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Mold for integrally preparing I-shaped longitudinally-horizontally-stiffened composite panel

A composite material and integrated technology, which is applied in household appliances, other household appliances, household components, etc., can solve the problems that the core mold cannot be pulled out, the core mold cannot be pulled out normally, etc., so as to achieve excellent internal and external surface quality and avoid the deformation of the workpiece , The effect of reducing manufacturing costs

Active Publication Date: 2018-12-07
AVIC BASIC TECH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Whether the traditional prepreg heat / autoclave process or the RTM molding process is used to integrally prepare the "I" type vertically and horizontally reinforced composite wall panels, there is a problem that the mandrel cannot be pulled out.
Due to the left and right flanging of the "I" type ribs, two or more "I" type vertically and horizontally reinforced panels will form a "well"-shaped semi-closed structure. Therefore, the mandrel is unable to come out normally

Method used

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  • Mold for integrally preparing I-shaped longitudinally-horizontally-stiffened composite panel
  • Mold for integrally preparing I-shaped longitudinally-horizontally-stiffened composite panel
  • Mold for integrally preparing I-shaped longitudinally-horizontally-stiffened composite panel

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preparation example Construction

[0033] The preparation process of the "I" type vertically and horizontally reinforced composite wall panels is as follows:

[0034] (1) Lay the criss-cross flanges in the flange positioning line of the lower mold 2 according to the design, and vacuum preform the flange prefabricated body after the pavement is completed;

[0035] (2) Connect the U-shaped mandrel 3-1 and the C-shaped forming die 3-2 to form a combined inner mandrel 3 through bolts, and lay the C-shaped prefabrication on the outside of the C-shaped forming die 3-2 according to the design body, and vacuum preform the prefabricated body;

[0036] (3) Place the combined inner core mold 3 in the sinking positioning groove 2-3 of the lower mold 2, and carry out vacuum presetting on the lower mold 2 and the combined inner core mold 3, so that the combined inner core mold 3 is positioned in the sunken position Accurate positioning in the slot;

[0037] (4) Lay the outer mandrel 4 according to the design and lay the dr...

specific Embodiment 1

[0041] Typical structure such as figure 1 As shown, the skin panel reinforced structure composed of two vertical and two horizontal "I"-shaped ribs has an overall size of 450mm×400mm×150mm (length×width×height), in which the flange of the "I"-shaped rib The width is 60mm, and the skin and "I"-shaped ribs are prepared from dry pre-shaped fabrics, and then injected with low-viscosity resin through the RTM process, and finally cured and formed. We have adopted the solution of the present invention, and all components of the mold are made of P20 steel.

[0042] The upper mold 1 is designed as a female mold, and the slope of the upper mold 1 side to the inner surface is 15°; the bottom surface is designed as a plane, and the length and width of the bottom surface are respectively extended by 10mm on the basis of the theoretical shape of the skin; The mouth positioning groove 1-1 has a length of 40mm, a width of 50mm, a depth of 10mm, and a slope of 10°;

[0043] The lower mold 2 ...

specific Embodiment 2

[0048] "I" type four vertical and four horizontal rib composite wall panels such as Figure 8 As shown, the overall dimensions are 2300mm×1200mm×150mm (length×width×height), in which the flange width of the "I" type rib is 80mm, the skin is made of prepreg, and the "I" type rib is made of dry state The pre-shaped fabric is prepared, then injected with low-viscosity resin through the RTM process, and finally cured and shaped. We have adopted the solution of the present invention. For the consideration of mold cost, the combined inner mandrel 3 and outer mandrel 4 are made of P20 steel, and the rest of the mold is made of 45# steel.

[0049] The upper mold 1 is designed as a female mold, and the slope of the upper mold 1 side to the inner surface is 20°; the bottom surface is consistent with the theoretical surface of the skin, and the length and width of the bottom surface are based on the theoretical shape of the skin. Each is extended by 20mm; the length of the mouth positio...

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Abstract

The invention belongs to the technical field of resin matrix composite forming, and relates to a mold for integrally preparing an I-shaped longitudinally-horizontally-stiffened composite panel. According to the mold for integrally preparing the I-shaped longitudinally-horizontally-stiffened composite panel provided by the invention, a design idea adopting a combined type inner core mold is provided, an uncovered part of an I-shaped flange is designed to be a U-shaped core mold capable of being demolded freely, and then a C-shaped forming mold formed through a block design is connected to the outer surface of the U-shaped core mold through a bolt; and when the longitudinally-horizontally-stiffened panel prepared by adopting the core mold is demolded, the U-shaped core mold can be firstly demolded, and then the C-shaped forming mold is sequentially taken out according to the design sequence along the direction perpendicular to an I-shaped stiffener web member. Meanwhile, based on an RTMforming process requirement, a whole set of design idea of the forming mold suitable for the I-shaped longitudinally-horizontally-stiffened panel is provided.

Description

technical field [0001] The invention belongs to the technical field of resin-based composite material molding, and relates to a mold for integrally preparing "I" type vertically and horizontally reinforced composite material wall panels. Background technique [0002] At present, composite materials are used in more and more parts of the aircraft, and the advantages of advanced composite materials such as high specific strength, high specific stiffness and designability are used to reduce structural weight and improve aircraft maneuverability or carrying capacity. Reinforced panel composite structure has become a widely used structural form of composite fuselage, wing and empennage due to its good stiffness. The commonly used reinforced wall panels can be divided into "T" type, "J" type, "I" type and mixed type reinforced wall panels according to the different cross-sections of the ribs. [0003] The traditional molding method is to use the prepreg / autoclave process to cure ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/54B29L31/30
CPCB29C70/54B29L2031/3076
Inventor 李伟东包建文罗楚养钟翔屿李晔张朋秦永乐赵秀芬
Owner AVIC BASIC TECH RES INST
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