A comprehensive electric loss curing method for carbon fiber reinforced resin matrix composites

A technology for reinforcing resin matrix and composite materials, which is applied in the field of carbon fiber reinforced resin matrix composite material manufacturing, can solve problems such as fiber etching, and achieve the effects of fast heating rate, low energy consumption, and high energy utilization rate

Active Publication Date: 2019-06-11
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of the present invention is to propose a comprehensive electric loss pressure curing method for large-scale carbon fiber reinforced resin matrix composite components, aiming at the problem that it is difficult to effectively heat large components in the existing carbon fiber self-resistance heating method, and the fibers are etched by current under high current density On the basis of controlling the internal current density of the material to be less than the current etching threshold, an alternating electric field is applied to each layer of material, and under the comprehensive action of various forms of electrical loss, a high voltage is applied to achieve high-quality, high-quality carbon fiber reinforced resin matrix composite components. High efficiency, low energy consumption curing

Method used

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  • A comprehensive electric loss curing method for carbon fiber reinforced resin matrix composites
  • A comprehensive electric loss curing method for carbon fiber reinforced resin matrix composites
  • A comprehensive electric loss curing method for carbon fiber reinforced resin matrix composites

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Embodiment approach

[0060] In this embodiment, the heat loss method of the present invention is used to solidify large-scale aerospace hyperboloid components in a high-pressure tank. The aviation hyperboloid large-scale component is made of unidirectional carbon fiber reinforced bismaleic polyimide resin-based composite material prepreg T700 / QY9611, and the laying method is as follows: There are 42 layers of symmetrical layup, the thickness of the single-layer prepreg is 0.25mm, and the projected size of the mold surface is 4500mm×2800mm. Apply a pair of metal sheet electrodes to the edge of the material, and lead out from the cable 3, the cable 3 is hermetically sealed through the flange 2 on the wall of the pressure tank, and lead out of the tank to connect to a multi-output AC power supply. The specific implementation method is as follows:

[0061] Step 1: Prepare for laying; call out the mold 8 from the mold library and place it in the designated layer area; use the method of mechanical rem...

Embodiment 2

[0070] In this embodiment, with the assistance of a hydraulic press, the carbon fiber-reinforced resin-based composite material component is solidified by comprehensive electric loss. In order to reduce manufacturing costs, hydraulic presses can be used for some components with relatively simple shapes and structures. Traditional compression molding uses upper and lower molds as heat sources. For parts with large thickness, the heat transfer speed is slow and the temperature gradient in the thickness direction is large. Curing quality is lower. Such as Figure 5 As shown, the component is laid up by biaxial carbon fiber reinforced epoxy resin-based prepreg KWC-225-40, and the layup method is [0° / 90°] 8 , a total of 16 layers, the projection size of the mold surface is 1300mm×800mm. Similar to Embodiment 1, a pair of metal sheet electrodes are applied to the edge of each layer of prepreg, and the whole material is placed between the upper mold 206 and the lower mold 209 clamp...

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Abstract

The invention discloses a comprehensive electrical loss curing method of a carbon fiber reinforced resin-based composite material. According to the method, paired metal sheets are respectively spreadalong the fiber direction and the direction vertical to fibers in each layer of the carbon fiber reinforced resin-based composite material; independently applying an alternating electric field havingcontinuous changing waveform, frequency and current density among each pair of sheets, and vertical to the fiber direction; vertical to the fiber direction, carbon fibers are the same as a plane-parallel capacitor, polarization loss, leakage conductance loss, free loss and other dielectric loss are generated from a fiber clearance matrix; along the fiber direction, conductance loss is generated bythe fibers under the current effect, and the material is integrally heated and finally cured into a composite material component under the comprehensive effect of lost heat with various modes. The method can realize high efficiency and low energy consumption curing of a large-sized large-thickness carbon fiber composite material component, improving the temperature uniformity of the component ineach direction in the curing process and improving the curing quality of large-sized components.

Description

technical field [0001] The invention relates to a method for manufacturing a carbon fiber reinforced resin-based composite material, in particular to a method for curing a carbon fiber-reinforced resin-based composite material, in particular to a method for curing a carbon fiber-reinforced resin-based composite material through comprehensive electrical loss. Background technique [0002] Carbon fiber reinforced resin matrix composites have become a key material widely used in the aerospace field, and their application occasions have developed from secondary load-bearing components such as aircraft radomes and stabilizer skins to include large spars, wing panels, wing boxes, etc. , the overall fuselage and other main load-bearing components. Aviation carbon fiber composite components have the characteristics of large size and large thickness. For example, the overall wing panel of the Boeing 787 reaches 28.6 meters, the diameter of the fuselage section of the A350 reaches 5.4...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C35/02B29C70/44B29L31/30
CPCB29C35/0272B29C70/44B29L2031/3076
Inventor 李迎光刘舒霆
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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