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Carbon Fiber Reinforced Prepreg Material and Forming Method for Its Wrapped Wing

A technology of prepreg and carbon fiber, which can be applied to other home appliances, coatings, applications, etc., and can solve problems such as large alternating stress, vibration, and fatigue cracks

Active Publication Date: 2021-09-21
北京航天天美科技有限公司 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the deformation, vibration, divergence and flutter of the wings during flight, if the vibration deformation is large, it is easy to generate large alternating stress, which is easy to cause fatigue cracks. Structural strength also puts forward higher requirements

Method used

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  • Carbon Fiber Reinforced Prepreg Material and Forming Method for Its Wrapped Wing
  • Carbon Fiber Reinforced Prepreg Material and Forming Method for Its Wrapped Wing
  • Carbon Fiber Reinforced Prepreg Material and Forming Method for Its Wrapped Wing

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0016] The pretreatment of carbon fiber fabrics is carried out in a dielectric barrier discharge reactor for plasma modification at room temperature. High-purity hydrogen sulfide and oxygen mixed gas are introduced between the electrodes of the reaction chamber at a flow rate of 25 mL / min. The volume ratio of hydrogen sulfide to oxygen is 0.3:1, apply 10kHz, 23kV AC power in the dielectric barrier discharge reactor to generate sulfur-containing plasma at room temperature, and apply treatment to the sample for 1-2min.

[0017] Submerge the modified carbon fiber fabric into the PPS resin glue solution at room temperature through a transfer roller, and evenly spread it on both sides of the sample. After standing for a period of time, immerse the resin glue solution again to make the resin soak into the carbon fiber fabric; The excess resin reaches the predetermined thickness to obtain carbon fiber reinforced prepreg cloth, put the carbon fiber cloth soaked in glue on the double-ro...

Embodiment 2-4 and comparative example 1-5

[0020] Examples 2-4 and Comparative Examples 1-4 were prepared by the same process as in Example 1 to obtain laminated structures, specific process parameters were adjusted, and tensile modulus and breaking strength were measured for each sample. In Comparative Example 5, the carbon fiber was not modified, and the method in Example 1 was used for PPS immersion and laminate preparation.

[0021] It can be seen from the test that the tensile modulus and breaking strength of the laminated structure prepared by the carbon fiber reinforced prepreg without surface modification are lower than those after surface modification, and the wings will be affected by complex airflow during flight , produce deformation, vibration and other phenomena, if the vibration deformation is large, it is easy to generate large alternating stress, which is easy to cause fatigue cracks, high elastic modulus can resist stress, avoid large deformation, and high fracture strength Can improve the reliability...

Embodiment 5

[0029] The end of the main beam of the wing includes an upper arc surface 1 and a lower arc surface 2, and the profile is divided into an upper profile 4 and a lower profile 3. Carbon fiber reinforced prepreg is laid on each area of ​​the wing surface, and then the carbon fiber is obtained by heating and curing. Composite wings. The specific carbon fiber composite wing laying wrapping winding molding method, the main steps are as follows: 1) Lay 14 layers of carbon fiber reinforced prepreg cloth at position 4 of the upper profile of the main beam of the wing using transition positioning tooling; 2) Lay down the main beam of the wing 38 layers of carbon fiber-reinforced prepreg are laid on surface 3 using transitional positioning tooling; 3) 4 layers of carbon fiber-reinforced prepreg are spread across the upper arc 1 and lower arc 2 of the main beam of the wing; 4) The main beam of the wing Wrap 4 layers of carbon fiber reinforced prepreg on the side; 5) Heat and cure the laid...

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Abstract

The application relates to a carbon fiber reinforced prepreg material, and a forming method of the wing after being laminated using the material. A dielectric barrier discharge reactor is used for plasma modification at room temperature to obtain a modified carbon fiber fabric. The modified carbon fiber fabric is immersed in the PPS resin glue solution at room temperature through a transfer roller to obtain a carbon fiber reinforced prepreg cloth, and The flaps are obtained by laminating the prepregs. Adding a sulfur-containing atmosphere to the plasma source gas facilitates the improvement of the combination with the sulfur-containing resin, and the plasma treatment can also achieve a roughening effect, which can ultimately improve the elastic modulus and fracture strength.

Description

technical field [0001] The application belongs to the technical field of preparation and application of composite materials, and in particular relates to a preparation method of a carbon fiber reinforced prepreg material, and a molding method for obtaining a wing by laminating the material. Background technique [0002] The missile wing is the main airfoil connected to the missile body, its main function is to generate air lift, lift the missile body, and play a role in stabilizing control. As modern weapons have higher and higher requirements for flight aerodynamic performance, the airfoil of the bomb wing is getting thinner and the bending torsional stiffness is getting smaller and smaller, and its aeroelasticity problem is becoming more and more serious. Conventional wings are made of lightweight alloys or composite materials. At present, carbon fiber reinforced prepregs are used as wings, which have excellent characteristics such as low specific weight. Carbon fiber rei...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29B15/08B29B15/12B29C70/38
CPCB29B15/08B29B15/125B29C70/386B29L2031/7772
Inventor 杨红娜蔡风园修建
Owner 北京航天天美科技有限公司
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