Composite Plate Layup ExamplesAerospace Engineering 复合地基航空航天工程实例上篮.doc

Composite Plate Layup Examples +90,0,+90 (symmetric layup), each lamina thickness=0.01, S-glass/epoxy, Nx=Ny=1,000 lb/in 3/+0, lamina thickness=0.01, Woven glass/epoxy, Nx=Ny=1,000 lb/in +45,0,-45 (antisymmetric layup), each lamina thickness=0.01, graphite/epoxy, Nx=Ny=1,000 lb/in same as 3, but Nx=1,000 lb/in same as 3, but Nxy=500 lb/in same as 3, but Mx=10 in-lb/in 4/+0,+45,-45,4/+0, each lamina thickness=0.01, graphite/epoxy, Nx=Ny=1,000 lb/in same as 7, but Mx=50 in-lb/in same as 7, but My=50 in-lb/in LAMINATE ANALYSIS (plane stress) – Example 1 The following orthotropic materials are now defined (english units: lbf, in) Mat # Material Name E1 E2 Nu12 G12 Vf 1 S-Glass/epoxy 63.00E+05 12.90E+05 .270 66.00E+04 .50 2 Woven-Glass/epo 43.10E+05 43.10E+05 .170 77.00E+04 .45 3 Kevlar/epoxy 12.60E+06 80.00E+04 .340 31.00E+04 .60 4 Carbon/epoxy(AS 20.60E+06 15.00E+05 .270 10.40E+05 .63 5 Graphite/epoxy 42.70E+06 92.00E+04 .230 71.00E+04 .57 6 Boron/epoxy 29.20E+06 31.50E+05 .170 78.00E+04 .50 7 Boron/aluminum 34.10E+06 19.90E+06 .300 68.00E+05 .50 8 SiCarbide/alum 29.60E+06 17.10E+06 .270 59.00E+05 .43 9 SiCarbide/ceram 17.60E+06 16.20E+06 .200 64.00E+05 .39 Summary of layup information. Total thickness is .03 in. (layup is symmetric) Layer# Material # thickness z-bar theta 1 1 0.0100 -.0100 90.0 2 1 0.0100 0.0000 0.0 3 1 0.0100 0.0100 90.0 Laminate Stiffness Matrices A Matrix follows 9.015E+04 1.061E+04 4.395E-02 1.061E+04 1.410E+05 5.700E-01 4.395E-02 5.700E-01 1.980E+04 B Matrix follows -3.803E-06 2.687E-07 -1.790E-12 2.687E-07 1.586E-06 -1.230E