Pixel subdivision payload transfer method and system

Abstract

The present invention relates to a pixel subdivision load transfer method and system. The pixel subdivision load transfer method comprises: obtaining surface pressure distribution data, the data being in the form of surface elements and corresponding pressure; subdividing surface element pixels into subdivision surface elements which are small enough; allocating the subdivision surface elements to corresponding structure bearing points; integrating the subdivision surface elements allocated to the same structure bearing point into concentrated force and moment, and transferring the concentrated force and moment to the structure bearing point; comparing load distribution before the transfer with load distribution after the transfer to obtain a difference, and determining whether the difference is less than given tolerance; if the difference is less than the given tolerance, obtaining a final load; and if the difference is greater than or equal to the given tolerance, continuing performing pixel subdivision on the surface elements, and repeating the subsequent steps until the final load is obtained. The pixel subdivision load transfer method and system of the present invention can achieve the following beneficial technical effects: transferring a pneumatic surface load onto a structure node, and achieving conservation before and after the transfer, and a precise match of load distribution.

Description

technical field [0001] The invention relates to a pixel subdivision load transfer method and system, and belongs to the field of aircraft aeroelasticity. Background technique [0002] Before it comes to product design where the shape is subjected to hydrodynamic pressure and the internal structure is loaded, it is necessary to evaluate the various external hydrodynamic loads that the internal structure may bear. Airplanes are one such product. [0003] Computational fluid dynamics assessments of external fluid dynamics typically use computational fluid dynamics analysis or wind tunnel test models to form meshes for hydrodynamic analysis. Store powerful data on each grid cell. [0004] Structural dynamic modeling is carried out on the internal structure to form a structural finite element model. The form of the structural finite elements does not match the mesh used for hydrodynamic analysis at all. The function of load transfer is to convert the force on the aerodynamic ...

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Problems solved by technology

[0006] 1. Mapping method: automatically match the structural unit and aerodynamic unit according to the spatial position for transmission. The disadvantage is that it is difficult to ensure energy conservation when the grid difference between the structure and the aerodynamic interface is large

[0007] 2. Interpolation method: All structural units and aerodynamic units are involved in three-dimensional interpolation, which has a high degree of automation and can ensure energy conservation during the boundary load transfer process. The disadvantage is that it is difficult to ensure the moment distribution in the case of large aspect ratio aircraft wings. Be consistent before and after passing

This method can use the partition method to improve the consistency before and after the transfer, but when there are many active surfaces on the wing, it is difficult to transfer the component load only through plane division

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