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Information × Registration Number 0225U002234, (0123U100590) , R & D reports Title Development of methods for numerical simulation of nonlinear oscillations of the wing with damage in a single structural element popup.stage_title Розробка методів та комп'ютерних програм для розрахунку коливань крила з пошкодженням окремого елемента конструкції Head Filipkovskyi Serhii V., Доктор технічних наук Registration Date 25-02-2025 Organization National Aerospace University "Kharkiv Aviation Institute" popup.description1 Development of numerical methods for determining the frequencies and modes of free oscillations and the stability of forced oscillations of an aircraft wing with damage in a single structural element. popup.description2  The object of the research is the wing of a regional transport aircraft. The goal of the current stage is to develop a mathematical model and an algorithm for calculating aeroelastic oscillations of the wing, allowing for play in the mechanical control linkage of the aileron, as well as variable bending and torsion of the console along the span. Research methods are the methods of mathematical modeling of free and forced oscillations of the wing. The paper substantiates and accepts assumptions for constructing a calculation model of the wing of a regional transport aircraft with play in the mechanical control linkage of the aileron. Based on the accepted hypothesis and assumptions, a finite element model with 20 degrees of freedom is constructed. The frequencies and modes of free oscillations of the wing model are studied. The calculation results showed that the natural frequencies of the model are in the range of oscillation frequencies of existing aircraft of the class under consideration, and the oscillation modes of the model correspond to the oscillation modes of existing wings. A mathematical model for studying forced aeroelastic oscillations of a wing with aileron play has been developed. This model involves the use of predetermined functions of aerodynamic forces and moments to calculate the wing's resonant frequencies and study the stability of oscillations at resonances. An algorithm for the continuation method is proposed to determine the resonant frequencies, and an iterative Newton method is used to calculate the resonant amplitudes. Product Description popup.authors Svitlychnyi Serhii P. Starodub Oleksii V. Filipkovskyi Serhii V. popup.nrat_date 2025-02-25 Close