摘要
碳纤维增强复合材料的失效机理复杂,试验成本高昂。受限于现有理论模型,传统的有限元方法难以精确模拟复合材料失效全过程,并存在显著的累积误差,造成了其精确模拟和不确定性量化的困难。机器学习方法为解决这一问题提供了潜在途径,但其有效性通常依赖于大量数据支撑。提出了一种多保真度数据驱动预测框架,旨在通过结合少量高保真度试验数据与大量低保真度仿真数据,实现对复合材料结构力学性能分布的准确预测。该框架的有效性经过切口层合板拉伸破坏试验验证。此外,为提高小样本试验数据的统计代表性,提出了一种基于贝叶斯理论的数据扩充方法,并推导了组间变异系数的理论分布以验证其有效性。交叉验证结果表明,所提方法在预测破坏载荷分布第10百分位数时的平均绝对误差率仅为4.99%。该研究有效缓解了复合材料结构性能预测过程中数值模型与物理试验数据关联困难及试验数据稀缺的问题。
The failure mechanisms of carbon-fiber-reinforced composites are complex,and experimental tests are costly.Traditional finite element methods,limited by current theoretical models,struggle to accurately simulate the en-tire failure process and exhibit significant cumulative errors,complicating precise modeling and uncertainty quantifica-tion.Machine learning approaches offer a promising alternative but generally require extensive datasets to achieve sat-isfactory performance.We present a multi-fidelity data-driven framework that blends a small set of high-fidelity test re-sults with an extensive collection of low-fidelity simulation data to predict the distribution of mechanical properties in composite structures.The framework is validated through tensile-failure experiments on notched laminates.To im-prove the statistical representativeness of the limited experimental samples,we introduce a Bayesian data-augmentation scheme and derive the theoretical distribution of the inter-group coefficient of variation to confirm its soundness.Cross-validation shows that the proposed method attains a mean absolute error of 4.99%when predicting the 10th percentile of the failure-load distribution.The study mitigates the twin challenges of scarce experimental data and weak coupling between numerical models and physical tests.
作者
唐铠瑞
王喆
陈向明
崔保让
陈艳辉
陈普会
TANG Kairui;WANG Zhe;CHEN Xiangming;CUI Baorang;CHEN Yanhui;CHEN Puhui(State Key Laboratory of Mechanics and Control of Mechanical Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China;National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi'an 710065,China;Center of Composite Materials,COMAC Shanghai Aircraft Manufacturing Company Limited,Shanghai 200123,China)
出处
《航空学报》
北大核心
2025年第21期231-248,共18页
Acta Aeronautica et Astronautica Sinica
关键词
复合材料
切口层合板
贝叶斯理论
多保真度方法
破坏载荷分布预测
composite materials
notched laminates
Bayesian theory
multi-fidelity methods
failure load distribution prediction
