Rapid modeling method for deformation design of aircraft structural part based on CATIA CAA

A technology for aircraft structural parts and deformation design, applied in geometric CAD, design optimization/simulation, special data processing applications, etc., can solve the problems of time-consuming and labor-intensive pass rate of similar model parts, so as to save modeling time, shorten development cycle, Effect of reducing design modeling time

Pending Publication Date: 2021-10-26
NORTHEASTERN UNIV
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Problems solved by technology

[0007] The purpose of the present invention is to provide a CATIA CAA-based rapid modeling method for deformation design of aircraft structural parts, in order to solve the time-consuming and labor-intensive and qualified rate problems of creating a large number of similar model parts

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  • Rapid modeling method for deformation design of aircraft structural part based on CATIA CAA
  • Rapid modeling method for deformation design of aircraft structural part based on CATIA CAA
  • Rapid modeling method for deformation design of aircraft structural part based on CATIA CAA

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Embodiment Construction

[0035] The present invention will be further described below in conjunction with specific drawings and embodiments.

[0036] As shown in Table 1, according to the factors affecting the aircraft structural parts, the parameters of each influencing factor are selected, and the type of the target part is deduced. It can be seen from the table that the profile height, crack growth resistance, opening size, manufacturing cost, bearing capacity and assembly manufacturability need to be filled in. According to the needs, the section height is selected as high; the crack growth resistance is selected as high; the opening size is selected as large; the manufacturing cost is selected as high; the bearing capacity is selected as high; the assembly process is selected as high. According to the rules in the rule library: IF profile height: high and crack growth resistance: high and opening size: large and manufacturing cost: high and bearing capacity: high and assembly process: high THEN t...

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Abstract

The invention provides a rapid modeling method for a deformation design of an aircraft structural part based on CATIA CAA. The method comprises the following steps of: step 1, selecting parameters of each influence factor according to factors influencing an airplane structural part, and reasoning the type of a target part through rule reasoning; step 2, on the basis of the reasoning result in step 1, inputting attributes of the type of the target part, and further reasoning a model close to the target part; step 3, calling out a template of the target part from a part library according to the model close to the target part obtained in step 2; step 4, modifying parameters of the target part and carrying out a deformation design to obtain a target part model. According to the method, the modeling time can be saved by more than 90%, the part modeling efficiency is improved, the workload of designers is reduced, and the design cycle is shortened.

Description

technical field [0001] The invention belongs to the field of computer-aided design of aircraft structural parts, and in particular relates to a rapid modeling method for deformation design of aircraft structural parts based on CATIA CAA. Background technique [0002] With the development of the aviation industry, my country has put forward higher requirements for the design quality and design efficiency of aircraft structural parts. In the process of product development, it is inevitable to use new technologies such as computer-aided design to shorten the development cycle, thereby reducing costs and enhancing Competitiveness. [0003] China's aviation industry is at a critical stage of overtaking the world's aviation powers, and shortening the aircraft development cycle is an inevitable choice for this process. There are many similar parts in the aircraft structure. The steps and process of modeling these similar parts using CATIA software are exactly the same. The properti...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/20
CPCG06F30/15G06F30/20
Inventor 郝博王杰刘芳尹兴超王明阳王婵娟闫俊伟郭嵩
Owner NORTHEASTERN UNIV
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