Composite material machine body skin integral forming tool and technology

A technology of integral molding and skinning of the fuselage, which is applied to other household appliances, household components, household appliances, etc., can solve problems such as weak bonding, honeycomb instability, and upper panel depression, so as to ensure the molding quality and reduce the difficulty of manufacturing , to ensure the effect of accuracy

Pending Publication Date: 2019-05-21
SICHUAN XIN WAN XING CARBON FIBER COMPOSITES
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, the molds used in the overall molding of the fuselage skin are relatively complicated. For the overall honeycomb sandwich structure process, there are co-curing and secondary bonding; but in the co-curing process, the resin fluidity is too good to cause excessive glue flow. Most of the time, the panel will be poor in glue, and the molding pressure will cause the upper panel to sag, the honeycomb will be unstable and slip, and the pressure will be small, which will lead to panel defects and weak bonding, which will make it difficult to control the yield of the fuselage skin

Method used

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  • Composite material machine body skin integral forming tool and technology
  • Composite material machine body skin integral forming tool and technology
  • Composite material machine body skin integral forming tool and technology

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Embodiment Construction

[0035] The present invention will be described in further detail below through specific implementation examples and in conjunction with the accompanying drawings.

[0036] Figure 1 to Figure 4 Shown is a composite fuselage skin overall molding tooling provided by the present invention, including a frame 1 and a tooling plate 2; two opposite surfaces of the frame 1 are provided with installation grooves 3, and the two installation grooves 3 are relatively arranged, and the two ends of the tooling plate 2 are fixedly fixed on the two installation grooves 3; the upper surface of the frame 1 is also equipped with two groups of detachable blocks 4, and the two groups of detachable blocks 4 are respectively Located on both sides of the tooling pattern 2, the inner surfaces of the two groups of detachable blocks 4 and the working surface of the tooling pattern 2 form a continuous surface, and the two groups of detachable blocks 4 and the tooling pattern 2 form a curing chamber 5.

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Abstract

The invention discloses a composite material machine body skin integral forming tool and technology, and relates to the technical field of unmanned aerial vehicle composite material manufacturing. A framework and a tool template are included. Installing grooves are formed in the two opposite faces of the framework, the two installing grooves are oppositely arranged, and the two ends of the tool template are fixedly clamped in the two installing grooves. Two detachable movable blocks are further arranged on the upper surface of the framework and located on the two sides of the tool template correspondingly, a continuous face is formed by the inner side faces of the two detachable movable blocks and the work face of the tool template, and a curing cavity is formed by the two detachable movable blocks and the tool template. The special technology is combined with the special tool, so that integral forming of large-curvature composite material unmanned aerial vehicle machine body skins isachieved.

Description

technical field [0001] The invention relates to the technical field of UAV composite material manufacturing, and in particular, relates to a composite material fuselage skin integral forming tooling and a forming process thereof. Background technique [0002] Advanced composite materials have the advantages of light weight, high strength, high specific stiffness, strong designability, good fatigue fracture resistance, corrosion resistance, and good dimensional stability; at the same time, the use of integrated manufacturing technology can greatly reduce parts and fastening The number of parts is reduced, the structural weight is reduced, and the production cost is reduced. Therefore, most of the drone fuselage skins are currently made of advanced composite materials. [0003] At present, the molds used in the overall molding of the fuselage skin are relatively complicated. For the overall honeycomb sandwich structure process, there are co-curing and secondary bonding; but in...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/44B29C70/54B29C33/30B29L31/30
Inventor 张立旻蒋晓东
Owner SICHUAN XIN WAN XING CARBON FIBER COMPOSITES
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