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A wing rib conformal tooling for a large aircraft

A technology of rib and tooling, applied in the field of digital assembly of large aircraft, can solve the problems affecting the accuracy of hole making and connection accuracy, etc.

Active Publication Date: 2019-11-19
ZHEJIANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Due to the narrow and long structural characteristics of the wing rib itself, the rib is prone to large deformation during the process of racking and the process of making holes between the rib and the wall plate, which affects the accuracy of the hole making and the accuracy of the connection

Method used

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  • A wing rib conformal tooling for a large aircraft
  • A wing rib conformal tooling for a large aircraft
  • A wing rib conformal tooling for a large aircraft

Examples

Experimental program
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Effect test

Embodiment

[0025] see figure 1 and figure 2 , the shape-preserving tooling includes a shape-preserving frame, a front upper positioning assembly 602 , a rear upper positioning assembly 601 , a front lower positioning assembly 604 and a rear lower positioning assembly 603 . The shape-preserving frame includes a bracing frame 1, rib face retaining parts 201, 202, front beam airfoil connectors 502, 504, rear beam airfoil connectors 501, 503, beam connecting plate bearings 401, 402, 403, 404, and solid The adjustment bolt 7 that is located at the lower end of the support frame. On the side of the support frame 1 away from the rib surface stoppers 201, 202, a number of clamping rivets 31, 32 arranged at intervals along the course for carrying the rib shape-conserving tooling are installed, so as to realize fast clamping on the trolley. Fast clamping and release by the holding mechanism, so as to improve the handling efficiency and quality.

[0026] see Figure 1 to Figure 3 The rib surfa...

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PUM

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Abstract

The invention discloses wing rib shape-preserving tooling of a large aircraft and belongs to the technical field of aircraft digital assembly. The tooling comprises a shape-preserving rack and a frontupper positioning component, a back upper positioning component, a front lower positioning component and a back lower positioning component which are located on the end side of the shape-preserving rack and used for adjusting and positioning the portions between wing ribs and an upper edge and between wing ribs and a lower edge; the shape-preserving rack comprises a supporting rack, a rib surfaceblocking part which is arranged on the supporting rack to clamp and position a wing rib web onto the supporting rack, a front beam wing surface connection part and a back beam wing surface connectionpart which are arranged at two ends of the supporting rack and position the positions of the wing ribs , a front beam and a back beam in the spanwise direction, and an adjustment bolt which is fixedly arranged at the lower end of the supporting rack and used for adjusting and positioning positions of the wing ribs in the spanwise direction. According to the wing rib shape-preserving tooling of the large aircraft, shape preserving of the wing ribs in the process of racking and hole production and positioning of the wing ribs in a wing box can be achieved, so that precision of hole production and connection intensity meet design requirements, and the tooling can be widely applied to the technical field of aircraft assembly.

Description

technical field [0001] The invention relates to the technical field of digital assembly of large aircraft, in particular to a shape-preserving tooling for large-size wing ribs of large aircraft. Background technique [0002] In the process of aircraft assembly, it is usually carried out in sections according to its structural characteristics. First, the parts are assembled into components such as wings, beams, frames, ribs and wall panels in the conformal frame, and then the components are combined into components such as the middle section of the wing, the front Edge, front section, middle section and tail section of the fuselage, etc., and finally complete the docking of each cloth section of the aircraft. [0003] Due to the narrow and long structural characteristics of the wing rib itself, it is prone to large deformation during the mounting process and the rib and wall plate hole making process, which affects the accuracy of hole making and connection accuracy. [0004...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/10B25B11/00
CPCB25B11/00B64F5/10
Inventor 柯臻铮王青李江雄柯映林
Owner ZHEJIANG UNIV