A numerical model of dynamical and deflected mades for separation systems of aircraft guided missiles

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

Mathematical models are described for computation of vibro-dynamical and deflected modes as well as separation parameters for a motion of guided missiles launched or catapulted by means of appropriate devices. Numerical results are given for dynamics of separation systems implemented as rail-type launchers with straight or curvilinear ways. Numerical analysis is also carried out to reveal an influence of elasticity and mass characteristics as well as structural nonlinearities for a system which consists of guided missile, launcher and aircraft wing onto separation parameters and strength of the separation system.

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