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Method and device for computing stiffness of aviation orthogonal stiffened plate

A technology for stiffness calculation and stiffened panels, which is applied in the field of aviation panels, can solve calculation and other problems, achieve the effect of improving processing quality and efficiency, correct algorithm principles, and meeting aircraft design requirements

Active Publication Date: 2018-07-06
BINZHOU UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Aiming at the deficiencies in the prior art and solving the problem of how to quickly and accurately calculate the stiffness value of complex multi-orthogonal stiffened aviation panels in the prior art, the present invention provides a method and device for calculating stiffness of aviation orthogonal stiffened panels

Method used

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  • Method and device for computing stiffness of aviation orthogonal stiffened plate
  • Method and device for computing stiffness of aviation orthogonal stiffened plate
  • Method and device for computing stiffness of aviation orthogonal stiffened plate

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Experimental program
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Embodiment 1

[0054] The purpose of this embodiment 1 is to provide a method for calculating the stiffness of an aeronautical orthogonally stiffened plate.

[0055] In order to achieve the above object, the present invention adopts the following technical scheme:

[0056] Such as figure 1 as shown,

[0057] A method for calculating the stiffness of an aeronautical orthogonally stiffened plate, the method comprising:

[0058] Step (1): Receive the data of the aeronautical orthogonally stiffened slab, construct the theoretical mechanical model of the single-rib orthotropic slab, and calculate the bending stiffness of the single-rib orthotropic slab;

[0059] Step (2): Calculating the bending deformation curve of an orthotropic plate with a single-rib distribution structure by applying a finite element model through a static bending moment;

[0060] Step (3): Comparing the data results calculated by the above two models, the correction parameters of the finite element model are obtained, th...

Embodiment 2

[0085] The purpose of Embodiment 2 is to provide a computer-readable storage medium.

[0086] In order to achieve the above object, the present invention adopts the following technical scheme:

[0087] A computer-readable storage medium, in which a plurality of instructions are stored, and the instructions are adapted to be loaded by a processor of a terminal device and perform the following processing:

[0088] Step (1): Receive the data of the aeronautical orthogonally stiffened slab, construct the theoretical mechanical model of the single-rib orthotropic slab, and calculate the bending stiffness of the single-rib orthotropic slab;

[0089] Step (2): Calculating the bending deformation curve of an orthotropic plate with a single-rib distribution structure by applying a finite element model through a static bending moment;

[0090] Step (3): Comparing the data results calculated by the above two models, the correction parameters of the finite element model are obtained, the...

Embodiment 3

[0092] The purpose of Embodiment 3 is to provide a terminal device.

[0093] In order to achieve the above object, the present invention adopts the following technical scheme:

[0094] A terminal device, including a processor and a computer-readable storage medium, the processor is used to implement instructions; the computer-readable storage medium is used to store multiple instructions, and the instructions are suitable for being loaded by the processor and performing the following processing:

[0095] Step (1): Receive the data of the aeronautical orthogonally stiffened slab, construct the theoretical mechanical model of the single-rib orthotropic slab, and calculate the bending stiffness of the single-rib orthotropic slab;

[0096] Step (2): Calculating the bending deformation curve of an orthotropic plate with a single-rib distribution structure by applying a finite element model through a static bending moment;

[0097] Step (3): Comparing the data results calculated by...

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Abstract

The invention discloses a method and a device for computing stiffness of an aviation orthogonal stiffened plate, which comprises the following steps of: receiving the data of the aviation orthogonal stiffened plate, constructing a theoretical mechanical model of the orthotropic plate of the single-stirrup, and calculating the bending rigidity value of the orthotropic plate of the single-stirrup; applying a finite element model by statics bending moment to calculate the bending deformation curve of the orthotropic plate of the single-stirrup distribution structure; Comparing the data results calculated by the two models to obtain a finite element model correction parameter, constructing a complex aviation multi-stirrup orthogonal plate numerical model, and calculating the rigidity value ofthe aviation orthogonal stiffened plate. The method and the device is characterized by taking the characteristics of wallboard parts as starting points, avoiding estimating the rigidity according to experience, calculating the rigidity of the aviation positive crossing reinforcement plate rapidly, and providing the theoretical basis for the clamping scheme and the quality control of the frame parts in the processing process, thereby improving the processing quality and the efficiency.

Description

technical field [0001] The invention belongs to the technical field of aviation panels, and relates to a method and device for calculating the stiffness of aviation orthogonally stiffened panels, in particular to a method and device for calculating the stiffness of complex multi-orthogonally reinforced aviation panels using finite element correction models . Background technique [0002] The advantages of aviation wallboard parts mainly include time-saving assembly and good overall performance. However, large-scale aviation panels also have disadvantages such as large size, complex features, and long processing cycle. It is interfered by factors such as material properties and structural characteristics during processing, and processing deformation will occur. It is difficult to meet the design requirements. [0003] Research in the industry mainly focuses on machine tools, cutting tools, cutting parameters, tool path, cutting force, etc., ignoring the analysis of the stru...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23G06F2119/06
Inventor 黄晓明
Owner BINZHOU UNIV
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