Boundary layer and its influence on strength of cylindrical shell with a variable thickness

Аuthors

Firsanov V. V.

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

e-mail: k906@mai.ru

Abstract

From a position of a three-dimensional problem of the theory of elasticity results of construction of a variant of the specified theory of calculation of cylindrical covers with asymmetrical essentially variable thickness are considered. The essence of this theory consists in construction of the basic intense condition which is based on a hypothesis of a vertical element, and an additional intense condition of the regional flat deformation arising of close rigidly jammed edge. It gives the chance to estimate the stress-strain state of thin-walled aircraft structures both in internal areas, and in narrow boundary zones near to irregularities of type of aviation connections, joints elements of structure with variation in wall thickness, etc.

Keywords:

the cylindrical shell, the stress-strain state, a hypothesis Kirchgof-Love, boundary layer , the elasticity theory, a boundary problem, variation method Vlasova-Kantorovicha.