Integrated forming mold for main beam box body structure of unmanned aerial vehicle

A technology for forming molds and unmanned aerial vehicles, which is applied to household appliances, other household appliances, household components, etc., can solve the problems of complex molding process and difficult integral molding.

Pending Publication Date: 2019-10-18
NINGBO LIGAO COMPOSITE MATERIAL
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Composite materials have excellent designability, but the molding process is more complicate

Method used

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  • Integrated forming mold for main beam box body structure of unmanned aerial vehicle
  • Integrated forming mold for main beam box body structure of unmanned aerial vehicle

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Embodiment Construction

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings that need to be used in the description of the embodiments or the prior art.

[0023] The box body structure of the main beam of the drone of the present invention is made of carbon fiber twill prepreg material, and is designed with a box body structure. in:

[0024] see figure 1 and figure 2 , the integrated molding mold for the main beam box structure of the UAV includes: main body forming tooling 700, 12 sets of positioning tooling 100 for laying, two sets of metal positioning tooling for curing 200, 200a, an expandable mandrel 300, conformal uniform The pressing plates 400, 500, 600 are integrally cured and molded by the autoclave process.

[0025] Three first positioning holes 710 are provided on the main body forming tool 700 .

[0026] During layup, each prepreg layup for positioning is positi...

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Abstract

The invention discloses an integrated forming mold for a main beam box body structure of an unmanned aerial vehicle. The integrated forming mold comprises a main body forming tool, a plurality of positioning tools for prepreg layering, a pair of metal positioning tools for curing, an expandable core mold, and a plurality of conformal pressure equalizing plates, wherein a plurality of first positioning holes are formed in the main body forming tool, each positioning tool for prepreg layering for positioning is positioned and installed on an adapting unit during layering, each adapting unit is positioned in the corresponding first positioning hole, the pair of metal positioning tools for curing are arranged on the left side and the right side of the main beam box body structure of the unmanned aerial vehicle, each metal positioning tool for curing is fixedly connected with the corresponding adapting unit, the metal positioning tools for curing are used for curing and positioning the leftside and the right side of the main beam box structure of the unmanned aerial vehicle under the action of an external force, the expandable core mold is used for forming an inner cavity of the main beam box body structure of the unmanned aerial vehicle, and when the main beam box body structure of the unmanned aerial vehicle is integrally cured and formed through an autoclave process, the plurality of conformal pressure equalizing plates are arranged on the surface of the main beam box body structure of the unmanned aerial vehicle.

Description

technical field [0001] The invention relates to the technical field of manufacturing unmanned aerial vehicle load-bearing structural parts, in particular to an integrated molding mold for the main beam box structure of the unmanned aerial vehicle. Background technique [0002] Long voyage, light weight, low cost, high maneuverability, high security, high concealment and other characteristics are the salient features of drones, and they are also the future development direction of the new generation of drones. The above-mentioned characteristics of the UAV mainly depend on its structural form and the selection of materials, and the composite material mainly composed of carbon fiber is undoubtedly the best choice. Carbon fiber composite materials have the characteristics of light weight, high strength, low thermal expansion coefficient, and fatigue resistance. Using them in the load-bearing structure and other components of drones can achieve effective weight reduction. At pr...

Claims

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Application Information

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IPC IPC(8): B29C70/34B29C70/54B29L31/30
CPCB29C70/342B29C70/54B29L2031/3076
Inventor 胡仲杰岑婵芳刘杰罗杰君董淑强赵景丽何颖
Owner NINGBO LIGAO COMPOSITE MATERIAL
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