【摘要】：發(fā)展了層合復合材料面內及分層失效模型,模型考慮了橫向壓剪殘余剪切變形和分層殘余相對位移。提出一種塊體單元包含若干鋪層的模型,以減少復合材料逐層分析時的計算量。對一種碳纖/環(huán)氧層合復合材料進行了橫向壓痕試驗,測量了不同壓力下凹坑的深度,用超聲C掃測得損傷面積。用發(fā)展的模型在ABAQUS平臺上通過用戶材料子程序UMAT模擬了上述試驗,分析了試驗曲線特征點對應的損傷機制,通過與試驗結果的對比,驗證了本文模型的合理性。
[Abstract]:The in-plane and delamination failure models of laminated composites are developed. The transverse compressive shear residual shear deformation and delamination residual relative displacement are considered in the model. A model of block element with several layers is proposed to reduce the computational complexity of composite layer by layer analysis. The transverse indentation test of a carbon fiber / epoxy laminated composite was carried out. The depth of the pits under different pressures was measured and the damage area was measured by ultrasonic C-scan. The developed model is used to simulate the above experiments on ABAQUS platform by means of the user material subroutine UMAT. The damage mechanism corresponding to the characteristic points of the test curve is analyzed. The rationality of the model is verified by comparing with the experimental results.
【作者單位】： 南京航空航天大學機械結構力學及控制國家重點實驗室;
【基金】：國家自然科學基金(11272147;10772078) 航空科學基金(2013ZF52074) 機械結構力學及控制國家重點實驗室基金(0214G02) 國家重點實驗室開放基金(IZD13001-1353;IZD150021556) 江蘇省高校優(yōu)勢學科建設工程項目
【分類號】：TB33
，

本文編號：2421443