Automatic partitioning method for appearance feature machining of aircraft structural parts

A technology for aircraft structural parts and shape features, applied in special data processing applications, geometric CAD, etc., can solve problems such as difficulty in ensuring efficiency and quality, dependence on manual experience, and complicated programming processes

Active Publication Date: 2020-12-04
CHENGDU AIRCRAFT INDUSTRY GROUP
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Problems solved by technology

[0004] Aiming at the problems that various interference objects need to be considered in the programming process of the shape features of aircraft structural parts, the programming process is complicated, relying on manual experience, and the efficiency and quality are difficult to guarantee. This application proposes an automatic partition method for the shape feature processing of aircraft structural parts, which can realize Automatic partitioning of feature processing, providing support for automatic programming of shape features

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  • Automatic partitioning method for appearance feature machining of aircraft structural parts
  • Automatic partitioning method for appearance feature machining of aircraft structural parts
  • Automatic partitioning method for appearance feature machining of aircraft structural parts

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Embodiment Construction

[0072] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0073] An automatic zoning method for processing the shape features of aircraft structural parts, comprising the following steps: aiming at the shape features of aircraft structural parts, identifying all geometric surface attributes of the shape features according to the definition of geometric surface attributes, and establishing the association relationship between the shape geometric surfaces; Based on the principle of partitioning of the shape surface, the geometric surface of the shape feature is initially partitioned; then the position and shape information of the interference objects such as the part process boss and the pressure plate are obtained, and the positional relationship between the interference object and the shape geometric surface is established; finally, the initial shape processing is carried out according to the position of the int...

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Abstract

The invention relates to the field of aircraft machining, in particular to an automatic partitioning method for appearance feature machining of aircraft structural parts which comprises the steps thatfirstly, acquiring all geometric surfaces of appearance features of the aircraft structural parts; identifying all geometric surface attributes of the shape features according to geometric surface attribute definitions, and establishing association relationships between geometric surfaces; formulating an appearance surface partition processing principle, and carrying out primary partition on thegeometric surfaces of the appearance features; establishing position relationships between appearance processing interference objects and appearance geometric surfaces by considering a process boss, apressing plate and the like; and according to the position of the interference object, carrying out secondary partitioning on the contour machining primary partitioning result, so as to obtain a structural part contour feature machining partitioning result considering interference factors such as the boss and the pressing plate, and provide a basis for automatic generation of an appearance feature machining program.

Description

technical field [0001] The present application relates to the field of aircraft processing, in particular to a method for processing partitions of shape features of aircraft structural parts. Background technique [0002] NC process design is an important link in the development of structural parts, which directly affects the final processing quality of parts. As an important part of the aerodynamic shape of an aircraft, the shape of structural parts contains complex features such as a large number of curved surfaces. In addition, the processing of structural parts mostly adopts the clamping method of boss pressing, which leads to a variety of interference factors in the shape processing of structural parts, which makes the programming of the processing of structural parts shape features cumbersome. The auxiliary manufacturing mode relies heavily on manual experience, low efficiency, and poor quality stability. [0003] Existing patents, such as the patent application numb...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15
CPCG06F30/15
Inventor 高鑫牟文平王鹏程宋戈王斌利李卫东李仁政唐李张云
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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