6-148 



DESIGN OF LAMINATES 



To determine the critical shear stress in equation 6. 55, the following constants are 

 necessary to obtain the factor "G a " for simply supported panels from Fig. 6-46: 



ct = 



Sa 



(E^^ 



-1 1 



El 



(6. 53) 



(6.54) 



0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 



/»« 



REFERENCE 17 



Fig. 6-46. Curves for Calculating the Buckling 

 Shear Stress in Orthotropic Rectangular Plates 

 with Simply Supported Edges Whose Axes of 

 Elastic Symmetry are Parallel to the Edges 



For the case where the orthotropic laminate is subjected to uniform shear and the warp 

 is parallel to the L axis, the following relationships have been obtained: 



The critical shearing stress can be calculated from: 



