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加筋复合材料结构分层损伤的贝叶斯诊断及预测

陈健 袁慎芳

陈健, 袁慎芳. 加筋复合材料结构分层损伤的贝叶斯诊断及预测[J]. 复合材料学报, 2021, 38(11): 3726-3736. doi: 10.13801/j.cnki.fhclxb.20210202.003
引用本文: 陈健, 袁慎芳. 加筋复合材料结构分层损伤的贝叶斯诊断及预测[J]. 复合材料学报, 2021, 38(11): 3726-3736. doi: 10.13801/j.cnki.fhclxb.20210202.003
CHEN Jian, YUAN Shenfang. Bayesian diagnosis and prognosis of delamination damage in the stiffened composite structure[J]. Acta Materiae Compositae Sinica, 2021, 38(11): 3726-3736. doi: 10.13801/j.cnki.fhclxb.20210202.003
Citation: CHEN Jian, YUAN Shenfang. Bayesian diagnosis and prognosis of delamination damage in the stiffened composite structure[J]. Acta Materiae Compositae Sinica, 2021, 38(11): 3726-3736. doi: 10.13801/j.cnki.fhclxb.20210202.003

加筋复合材料结构分层损伤的贝叶斯诊断及预测

doi: 10.13801/j.cnki.fhclxb.20210202.003
基金项目: 国家自然科学基金创新群体项目(51921003);国家自然科学基金重点项目(51635008);江苏省重点研发计划(BE2018123);江苏高校优势学科建设工程资助项目
详细信息
    通讯作者:

    袁慎芳,博士,教授,博士生导师,研究方向为飞行器结构健康监测和智能结构  E-mail:ysf@nuaa.edu.cn

  • 中图分类号: TB332

Bayesian diagnosis and prognosis of delamination damage in the stiffened composite structure

  • 摘要: 针对复合材料结构疲劳损伤的在线监测和预测问题,提出了一种基于结构健康监测 (Structural health monitoring, SHM) 和贝叶斯理论的结构分层损伤诊断及结构剩余使用寿命预测方法。在贝叶斯概率理论框架下,采用指数模型描述复合材料结构疲劳分层损伤面积的先验演化规律,融合在线SHM数据对结构分层损伤状态,以及损伤面积演化模型的参数进行联合后验估计,即为损伤诊断结果。进一步通过后验估计得到的损伤状态和模型参数预测未来时刻结构分层损伤面积的演化,从而得到当前复合材料结构的剩余使用寿命预测结果。通过有限元仿真的加筋复合材料结构疲劳分层扩展对所提出的方法进行了验证。结果表明,方法可以在线准确地诊断结构分层损伤状态以及预测结构的剩余使用寿命。

     

  • 图  1  基于贝叶斯理论的分层损伤诊断和预测方法流程图

    Figure  1.  Flowchart of the Bayesian theory-based delamination diagnosis and prognosis method

    图  2  仿真的碳纤维增强环氧树脂基复合材料加筋板

    Figure  2.  Simulated stiffened panel made of carbon fiber reinforced epoxy resin matrix composites

    图  3  复合材料加筋板的有限元模型及其初始分层设置

    Figure  3.  Finite element model of the stiffened composite panel and its initial delamination setting

    图  4  复合材料加筋板算例T25的仿真分层损伤扩展情况

    Figure  4.  Simulated delamination growth in the case T25 of the stiffened composite panel

    图  5  典型复合材料加筋板仿真算例中损伤变量随循环载荷数的变化

    Figure  5.  Damage variables during the fatigue delamination growth in typical simulation cases of the stiffened composite panel

    图  6  模拟光纤光栅(FBG)应变传感器布置

    Figure  6.  Layout of the simulated fiber Bragg grating (FBG) sensor

    图  7  通过模拟FBG传感器获得的复合材料加筋板应变数据示例

    Figure  7.  Example of the strain data of the stiffened composite panel collected from the simulated FBG sensor

    图  8  通过复合材料加筋板算例T1~T35仿真数据得到的分层损伤面积演化模型参数

    Figure  8.  Delamination area progression model parameters evaluated with the simulation data from the cases T1-T35 of the stiffened composite panel

    图  9  复合材料加筋板人工神经网络(ANN)观测模型典型应变输出结果

    Figure  9.  Typical strain output of the artificial neural network (ANN) measurement model for the stiffened composite panel

    图  10  复合材料加筋板算例V1的疲劳分层损伤面积诊断结果

    Figure  10.  Diagnosis results of the fatigue delamination area in the case V1 of the stiffened composite panel

    图  11  复合材料加筋板算例V1的疲劳分层损伤位置的诊断结果

    Figure  11.  Diagnosis results of the fatigue delamination location in the case V1 of the stiffened composite panel

    图  12  复合材料加筋板算例V1的分层损伤面积演化模型参数后验估计

    Figure  12.  Posterior estimations of the delamination area progression model parameters for the case V1 of the stiffened composite panel

    图  13  复合材料加筋板算例V1的分层损伤面积演化预测示意

    Figure  13.  Illustration of the delamination area progression prediction for the case V1 of the stiffened composite panel

    图  14  复合材料加筋板算例V1的剩余使用寿命(RUL)预测结果

    Figure  14.  Remaining useful life (RUL) prediction result for the case V1 of the stiffened composite panel

    表  1  碳纤维增强环氧树脂基复合材料力学性能参数

    Table  1.   Mechanical properties of the carbon fiber reinforced epoxy resin matrix composites

    PropertyValue
    E1/MPa 157486
    E2/MPa 9946
    v 0.24
    G12/MPa 4950
    G13/MPa 4950
    G23/MPa 3208
    Notes: E1 and E2 are Young’s moduli in 1 and 2 direction, respectively; v is Poisson’s ratio; G12, G13 and G23 are shear moduli in 1-2 plane, 1-3 plane and 2-3 plane, respectively.
    下载: 导出CSV

    表  2  仿真疲劳分层损伤扩展的虚拟裂纹闭合技术(VCCT)参数

    Table  2.   Virtual crack closure technique (VCCT) parameters for simulating fatigue delamination growth

    ParameterValue
    GIC/(MPa·mm−1/2) 0.45
    GIIC/(MPa·mm−1/2) 1.38
    GIIIC/(MPa·mm−1/2) 1.38
    C1 1×10−5
    C2 1
    C3 1×104
    C4 5
    Notes: GIC is the critical mode I energy release rate; GIIC is the critical mode II energy release rate; GIIIC is the critical mode III energy release rate; C1 and C2 are the material constants determining the onset of delamination growth; C3 and C4 are the material constants determining the fatigue delamination growth rate.
    下载: 导出CSV
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出版历程
  • 收稿日期:  2020-11-20
  • 录用日期:  2021-01-18
  • 网络出版日期:  2021-02-02
  • 刊出日期:  2021-11-01

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