積層板複合材料基材裂紋損傷演化律與破壞條件

Matrix Cracking Evolution Laws and Failure Conditions for Laminated Composite Materials

馬仁宏(Ren-Horng Maa) ； 鄭榮和(Jung-Ho Cheng)

《中國航空太空學會學刊》 35卷4期 (2003/12) Pp. 353-364

https://doi.org/10.6124/TAASRC.200312_35(4).06

摘要

本文提出複合材料基材裂紋微觀連體損傷力學模型，這個模型結合微觀均質化方法與不可逆連體熱力學內變量理論，能夠同時考量基材裂紋起始、演化與飽和，並能區分加載方式對破壞模式的影響，是一個完整的非等向性彈性損傷破壞模型。在提出損傷材料常數求取方法後，我們利用本模型預測[θ]單層板拉伸強度與[90]單層板Iosipescu剪切強度，獲得準確的結果。在比較本模型、Hashin基材破壞準則與Shahid-Chang基材損傷累積模型差異後，發現本模型觀念簡單且使用容易。最後將基材損傷模型寫成ABAQUS副程式UMAT，並分析含圓洞[0/904]S複合材料積層板受拉伸時，基材裂紋損傷累積情形，發現損傷會在應力集中處迅速累積並會降低整體結構剛性。

關鍵字

積層板複合材料 ； 基材裂紋 ； 連體損傷力學 ； 破壞條件

並列摘要

This paper proposes a matrix cracking micromechanically based continuum damage mechanics model, which combines the advantages of the micromechanical homogenization method with the continuum thermodynamics of internal variable theory. Moreover, the proposed model is an anisotropic elastic-damage-failure model since it describes the matrix cracking initiation, propagation, saturation as well as distinguishes the effect of loading conditions on the failure modes. After obtaining the material damage constants, the model is used to predict the failure strength of the[θ]lamina subjected to tension and [90] lamina subjected to Iosipescu shear, and the predicted results are in good agreements with experimental data. The drawbacks of the Hashin failure criterion and Shahid-Chang matrix damage accumulated model are discussed in detail. Finally, the proposed model is programmed into UMAT subroutine of the commercial finite element code ABAQUS, and the [0/904]S composite laminate with a central hole subjected to tensile loading is simulated. The results show that matrix cracking damage accumulates around the stress concentration area and tends to decrease the rigidity of the structure.

並列關鍵字

Laminated composite material ； Matrix cracking ； Continuum damage mechanics ； Failure condition