Abstract:

Are obtained in the conditions of physical and geometric non-linearity for multilayer thinwalled shells and plates the task solving regularity infringing factors. This solving, together with simplifying the algorithms are taking into account the mode of deformation condition particularity in the tense concentration zones. Are offered simplified variants of calculation of the cuttings and holes of thin-walled sandwich plates. Are solved tasks for calculation practice of the cuttings and holes thin-walled sandwich plates in the conditions of several variants of inserting the edges and different loads. Calculation methods of the sandwich shells and plates by considering the geometric and physical nonlinearity, let us to estimate variety of all the components of mode of deformation condition, values of critical load and the form of buckling in the load process, in addition, this method is more efficient in comparison with other numerical and numerical-analyzing methods.

Keywords: Aviation; wing; aircraft; skin; composite