LAMINATION-CONFIGURATION METHOD OF CFRP INTERLAYER BREAKDOWN TOUGHNESS TEST PIECE

摘要

PURPOSE:To produce a carbon fiber composite material test piece which is not twisted even if delamination is performed by setting a portion to be subjected to delamination to asymmetrical lamination angles in upper and lower directions, a lamination angle to be symmetrical at both upper-side and lower- side lamination portions, and by setting those fiber angles to be equal. CONSTITUTION:When a test piece is produced by laminating a material 1 so that directions of a carbon fiber 2 differ, lamination portions A and B are in symmetrical lamination each other to prevent an upper-side lamination portion A and a lower-side lamination portion B which are released at the time of test from being warped and twisted. Namely, the interlayer to be released as an entire test piece is in an asymmetrical layer with a fiber angle of thetadegrees and that of -theta degrees crossing it. However, the upper-side lamination portion A which causes the delamination is in symmetrical layer as in theta -theta, -thetaand theta, the lower-side lamination portion B is in a symmetrical layer as in -theta, theta, theta, and -theta, and further the lamination angle theta and -theta are set to the same angle at the lamination portions A and B.