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Integrated full-aircraft assembly tool

An assembly tooling and integrated technology, which is applied in the direction of aircraft assembly, etc., to achieve the effect of improving the quality and competitiveness of drones and shortening the development cycle

Active Publication Date: 2021-07-16
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to meet the development needs of new small and medium-sized UAVs, it is necessary to propose an integrated tooling for UAV assembly, so that the front fuselage, middle fuselage, rear fuselage, wing assembly, alignment and finishing of the UAV are integrated into the The implementation of the same tooling ensures the high performance and short development cycle of the new series of drones, and at the same time greatly reduces the cost of tooling and improves the quality and competitiveness of drones. At present, there is no tooling for the assembly of drones. Related reports

Method used

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  • Integrated full-aircraft assembly tool

Examples

Experimental program
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Effect test

Embodiment 1

[0034] The main structure of this embodiment, such as figure 1 As shown, it includes a skeleton assembly 1, on which a nose cone positioning assembly 2, a front landing gear assembly 3, a clamping plate positioning assembly 4, a drilling template assembly 5, a wing assembly 6, a cooling tube assembly 7, Frame beam positioning assembly 8, the nose cone positioning assembly 2 is placed at the front end of the skeleton assembly 1, the front landing gear assembly 3 is placed behind the nose cone positioning assembly 2, and the drilling template assembly 5 is distributed on the skeleton assembly 1 In the middle part, the wing assembly 6 is distributed on both sides of the frame assembly 1, the cooling tube assembly 7, the frame beam positioning assembly 8 are placed at the rear of the frame assembly 1, and the clamp positioning assembly 4 is positioned with the frame beam The components 8 are all arranged on the upper part of the skeleton component 1 .

Embodiment 2

[0036] On the basis of the above-mentioned embodiments, this embodiment further defines the structure of the frame assembly 1, such as figure 2As shown, the frame assembly 1 is mainly composed of a frame body 11, angle braces 12 and anchor bolts 13; the frame body 11 is a giant frame composed of a plurality of square steel and steel plates for supporting and installing tool positioners , The square steel is connected by 12, which is convenient for disassembly, and meets the requirements of green manufacturing. The lower part of the skeleton main body 11 is provided with a number of anchor bolts 13, which can be used for leveling the tooling skeleton to achieve the role of support. Other parts of this embodiment are the same as those of the foregoing embodiment, and will not be repeated here.

Embodiment 3

[0038] On the basis of the foregoing embodiments, this embodiment further defines the structure of the nose cone positioning assembly 2, such as image 3 , Figure 4 As shown, the nose cone positioning assembly 2 is mainly composed of a column 21, a double guide rod positioner 22, a nose cone clamping plate 23, a frame positioning plate 24, a latch 25, an end face clamping plate 26, a web stringer positioner 27 and a connection The support 28 is formed; the nose cone clamping plate 23 is welded into a cross shape by four clamping plates, and the profile of each clamping plate is consistent with the profile of the nose cone of the aircraft; Linear movement pushes the nose cone clamping plate 23 to press the nose cone of the aircraft for positioning; the frame positioning plate 24 and the end face clamping plate 26 position and hold the aircraft frame through the positioning pin 25 and the web stringer positioner 27. Other parts of this embodiment are the same as those of the f...

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Abstract

The invention discloses an integrated full-aircraft assembly tool. The tool comprises a framework assembly, the framework assembly is provided with a nose cone positioning assembly, a front landing frame assembly, a clamping plate positioning assembly, a drill plate assembly, wing assemblies, a heat dissipation cylinder assembly and a frame beam positioning assembly, the nose cone positioning assembly is arranged at the foremost end of the framework assembly, the front landing frame assembly is arranged behind the nose cone positioning assembly, the drill plate assembly is distributed in the middle of the framework assembly, the wing assemblies are distributed on the two sides of the framework assembly, the heat dissipation cylinder assembly and the frame beam positioning assembly are arranged on the rear portion of the framework assembly, and the clamping plate positioning assembly and the frame beam positioning assembly are both arranged on the upper portion of the framework assembly. According to the invention, technologies of modularization, detachable parts, rapid tool resetting and the like are adopted at multiple positions, and the procedures of assembling, folding, finish machining and the like of the whole aircraft body are integrated on one set of tool platform, so that the requirements of high performance and short development period of novel series unmanned aerial vehicles are ensured, the corresponding speed of the tool is increased, and the manufacturing cost is saved.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicle assembly tooling, in particular to an integrated whole-machine assembly tooling. Background technique [0002] The production of drones presents the characteristics of multiple varieties, small batches, and frequent changes. In order to meet the needs of the market, use and technology development, compared with traditional models, the development cycle of UAV development is very short, and the speed of upgrading and replacement is also very fast, which poses a huge challenge to the traditional development model. In order to meet the development needs of new small and medium-sized UAVs, it is necessary to propose an integrated tooling for UAV assembly, so that the front fuselage, middle fuselage, rear fuselage, wing assembly, alignment and finishing of the UAV are integrated into the The implementation of the same tooling ensures the high performance and short development cycle of ...

Claims

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Application Information

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IPC IPC(8): B64F5/10
CPCB64F5/10
Inventor 赵颖邓军石章虎陈雪梅
Owner CHENGDU AIRCRAFT INDUSTRY GROUP