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Parametrization design method of first-level member of beam, wall and rib type parts of airplane

A parametric design and parametric technology, applied in the parametric design of aircraft beams, rib parts, first-level components, and walls, which can solve problems such as inconsistency of geometric types, affecting the seamless connection between CAD and CAE, etc.

Active Publication Date: 2013-03-20
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, CAD and CAE technology can achieve seamless integration in terms of physical analysis of parts, but how to solve the seamless integration of aerospace thin-walled structures, that is, to solve the problem of inconsistency between the geometric type of the CAE model and the geometric type of the CAE model, has become an influential factor. The key to the seamless connection between CAD and CAE cannot be solved by the existing technology

Method used

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  • Parametrization design method of first-level member of beam, wall and rib type parts of airplane
  • Parametrization design method of first-level member of beam, wall and rib type parts of airplane
  • Parametrization design method of first-level member of beam, wall and rib type parts of airplane

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Embodiment 1

[0078] A first-level component parametric design method for aircraft beams, walls, and ribs used in the aircraft structure design method based on parametric components. Its technical basis is the aircraft structure design method based on parametric components. For related content, please refer to the "Contents of Invention" in the manual.

[0079] The focus of this embodiment relates to a parametric design method for first-level components of aircraft beams, walls, and ribs: use parametric components to describe beams, walls, and ribs in aircraft structures, and aircraft beams, walls, and ribs 1 The parametric expression of level components specifically involves the following four parts: "basic properties", "geometric properties", "non-geometric properties", and "two-dimensional cross-section diagram"; where:

[0080] "Basic attributes" specifically include: component name, version number, creation time, component description, manufacturing process, remarks;

[0081] The "geo...

example

[0085] Example: For composite beam-wall members whose upper and lower flanges are T-shaped extruded profiles, they can be decomposed into upper and lower flanges and webs. For the upper edge strip, see Table 2 for the simplified unit and computed attribute table.

[0086] Table 2 can be simplified as member calculation properties and associated formulas of bar and beam elements

[0087]

[0088] For the lower edge, the simplified elements and calculation properties are the same as the upper edge, the difference is that the parameters of the associated formula are different.

[0089] For the web, the simplified elements and calculated properties are shown in Table 3.

[0090] Table 3 can be simplified to the calculated properties of members of various plate units

[0091]

[0092] "Two-dimensional section view": it is used for the user to correctly understand the physical meaning of each parameter of the component when the component is instantiated.

[0093] The parame...

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Abstract

The invention discloses a parametrization design method of first-level member of beam, wall and rib type parts of airplane. The parametrization design method comprises the following steps of: stating the beam, wall and rib type parts in the airplane structure by using parametrization members, wherein the parametrization statement of the first-level members of the beam, wall and rib parts of the airplane specifically relates to contents of four parts as follows: 1) the basic attributes specifically comprise the names of the members, the version numbers, the establishment time, the member description, the manufacturing process and the remarks; 2) the geometric attributes specifically consist of two parts of positioning parameters and cross-section parameters; 3) non-geometric attributes specifically relate to decomposition schemes and non-geometric attribute information corresponding to the decomposition schemes; and 4) a two-dimensional sectional drawing is used for helping a user to correctly understand the physical meaning of the parameters of the members in member instantiation. The parametrization design method is helpful in establishing a member bank system, functional and performance model data basis for the standardization and simulation analysis in airplane design is provided, the coordination of data of a geometric model machine and a functional model machine / performance model machine is ensured, the design quality of the airplane is improved, and the research and manufacturing period is shortened.

Description

Technical field: [0001] The invention relates to the technical field of aircraft structure design, and in particular provides a parametric design method for first-level components of aircraft beams, walls, and ribs. Background technique: [0002] In the prior art, with the continuous in-depth application of CAD technology, CAD technology has increasingly become an indispensable tool for aircraft design departments. Designers need to solve the parameter determination problem before using CAD to complete the 3D solid model of the product - design. If CAD technology cannot participate in the determination of product parameters, then the application of CAD technology in design is only a description of design results, not a real design. The model construction of the design process becomes the key for the CAD system to participate in the product design process. This model should be suitable for the data requirements of CAD / CAE and other systems, and conform to the description of...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 杨旭朴春雨吴斌
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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