Modeling the mechanical tests of composite flange sample-segment from aircraft engine cover

The stress-strain state of segment-sample of a typical aircraft engines composite casing fiberglass flange was calculated. The problem of anisotropic elasticity theory for inhomogeneous multilayered structure was solved with three-dimensional formulation using ANSYS. Diagrams of stresses in the most loaded parts of the segment-sample were drawn. It is shown that the most dangerous, defining the beginning of the destruction of the flange, is tension interlamination stresses. The analysis of the interlamination stress fields and static strength of the segment-sample was conducted. Comparison of the calculation results and results of laboratory tests was made.