Разработка и апробация методики численного моделирования аэроупругого состояния крыла на основе методов конечных элементов и контрольных объемов

Abstract

The paper considers a current trend in designing structural elements for the modern airliners. Calculation of the aerodynamic loads acting on the aircraft in flight is of primary interest at the initial design and development stages. Based on the experimental data, a CAD model was developed, and a computational grid for the CFD solver and the finite element model were constructed. The proposed technique for determining external loads on the airframe is based on the coupled solution of the aerodynamics and strength dynamic models. When using this technique, the serial data exchange between the solvers was actually implemented making it possible to simulate various periodic processes, including the structural vibrations. This work studies aerodynamic characteristics and eigenforms of the loaded wing using the example of the wing blowing calculated repetition in a cryogenic wind tunnel. The purpose of the work is to develop and test a technique for numerical simulation of the wing aeroelastic state, which allows performing calculations to determine the loads on both the lightly loaded elements and the critical units, including the wing box and the empennage. The results obtained testify to applicability of the developed technique at the transonic speeds, as well as a good convergence of the mathematical simulation results with the experimental data.