アラミド繊維/エポキシ樹脂複合材料の破壊機構と超音波顕微鏡による損傷評価

概要

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An investigation of the fracture mechanisms of (0/±45/90)_<2S> aramid fiber/epoxy composies, i.e., Kevlar 49 and HM50 composites, has been carried out, and the delamination characteristics have been quantitatively measured by means of an acoustic microscope. Free-edge delamination occurs initially at -45°/90° and 90°/0° interfaces in static tensile tests, whereas it occurs initially at ±45° interfaces in fatigue tests. Under static tensile loading, resin cracking and interface debonding in the weakest 90° ply are followed by the lowering of the load-carrying capacity of 90° and 45° plies. The final fracture is caused through an increase in 0° ply stress. No difference in the fracture process betwen Kevlar 49 and HM50 composites is observed. Compliance changes in fatigue tests are divided into two stages : stage I where the compliance is almost constant, and stage II where the compliance grows with progression of stress cycles. In stage I, no 0° ply damage occurs, whilst 0° ply damage as well as 0°/45° and 90°/0° delaminations takes place in stage II.
一般社団法人日本機械学会の論文
1992-02-25