Stresses in a fuselage model due to concentrated radial loads

Experimental values of shear and direct stresses on cross–sections of a fuselage model, due to concentrated radial loads applied to a frame, are compared with values predicted by a matrix force analysis. The results include the effect of cut–outs in the surface of the shell. Comparisons are also made of the direct stress on the inner flange of the directly–loaded frame and of the frames bounding the cut–outs. Results indicate that the degree of accuracy of the theoretical stresses is adequate for the purpose of design.