Abstract
Aircraft flaps play an important role in the operation of the aircraft. They are used to increase the lifting force of the aircraft at a given speed, which allows for slower take-off and landing. By increasing the camber of the wing, the flaps provide additional lift, which is especially useful during takeoff and landing when the aircraft needs to maintain control at low speeds. In addition, flaps also help increase the drag of the aircraft, which slows it down during landing. The flaps have a complex geometric shape, and therefore, to assess their stress-strain state, it is necessary to use numerical methods, primarily the finite element method. In the work based on the method of finite elements, there were determinations of stress under real operating loads. The proposed method makes it possible to carry out both verification calculations during design and optimization of the mass of the aircraft flap.
Published Version
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