Stress-Strain State and Buckling Problems of Structurally-Anisotropic Aircraft Panels Made of Composite Materials in View of Production Technology

Abstract

The main relations of a mathematical model for analyzing the stress-strain state and buckling of structurally-anisotropic panels made of composite materials are proposed. The mathematical model of a stiffening rib being in one-side contact with the skin is refined. One takes into account the influence of panel production technology, namely, residual thermal stresses and preliminary tension of reinforcing fibers. Exact analytical solutions for boundary value problems with the resolvent eight order equation are considered. The influence of the structure parameters on the level of stresses, displacements, buckling forces for bending and torsion modes has analyzed.