Statement and general technique for solving problem of oscillation of a hereditarily deformable aircraft

This article provides a general statement and technique for solving the problem of oscillations hereditarily deformable aircraft in gas flow with finite number degrees freedom. Using Lagrange equations variational principle hereditary theory viscoelasticity, motion under consideration are derived. The generalized forces acting on subsonic flight mode determined according to stationarity hypothesis. As result, closed interconnected weakly singular integro-differential obtained that describe mathematical model General schemes numerical solution these outlined. an example, flexural-torsional-aileron flutter transient process wing freedom is considered.