Method of calculation dynamic and stress-strain state of an aircraft skin at action muzzle shock wave

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

The method and algorithm of calculation of the dynamic and is intense-deformed conditions of the panel of an aircraft skin, being in immediate proximity from a cut of a trunk and subject to influence a muzzle shock wave is considered.
The technique is based on definition of muzzle shock wave parameters by means of the empirical theory of dimensions, and the dynamic condition of a covering pays off with the help of the theory of elastic covers. Entrance data are the geometry and an arrangement of a cut of a trunk and the characteristic filling compound, and also geometrical and mechanical properties of the panel of an aircraft skin. Output characteristics are dynamic accelerations, stresses and a panel deflection.

Keywords:

the skin panel, a dynamic state, muzzle shock wave, the empirical theory of dimensions, the theory of shells, pressure, a force impulse, stress, the graf-analytic approach