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A method for integral co-curing molding of UAV wings

A curing molding and unmanned aerial vehicle technology, applied in aircraft assembly, weight reduction, etc., can solve the problems of high technical requirements for operators, long preparation time, and unstable overall quality, so as to achieve obvious advantages, avoid inspection workload, The effect of avoiding hole sealing problems

Active Publication Date: 2022-07-05
GUANGLIAN AVIATION IND CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantages of this method are: each part needs to be machined, the work efficiency is low, and the progress is slow; most parts are processed by cutting, the material utilization rate is low, and a lot of material is wasted; a large number of molds and frames are required. It takes a long time to prepare equipment, and it is not easy to change midway; most of them use riveting technology, and the labor cost is too high; closed spaces can only use riveting technology, and the strength is low; the technical requirements for operators are high, and the overall quality is not stable

Method used

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  • A method for integral co-curing molding of UAV wings
  • A method for integral co-curing molding of UAV wings
  • A method for integral co-curing molding of UAV wings

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specific Embodiment approach 1

[0049] Specific implementation one: as Figure 1-Figure 4 , Figure 16-Figure 18 As shown, this embodiment discloses a method for integral co-curing molding of a UAV wing, the method comprising the following steps:

[0050] Step 1: Assemble the wing frame 15;

[0051] Two beams 15-2 are pre-laid with front and rear beam forming molds (for the prior art), and the pre-laid two beams 15-2 are arranged in parallel, and four rib boxes 15-1 are pre-laid with foam. Three of the rib boxes 15-1 laid on the foam are arranged close to the front ends of the two beams 15-2, and the three rib boxes 15-1 are all connected with the fork ears 15-3 provided at the front ends of the two beams 15-2. They are arranged in parallel, and the three rib boxes 15-1 and the two beams 15-2 are arranged alternately in turn. -1 is respectively fixedly connected with a corresponding beam 15-2, and the remaining rib box 15-1 laid on the foam is placed against the rear ends of the two beams 15-2 to form a w...

specific Embodiment approach 2

[0064] Embodiment 2: This embodiment is a further description of Embodiment 1. In step 3, the cleanliness of the air in the purification room is that the content of dust particles with a diameter greater than 10 μm is not greater than 10 / L.

specific Embodiment approach 3

[0065] Embodiment 3: This embodiment is a further description of Embodiment 1 or 2. In step 4, when the ambient temperature and humidity conditions meet the requirements, the temperature is 18-22°C, and the humidity is less than 25-30%.

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Abstract

An integral co-curing molding method for an unmanned aerial vehicle wing belongs to the field of aviation composite material molding. The method steps are: step 1: assembling the wing frame; step 2: assembling the lower mold; step 3: making the lower wing surface skin of the wing in the assembled lower mold mold, and reserving the upper wing surface skin when paving step 4: positioning the wing frame; step 5: making the upper wing surface skin; step 6: assembling the upper mold; step 7: curing and demoulding. The wing prepared by the method of the present invention can be molded at one time, which improves the strength, saves the cost, and improves the manufacturing speed.

Description

technical field [0001] The invention belongs to the field of aviation composite material forming, and in particular relates to an integral co-curing forming method for an unmanned aerial vehicle wing. Background technique [0002] The traditional wing manufacturing method is to first use the mechanical processing method to manufacture wing structural parts such as wing ribs, main beams, leading edges, etc., and then assemble the parts on the assembly frame through the riveting process. The individual pipes are installed in the wing frame. The wing skin is then fabricated by tooling and then assembled by riveting. The disadvantage of this method is that it needs to be machined for each part, the work efficiency is low, and the progress is slow; most parts are processed by cutting, the material utilization rate is low, and a lot of materials are wasted; a large number of molds and frames are required to produce Preparing equipment, the preparation time is long in the early s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/10
CPCB64F5/10Y02T50/40
Inventor 林琳杨亮吴昊耿绍坤杨智儒
Owner GUANGLIAN AVIATION IND CO LTD
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