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Laying method of full-height foam sandwich wing surface laying layer

A layer laying and foaming technology, which is applied in the field of integral molding of composite materials, can solve the problems of complexity, many auxiliary forming tools, and difficulty in laying layers, so as to achieve simple operation, reduce the number of forming tools, and reduce the number of layers and layers. The effect of difficulty

Active Publication Date: 2020-02-21
HARBIN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Components manufactured by integral co-curing molding technology require the least number of parts and standard parts, and the highest level of integration, but there are also disadvantages such as difficult laying of layers, and many and complicated auxiliary molding tools.

Method used

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  • Laying method of full-height foam sandwich wing surface laying layer
  • Laying method of full-height foam sandwich wing surface laying layer
  • Laying method of full-height foam sandwich wing surface laying layer

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0057] The wing box section of a certain type of UAV is made of soft skin, soft front and rear beams, and the front, middle and rear three sections of full-height foam are formed at one time by the overall co-curing molding method. The inner profile of the box section is supported by filled full-height foam, and the outer profile is guaranteed by the upper and lower combined molds. There is no gap between the foam and the skeleton and skin. A certain amount of shrinkage is reserved when the foam is machined. Clamped with bolts, molded after curing and formed, polished and trimmed, the quality of the non-destructive testing parts is good, meeting the design index requirements, installed and used, the parts are shown as follows Figure 10 As shown, the steps of laying boxes are as follows Figure 12 shown.

Embodiment 2

[0059] The flap of a certain type of UAV is an integral co-cured structure. During use, the right rear side of the flap was torn in a large area due to collision caused by improper traction. After removing the damaged area, a new full-height foam sandwich was made to restore the structural integrity. Reinforcements are repaired. Reinforcing parts are shown as Figure 13 As shown, the laying steps of reinforcements are as follows Figure 15 shown.

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Abstract

The invention belongs to the technical field of composite material integral forming, and relates to a laying method of a full-height foam sandwich wing surface laying layer. The technical scheme is characterized in that when a full-height foam sandwich wing surface is laid by adopting upper and lower mold closing tools, the skin of the wing surface is divided into an upper part and a lower part, and a framework is divided into an upper part, a middle part and a lower part; and when a framework part laying layer is laid, a foam sandwich is used as a forming tool of the framework to assist layerlaying. The method comprises the steps that laying of a lower skin mold attaching laying layer group is completed on the lower mold closing tool, laying of a framework laying layer group is completedon the foam sandwich, and the framework laying layer group is of a beam type structure; an upper skin lap joint laying layer group is laid on the upper surface of the foam sandwich and the upper surface of the framework laying layer group; and the upper mold closing tool is in butt joint with the lower mold closing tool to finish tool mold closing, and the whole laying process of the laying layers is completed. According to the method, the number of forming tools is greatly reduced, the manufacturing cost is reduced, the laying process of the laying layers is optimized, the laying difficultyof the laying layers is greatly reduced, and the production efficiency is improved.

Description

technical field [0001] The invention belongs to composite material integral forming technology, relates to a composite material integral co-curing forming method, in particular to a laying method of a full-height foam sandwich airfoil layer. Background technique [0002] The full-height foam sandwich airfoil structure is mainly composed of composite material skin (1), composite material skeleton (2) and foam sandwich core (3). figure 1 shown. The full-height foam sandwich airfoil structure has many advantages such as simple structure, light structure weight, greater bending stiffness and strength, fewer parts and standard parts, etc., especially suitable for the wings of medium and small UAVs and general aircrafts Load-bearing components or secondary load-bearing components such as box section, wingtip, empennage stabilizer and control rudder surface. [0003] In order to improve the integration level of the airfoil structure, it is necessary to adopt the integral molding ...

Claims

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Application Information

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IPC IPC(8): B29C70/38B29L31/30
CPCB29C70/38B29L2031/3085
Inventor 章强于领军曹景斌王珺王乃问王松
Owner HARBIN
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