Preparation molding method of Glare component

A component and aging forming technology, which is applied in the preparation and forming of Glare components and the preparation and forming of metal components, can solve the problems of limited improvement of the forming limit of Glare components, difficulty in springback control, poor forming accuracy, etc., and achieve low production costs. , the effect of high engineering application value and high forming efficiency

Active Publication Date: 2014-07-02
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

But there are following deficiencies: (1), this process needs to carry out plastic forming to the multi-layer aluminum alloy sheets required by Glare components respectively, and the forming efficiency is extremely low; (2), this process utilizes cold forming to respectively carry out plastic forming to aluminum alloy sheets Forming, its springback control is difficult, and the deformation of different thin plate components is superimposed on the hot pressing preparation process, which will bring about a large springback of Glare components and poor forming accuracy; (3), this process can only limitedly improve Glare Due to the forming limit of components, more complex and large deformation components cannot be realized

Method used

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  • Preparation molding method of Glare component
  • Preparation molding method of Glare component
  • Preparation molding method of Glare component

Examples

Experimental program
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Effect test

Embodiment 1

[0032] The first step is to select a 2024-T3 aluminum alloy blank of 500mm×500mm×0.4mm, and perform phosphoric acid anodic oxidation treatment, so that the surface of the 2024-T3 aluminum alloy can obtain a more favorable surface morphology for hot-pressing resin composite;

[0033] The second step is to select and cut S4 high-strength glass fiber reinforced epoxy resin prepreg of 500mm×500mm×0.125mm, and its resin content is 30wt%;

[0034] The third step is to adopt a 3 / 2 orthogonal laminate structure design, and lay composite laminates in the following order: 2024-T3 aluminum alloy / 0°S4 high-strength glass fiber reinforced epoxy resin prepreg / 90°S4 high-strength glass fiber reinforced Epoxy resin prepreg / 2024-T3 aluminum alloy / 0°S4 high-strength glass fiber reinforced epoxy resin prepreg / 90°S4 high-strength glass fiber reinforced epoxy resin prepreg / 2024-T3 aluminum alloy, 2024 per layer - Lay 70g / m between T3 aluminum alloy and S4 high-strength glass fiber reinforced epoxy...

Embodiment 2

[0040] The first step is to select 1000mm×500mm×0.3mm 2060-W (quenched) aluminum-lithium alloy for surface sandblasting, so that the surface of 2060-W aluminum-lithium alloy aluminum alloy can obtain a more favorable surface shape for hot-pressing resin composite. appearance;

[0041] The second step is to select and cut 1000 mm×500 mm×0.125mm S4 high-strength glass fiber reinforced medium temperature epoxy resin prepreg with a resin content of 40wt%;

[0042] The third step is to adopt a 2 / 1 unidirectional laminate structure design, and lay composite laminates in the following order: 2060-W aluminum-lithium alloy / 0°S4 high-strength glass fiber reinforced medium-temperature epoxy resin prepreg / 0°S4 high-strength Glass fiber reinforced medium temperature epoxy resin prepreg / 2060-W aluminum-lithium alloy, each layer of 2060-W aluminum lithium alloy and S4 high-strength glass fiber reinforced medium temperature epoxy resin prepreg is laid at 180g / m 2 epoxy resin film;

[0043] ...

Embodiment 3

[0048] The first step is to select 500mm×500mm×0.35mm 7075-T4 aluminum alloy for surface sandblasting treatment, so that the surface of 7075-T4 aluminum alloy can obtain a more favorable surface morphology for hot-pressing resin composite;

[0049] The second step is to select and cut 500 mm×500 mm×0.125mm S4 high-strength glass fiber reinforced medium temperature epoxy resin prepreg with a resin content of 40wt%;

[0050] The third step is to adopt a 4 / 3 orthogonal laminate structure design, and lay composite laminates in the following order: 7075-T4 aluminum alloy / 0°S4 high-strength glass fiber reinforced medium-temperature epoxy resin prepreg / 90°S4 high-strength glass Fiber reinforced medium temperature epoxy resin prepreg / 7075-T4 aluminum alloy / 0°S4 high strength glass fiber reinforced medium temperature epoxy resin prepreg / 90°S4 high strength glass fiber reinforced medium temperature epoxy resin prepreg / 7075-T4 aluminum Alloy / 0°S4 high-strength glass fiber reinforced medi...

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Abstract

The invention discloses a preparation molding method of a Glare component, and belongs to the field of preparation and molding of composite materials. The method comprises the following steps: treating the surface of an aluminum alloy blank; laying a composite laminate; positioning the composite laminate on a concave die of a differential-pressure molding device; treating by vacuumizing and side pressing; heating the composite laminate to reach the temperature required for realizing the synchronization of solidifying of epoxy resin and age molding of aluminum alloy; performing bidirectional differential-pressure loading on the composite laminate in the differential-pressure molding device to realize the synchronization of the solidification of the epoxy resin and age molding and strengthening of aluminum alloy, thus realizing the preparation of a Glare laminate and integral molding of the component; then clipping redundant blanks on the Glare component. The preparation molding method of the Glare component is applicable to integrated molding of the Glare components of various complex structures, is also high in molding efficiency, outstanding in accuracy, small in resilience and relatively high in engineering application value.

Description

technical field [0001] The invention relates to a method for preparing and forming metal components, in particular to a method for preparing and forming Glare components, and belongs to the field of preparation and forming of composite materials. Background technique [0002] Fiber metal laminates (Fiber Metal Laminates, FMLs) is a kind of interlayer hybrid composite material, which is formed by alternate lamination of metal sheets and fiber composite materials, and cured under a certain temperature and pressure, also known as hyperhybrid laminates. (Super Hybrid Laminates). FMLs combines the characteristics of traditional fiber composite materials and metal materials, and has high specific strength and specific stiffness, excellent fatigue performance and damage tolerance performance. These advantages make FMLs widely used in the aerospace industry. As the second generation of FMLs, Glare laminates are alternately laminated with 0.3-0.5 mm thick aluminum alloy sheets and 0...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B37/10
Inventor 陶杰李华冠胡玉冰郭训忠
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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