A V Homchenko ("AURUS-AERO" LLC) :
Articles:
539.31 Modeling of transient dynamics of a fragment of a passenger airplane lower flap panel
Serdyuk D. O. (Moscow Aviation Institute (National Research University)), Homchenko A. V. ("AURUS-AERO" LLC)
doi: 10.18698/2309-3684-2025-4-124147
In this paper, a new transient normal displacement function for a thin elastic anisotropic plate associated with an elastic-inertial base and with local boundary conditions on an arbitrary contour is constructed by numerical and analytical methods. The Timoshenko hypotheses are adopted as the plate theory. The work is based on the method of fundamental solutions and the method of compensating loads. The fundamental solutions for an unbounded plate are constructed by means of Fourier integral transforms on spatial coordinates and Laplace integral transform on time. The corresponding originals are found using the analytic inversion of the Laplace integral transform. The original of the two-dimensional Fourier integral transform is found using integration methods for rapidly oscillating functions. Then, integral representations for transient plate displacements with local boundary conditions on an arbitrary contour are obtained using the fundamental solutions and the compensating load method. The time-dependent compensating loads are obtained from the solution of the system of first kind Volterra integral equations. By applying the quadrature method at each time step, the problem of compensating loads is reduced to the solution of a system of linear algebraic equations. As an example of calculation, we consider transient deformation of a fragment of the lower flap panel of a passenger airplane at impact of a piece of aviation pneumatic. For this object of research in the calculation scheme rivets act as local supports. In order to assess the validity of the solution results are compared with the results of the solution in the Simcenter Nastran software package. The finite element model of the plate was performed in Simcenter Femap using four-node layered shell elements “PCOMP” and linear-elastic material model of monolayers “2D ORTHOTROPIC”. The solution of the problem of transient plate deformation was obtained with Nastran Multi-Step Nonlinear Kinematic Transient (SOL402) using the integration scheme “Modified Generalized Alpha”.
Cердюк Д.О., Хомченко А.В. Моделирование нестационарной динамики фрагмента нижней панели закрылка пассажирского самолёта. Математическое моделирование и численные методы, 2025, № 4, с. 124–147.