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Integral forming method of composite material structural member comprising double-curved-surface profile structure

A composite material and integral molding technology, which is applied in the field of composite material molding, can solve the problems of unfavorable weight loss and comprehensive performance guarantee of the whole machine

Inactive Publication Date: 2015-02-25
SHENYANG AIRCRAFT CORP
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At present, foreign countries have already mastered the overall molding and effective demoulding technology of the hyperbolic composite structural parts of the tail section of the fuselage. The mode of assembling parts into a whole is not conducive to the weight reduction of the whole machine and the guarantee of comprehensive performance

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  • Integral forming method of composite material structural member comprising double-curved-surface profile structure
  • Integral forming method of composite material structural member comprising double-curved-surface profile structure
  • Integral forming method of composite material structural member comprising double-curved-surface profile structure

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Embodiment Construction

[0019] A method for integral forming of a composite material structural part containing a hyperboloid surface structure, comprising the following steps:

[0020] 1) if Figure 1 to Figure 4 As shown, a number of groups of hydraulic rods 2 are respectively arranged around the central main shaft 3, and wall panel forming tooling 1 is connected to the hydraulic rods 2. After the hydraulic rods are stretched out, between every two panel forming tooling The wall panel auxiliary tooling 4 is connected by fasteners, and the positioning block is used to make the wall panel auxiliary tooling 4 and the wall panel forming tooling 1 realize accurate positioning, so as to ensure that the outer circumference of the wall panel auxiliary tooling 4 and the wall panel forming tooling 1 is hyperbolic as a whole The overall forming tooling of the barrel section structure of the profile;

[0021] 2) Adhesive sealing material is used at the connection between the auxiliary panel tooling 4 and the ...

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Abstract

The invention relates to an integral forming method of composite material structural member comprising a double-curved-surface profile structure. The integral forming method comprises the following steps: 1), arranging hydraulic rods around a central spindle, and connecting a wall board assisting tool between each two wall board forming tools through a fastening member after the hydraulic rods are unfolded, where the hydraulic rods are connected with wall board forming tools; 2), bonding a sealing material between the wall board assisting tools and the wall board forming tools; 3), coating a demoulding agent on the outer surface of an integral forming tool, winding prepreg on the surface of the integral forming tool, and making an uncured composite material blank; 4), integrally encapsulating the double-curved-surface composite material blank and the integral forming tool, and utilizing an autoclave for curing and forming; 5), after curing and forming, realizing easy demoulding. By the integral forming method, on the basis that integral forming of the composite material structural member of a machine body tail section structure is realized, effective integral demoulding of the composite material structural member after curing can be realized.

Description

technical field [0001] The invention relates to an integral molding method for a composite material structural part with a hyperboloid surface structure, which is suitable for the integral molding and demoulding of the composite material structural part with a hyperbolic surface structure at the tail section of a fuselage, and belongs to the technical field of composite material forming. Background technique [0002] The traditional manufacturing method of hyperbolic structural composite material structural parts of the tail section of the fuselage usually adopts the method of manufacturing the structural wall panels of the tail section of the fuselage in blocks, and then combines the block parts into a barrel structural composite material through machining and assembly processes The schema of the frame. Due to the existence of a large number of machining and assembly processes, not only is it easy to cause delamination of the composite material block parts during the machin...

Claims

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Application Information

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IPC IPC(8): B29C70/44
CPCB29C70/44B29C70/542
Inventor 王乾蒲永伟
Owner SHENYANG AIRCRAFT CORP
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