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Deformation monitoring method and system for aircraft panel precision self-correction

A technology for deformation monitoring and aircraft panels, applied in aircraft component testing, aircraft assembly, measuring devices, etc.

Pending Publication Date: 2021-02-05
杨海成
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] This application aims at the deformation problem of the aircraft panel during the manufacturing process, and applies the structured light imaging technology to the processing and assembly process of the aircraft panel, aiming to provide a deformation monitoring method for the self-correction of the accuracy of the aircraft panel

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  • Deformation monitoring method and system for aircraft panel precision self-correction
  • Deformation monitoring method and system for aircraft panel precision self-correction
  • Deformation monitoring method and system for aircraft panel precision self-correction

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Embodiment Construction

[0048] Example embodiments will be described more fully hereinafter with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the embodiments set forth herein. These embodiments are provided so that this application will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals denote the same or similar parts in the drawings, and thus their repeated descriptions will be omitted.

[0049] Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided in order to give a thorough understanding of the embodiments of the application. However, those skilled in the art will appreciate that the technical solutions of the present application may be practiced without one or mor...

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Abstract

The invention provides a deformation monitoring method and system for aircraft panel precision self-correction. The deformation monitoring method comprises the following steps: determining key characteristics influencing deformation of a aircraft panel in a manufacturing process; monitoring the key characteristics in real time by using a binocular camera based on structured light; performing key characteristic deformation error calculation according to a real-time monitoring result to obtain deformation data; and performing numerical calculation according to the deformation data of the key characteristics to obtain overall deformation data. Structured light is adopted as an imaging light source so that a problem of light reflection when a common white light source irradiates a metal wall plate is effectively avoided. Meanwhile, structured light imaging operation is simple, a large number of camera identification marks do not need to be pasted on the surface of a measured object, and workloads are greatly reduced. Binocular camera type deformation monitoring is used, a measurement range is large, the measurement response is fast, the structured light is used as a characteristic matching light source, and the measurement precision is ensured.

Description

technical field [0001] The present application relates to the field of aviation manufacturing, in particular to a deformation monitoring method and system for self-correction of aircraft panel accuracy. Background technique [0002] Aircraft panels have the characteristics of large size (eg 2500mm×30000mm) and thin thickness (eg 60mm), and are typical large thin-walled parts. In the process of aircraft panel processing or assembly, in order to ensure the final accuracy of the panel, the deformation of the workpiece must be controlled within a certain range during processing or assembly. At present, for the deformation problem in the manufacturing process of the aircraft panel, it is usually solved by manual correction after the manufacturing is completed. Under the current technological conditions, the accuracy of the shape of the aircraft panel is guaranteed by the tooling, for example, by the assembly frame during the assembly process. Assembly jigs are a rigid positioni...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60B64F5/10G01B11/16
CPCB64F5/60B64F5/10G01B11/16Y02T90/00
Inventor 杨海成
Owner 杨海成