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Control system for flexible tools for assembly of wing foreparts

A technology of flexible tooling and control systems, applied in the direction of digital control, electrical program control, etc., can solve the problem that rigid tooling cannot meet the requirements of various wing flaps.

Inactive Publication Date: 2015-06-03
NORTHWESTERN POLYTECHNICAL UNIV +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Aiming at the problem in the prior art that a set of rigid tooling cannot satisfy the assembly of various wing flaps during wing flap assembly, the present invention proposes a flexible tooling control system for wing flap assembly

Method used

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  • Control system for flexible tools for assembly of wing foreparts
  • Control system for flexible tools for assembly of wing foreparts

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Experimental program
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Effect test

Embodiment Construction

[0018] This embodiment is a flexible tooling control system for assembling the front flap of the wing. The single-axis servo motor on the SERCOS-III bus node is controlled by the motion controller to realize the motion control of the entire set of flexible tooling for the front flap of the wing, and to digitize the front flap of the wing. assembly.

[0019] see figure 1 , figure 2 , The control structure of the flexible assembly unit of the leading edge flap adopts the multi-level distributed control method introduced by the field bus.

[0020] The industrial computer 1 communicates control commands and status information with the motion controller 2 , the laser tracker controller 6 and the robot controller 7 through the TCP / IP network.

[0021] The industrial computer 1 communicates with the TCP / IP network communication module 3 in the motion controller 2 through the TCP / IP network. The driver 10 of the motion unit 8 sends motion control commands, and simultaneously colle...

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Abstract

The invention discloses a control system for flexible tools for assembly of wing foreparts. A single-axis servo motor on an SERCOS-III (serial real time communication specification-III) bus node is controlled through a motion controller, and therefore the motion control of a complete set of flexible tools for the assembly of the wing foreparts is realized, and the digital assembly of the wing foreparts is performed. The control system comprises a digital flexible tool, a laser tracker, a robot drilling system integration interface and a software integration platform, and all systems run harmoniously; control command and status return information interaction is implemented between the controller and an actuator unit; distributed motion control is performed on all shafts of the digital flexible tool; control is performed on the shafts of the flexible tool by an IPC (Industrial Personal Computer), and single-point location control is realized on each shaft; each shaft is provided with a grating ruler, and an actual position signal is measured, and is fed back to the control system to realize full-closed loop control of all the shafts. By changing the digital assembly process for the wing foreparts, servo control of different actions can be performed to realize the assembly of the wing foreparts of different types.

Description

technical field [0001] The invention relates to the field of aircraft manufacturing, process equipment and automatic control, in particular to a flexible tooling control system for assembling a wing front flap. Background technique [0002] Aircraft digital flexible assembly technology is the characteristics of the aviation product itself as an assembly object. Based on the digital definition of aircraft products, through the aircraft flexible assembly process, digital assembly technology, assembly tool design, assembly process optimization, automatic positioning and control technology, digital measurement, automatic Drilling, servo control and clamping to achieve fast and accurate positioning and assembly technology of aircraft parts. [0003] Invention patent CN102001451A discloses "a system and method for attitude adjustment and docking of aircraft components based on four numerically controlled positioners, an attitude adjustment platform and a moving bracket". The syst...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B19/414
CPCG05B19/414
Inventor 王仲奇胡玉龙梁青霄任聪李桂香李西宁李金达戴卫康永刚李卫平巴晓甫
Owner NORTHWESTERN POLYTECHNICAL UNIV
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