МЕТОД ВИЗНАЧЕННЯ ХАРАКТЕРИСТИК ЗАГАЛЬНОГО НАПРУЖЕНО-ДЕФОРМОВАНОГО СТАНУ В СИЛОВИХ ЕЛЕМЕНТАХ КОНСОЛІ КРИЛА ВІД НАВАНТАЖЕННЯ ФУНКЦІОНУВАННЯ

Abstract

When the high - lift system are released, the aerodynamic flow around the wing changes significantly, which in turn leads to a change in the stress-strain state of the wing. This is due not only to an increase in lift due to a change in the curvature of the wing and an increase in the wing area, but also a change in the position of the center of pressure relative to the wing chord. A significant increase in torque leads to a change in the stress-strain state of the wing mean joints. An aerodynamic calculation was performed using ANSYS CFX to obtain the position of the point of action of the lift force in each elements of the wing (slat, wing box and flap). Were obtained the relative positions of the points of action of the lift of individual parts of the wing: the slat, the wing box and the flap. These values were used to apply the forces acting from the high - lift system. The distributed air load was proportionally distributed across the slat, wing box and flap in accordance with the obtained aerodynamic calculations using ANSYS CFX. Plots of internal force factors were plotted, such as a diagram of shear force, bending and torque for wing configurations without extended high - lift system, as well as with takeoff and landing positions of high - lift system. Obtaining the value of the internal force factors, were used to create calculation models. The structural elements of the wing, in particular the attachment points of the high - lift system, operate in a complexly stressed state. This complicates the process of predicting the fatigue life of these elements. To obtain a competitive aircraft, it is necessary to develop new methods of wing design with widespread use of integrated systems. The study of the change in the stress-strain state of the wing with the extended position of the high - lift system makes it possible to predict the fatigue life with high accuracy. The process of creating and preparing a wing model for calculation, setting boundary conditions and choosing the optimal size of a mesh element is described. Obtaining aerodynamic characteristics using a CAE system to create a design model.