示意图

Figure 4. Sketch of dividing RUC1 into subcells

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图 5 GMC模型多尺度模拟结果

Figure 5. Multi-scale simulated results of the GMC model

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图 6 细观有限元法模拟结果

Figure 6. Simulated results of meso-scale FEM

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图 7 波纹点阵夹芯平板高温力学性能验证试验

Figure 7. Verification test for high-temperature mechanical property of the corrugated lattice sandwich panel

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图 8 面内压缩宏观应力应变曲线对比

Figure 8. Comparison of macroscale strain-stress curves for the in-plane compression

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图 9 面外压缩宏观应力应变曲线对比

Figure 9. Comparison of macroscale strain-stress curves for the out-of-plane compression

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图 10 面内压缩内部细观应力结果对比

Figure 10. Comparison of interior mesoscale stress results for the in-plane compression

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图 11 面外压缩内部细观应力结果对比

Figure 11. Comparison of interior mesoscale stress results for the out-of-plane compression

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表 1 单胞1的宏观等效材料参数

Table 1. Macroscopic effective material property parameters for RUC1

材料性能	数值
E₁₁ /GPa	26.62
E₂₂ /GPa	9.96
E₃₃ /GPa	12.40
ν₁₂	0.33
ν₁₃	0.33
ν₂₃	0.10
G₁₂ /GPa	3.89
G₁₃ /GPa	5.45
G₂₃ /GPa	0.30

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表 2 宏观等效材料性能参数结果对比

Table 2. Comparison of macroscopic effective material property parameters

材料性能	模拟结果	测试结果
E₁₁/GPa	16.09
E₂₂/GPa	5.36	5.21（Specimen #3） 5.60（Specimen #4）
E₃₃/GPa	11.97	11.85（Specimen #1） 12.22（Specimen #2）
ν₁₂	0.18
ν₁₃	0.33
ν₂₃	0.05
G₁₂/GPa	2.09
G₁₃/GPa	5.45
G₂₃/GPa	0.16

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