A method, device, equipment and medium for static aeroelastic correction of wind tunnel test data

Abstract

The invention discloses a method, device, equipment and medium for static aero-elastic correction of wind tunnel test data. The method includes: performing numerical simulation of fluid mechanics based on a three-dimensional structured fluid grid of a wing test model to obtain aerodynamic load data on the surface of the wing test model; Structural finite element numerical analysis, to obtain the difference between the current wing displacement and the previous wing displacement; if the difference between the current wing displacement and the previous wing displacement is less than the preset difference, then based on the obtained The aerodynamic force difference of the wing test model is obtained, and the modified aerodynamic force of the wing test model is obtained. The above method uses the three-dimensional structured fluid grid of the wing test model and the geometric nonlinear finite element model to iteratively solve the aerodynamic difference of the wing test model obtained by multiple iterations, and then obtains the modified aerodynamic force of the wing test model.

Description

technical field [0001] Embodiments of the present invention relate to aeronautical wind tunnel test technology, and in particular, to a method, device, equipment and medium for static aeroelastic correction of wind tunnel test data. Background technique [0002] In order to fly at high subsonic speeds, modern civil airliners use swept wings. The characteristic of the swept wing is that under the action of aerodynamic force, it will produce a combination of bending and torsion deformation. This deformation causes changes in the aerodynamics of the wing, which in turn further changes the amount of deformation of the wing until the wing structure reaches a state of static equilibrium. This phenomenon of coupling between structure and aerodynamic force is called the static aeroelastic effect. In the wind tunnel test of the civil airliner, the swept wing of the test model will also produce static aeroelastic deformation under the action of aerodynamic force. The aerodynamic va...

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Problems solved by technology

[0004] In the prior art, in the process of correcting the test deviation, the hydrodynamic analysis and the finite element analysis only carried out aerodynamic load data transmission once, lacking multiple iterative couplings, resulting in large deviations in the obtained model deformation results

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