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Static aeroelasticity correction method for aircraft wing

A static aeroelasticity and 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: 2020-04-17
XIAN AIRCRAFT IND GROUP
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  • Application Information

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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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  • Static aeroelasticity correction method for aircraft wing
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Embodiment Construction

[0017] See attached picture,

[0018] The static aeroelasticity correction method of the aircraft wing proposed in this application is applicable to the situation with wind tunnel test data. Known the aerodynamic model 1 of aircraft wing, the application carries out the static aeroelasticity correction of aircraft wing with the wing aerodynamic model 1 when the aircraft is done longitudinal pitch maneuvering state as an example, known the angle of attack of aircraft under this state, flight speed Pressure, flight altitude, wing normal aerodynamic coefficient, wing aerodynamic influence coefficient matrix, aircraft flap position is retracted, aileron deflection is zero.

[0019] The test pressure distribution of the whole aircraft including the wing of the aircraft 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 wing, fuselage and nacelle can be obtained. The test pressu...

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Abstract

A static aeroelasticity correction method for an aircraft wing comprises the steps: dividing an aerodynamic model of the aircraft wing into a plurality of strip blocks in the heading direction, and arranging a horseshoe vortex on each strip block to replace lift force generated by the strip block of the aircraft wing; solving an aerodynamic force basic equation of the aircraft wing according to the aerodynamic model of the aircraft wing, and calculating a theoretical aerodynamic force and an aerodynamic force interference angle of each block of the aircraft wing; according to full-aircraft test pressure distribution, determining the actual value of the lift line slope of the aircraft wing, the aerodynamic force correction interference angle of the aircraft wing and the actual aerodynamic force interference angle of the aircraft wing, and then calculating the actual aerodynamic force of each strip block of the aircraft wing through the aerodynamic force basic equation of the aircraft wing.

Description

technical field [0001] The invention relates to the field of aircraft strength design, in particular to an aircraft static aeroelastic correction method. Background technique [0002] The wing of a modern aircraft is the main force-bearing and force-transmitting component of the aircraft structure, and its design technology is one of the core key technologies of aircraft design. Due to the influence of the flexibility of the structure during the flight, the geometric shape and position of the wing will change under the action of the aerodynamic load. This elastic deformation change will inevitably affect the distribution of the aerodynamic load on the wing surface, which in turn leads to further wing deformation. , which is the aeroelastic phenomenon of the wing. [0003] For aircraft with large aspect ratio and elastic airfoil structure, the influence of static aeroelastic deformation of wing structure on aerodynamic load distribution is usually not negligible, and the inf...

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Application Information

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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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