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A Static Aeroelasticity Correction Method for Aircraft Wings

A static aeroelasticity, wing technology, applied in aircraft parts, aircraft component testing, computer-aided design, etc., can solve problems such as imperfect correction methods and oversimplified theoretical models of lift lines.

Active Publication Date: 2022-08-05
XIAN AIRCRAFT IND GROUP
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Problems solved by technology

[0005] The traditional correction method of the existing static aeroelastic uses the lift line theory, one of the limitations is that the theoretical value 2π is taken for the lift line slope of the airfoil vortex unit, or the lift line slope Cya of the whole aircraft is taken, which is only applicable to the lack of The situation of the wind tunnel test data; the second is that the theoretical model of the lift line is too simplified, and the spanwise arranged horseshoe vortex is used to replace the wing, without taking into account the aerodynamic and aerodynamic interference of the fuselage, nacelle and other components, and the correction method is not perfect

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  • A Static Aeroelasticity Correction Method for Aircraft Wings
  • A Static Aeroelasticity Correction Method for Aircraft Wings

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Embodiment Construction

[0017] see attached,

[0018] The static aeroelastic correction method of the aircraft wing proposed in this application is suitable for the situation where the wind tunnel test data is available. The aerodynamic model 1 of an aircraft wing is known. In this application, the aerodynamic model 1 of the wing when the aircraft is in a vertical pitch maneuver state is used as an example to perform the static aeroelastic correction of the aircraft wing. The angle of attack and the flight speed of the aircraft in this state are known. pressure, flight height, wing normal aerodynamic coefficient, aerodynamic influence coefficient matrix of the wing, the aircraft flap position is retracted, and the aileron deflection is zero.

[0019] The test pressure distribution of the whole aircraft including the aircraft wing is known. The wind tunnel test here refers to the high-speed wind tunnel pressure test of the whole aircraft, and the whole aircraft assembly including the aircraft wing, fu...

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Abstract

A static aeroelastic correction method for an aircraft wing, which divides the aerodynamic model of the aircraft wing into a plurality of blocks along the course, and arranges a horseshoe vortex on each block to replace the lift generated by the block wing; According to the aerodynamic model of the aircraft wing, the basic equation of the aerodynamic force of the aircraft wing is solved, and the theoretical aerodynamic force and aerodynamic interference angle of each block of the wing are calculated; according to the test pressure distribution of the whole aircraft, the actual value of the slope of the lift line of the aircraft wing is determined. And the aerodynamic correction interference angle of the aircraft wing and the actual aerodynamic interference angle of the aircraft wing, and then through the basic equation of the aerodynamic force of the aircraft wing, the actual aerodynamic force of each block of the wing is calculated.

Description

technical field [0001] The invention relates to the field of aircraft strength design, in particular to a static aeroelasticity correction method for aircraft. Background technique [0002] The wing of a modern aircraft is the main load-bearing and force-transmitting component of the aircraft structure, and its design technology is one of the core key technologies of aircraft design. During the flight of the wing, due to the influence of the flexibility of the structure, the geometric shape and position will change under the action of the aerodynamic load. This elastic deformation change will inevitably affect the distribution of the aerodynamic load on the surface of the wing, which will lead to further wing deformation. , which is the aeroelastic phenomenon of the wing. [0003] For aircraft with a large aspect ratio and an elastic airfoil structure, the influence of the static aeroelastic deformation of the wing structure on the aerodynamic load distribution is usually n...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00B64F5/60G06F30/15G06F30/28G06F113/08G06F119/14
CPCB64F5/00B64F5/60Y02T90/00
Inventor 党西军郭天天杨全刘伟
Owner XIAN AIRCRAFT IND GROUP
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