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A method for preparing thermoplastic composite aircraft horizontal tail leading edge skin

A composite material and leading edge skin technology, which is applied in the field of preparing textile structure carbon fiber reinforced thermoplastic composite aircraft flat tail leading edge skin, which can solve the problems of high product porosity, poor fiber wettability, and insufficient strength and toughness of the matrix itself

Inactive Publication Date: 2019-01-11
DONGHUA UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the PPS-CFF composite material prepared based on the traditional carbon fiber fabric thermocompression molding method has not been widely promoted because of its poor wettability of the resin to the fiber, high porosity of the product, and low fiber volume content. The strength and toughness of the matrix itself are not high enough

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] A method for preparing a thermoplastic composite aircraft leading edge skin, firstly, surface treatment is performed on the CFF before laminating the CFF and the PPS film, and the steps of the surface treatment are:

[0033] (1) fully mix surface modifier KH-570 and solvent acetone by mass percentage 1%;

[0034] (2) Put CFF in N 2 At 350 ℃, de-sizing and activation treatment was carried out for 3 hours;

[0035] (3) placing the CFF treated in step (2) in the solution prepared in step (1) at 20°C, soaking for 1 hour, and then placing it in a 70°C oven for drying treatment for 6 hours to obtain a surface-treated CFF CFF.

[0036] Then do the following steps:

[0037] (1) Melting: CFF and PPS film with a weight-average molecular weight of 30,000 are alternately laminated for 3 layers, the upper and lower layers are PPS films, and the temperature is raised to 320° C. to melt all the PPS films;

[0038] (2) Wetting: After the PPS film is completely melted, the PPS melt an...

Embodiment 2

[0045] A method for preparing a thermoplastic composite aircraft leading edge skin, firstly, surface treatment is performed on CFF before laminating CFF and PPS non-woven fabric, and the surface treatment steps are:

[0046] (1) fully mix surface modifier KH-570 and solvent acetone by mass percentage 10%;

[0047] (2) Put CFF in N 2 At 500 ℃, the desizing and activation treatment was carried out for 5 hours;

[0048] (3) placing the CFF treated in step (2) in the solution prepared in step (1) at 80° C., soaking for 8 hours, and then placing it in a 100° C. oven for drying treatment for 10 hours to obtain a surface-treated CFF CFF.

[0049] Then do the following steps:

[0050] (1) melting: the PPS non-woven fabric with a weight-average molecular weight of 120,000 is alternately laminated 51 layers and placed in the mold, so that the upper and lower layers are PPS non-woven fabrics, and the temperature is raised to 340 ℃, so that all the PPS non-woven fabrics are melted;

...

Embodiment 3

[0058] A method for preparing a thermoplastic composite aircraft leading edge skin, firstly, surface treatment is performed on CFF before laminating CFF and PPS non-woven fabric, and the surface treatment steps are:

[0059] (1) fully mix the surface modifier SKE-1 with the solvent acetone by mass percentage 1%;

[0060] (2) Put CFF in N 2 At 400 °C, the desizing and activation treatment was carried out for 5 hours;

[0061] (3) placing the CFF treated in step (2) in the solution prepared in step (1) at 50°C, soaking for 8 hours, and then placing it in a 100°C oven for drying treatment for 10 hours to obtain a surface-treated CFF CFF.

[0062] Then do the following steps:

[0063] (1) Melting: Alternate lamination of CFF and PPS non-woven fabric with a weight-average molecular weight of 30,000 is a total of 43 layers, so that the upper and lower layers are PPS non-woven fabrics, and the temperature is raised to 340 ° C, so that all the PPS non-woven fabrics are melted;

[...

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Abstract

The invention discloses a method for preparing a thermoplastic composite material airplane horizontal tail leading-edge sheath, wherein the method comprises the steps: alternately laminating a reinforcing fiber fabric and a PPS thin film material, and heating up to 320-340 DEG C, to make PPS completely molten; then pressurizing to 0.5-2.1 MPa, and making the reinforcing fiber fabric fully infiltrated with the PPS; cooling the PPS / reinforcing fiber fabric at the cooling rate of 40-100 DEG C / min, after cooling to 240 DEG C-260 DEG C, pressurizing to 3-7 MPa, and maintaining the pressure for 5-10 min; releasing the pressure to normal pressure, and naturally cooling to room temperature; and heating the obtained material to 270-280 DEG C, putting into a 230-250 DEG C airplane leading-edge sheath mold, increasing the mold pressure to 1-8 MPa in 15-30 s, and maintaining the pressure for 1-4 min at the maximum pressure. The tensile strength of the product reaches 600-1000 MPa, the modulus is 58-70 GPa, and the impact strength is 50-90 kJ / m<2>.

Description

technical field [0001] The invention relates to the technical field of aircraft structural component preparation, in particular to a method for preparing a textile structure carbon fiber reinforced thermoplastic composite material aircraft flat tail leading edge skin. Background technique [0002] The main function of the leading edge of the aircraft horizontal tail (flat tail) is to prevent or reduce the damage to the wing caused by bird strikes (material open physical trauma). In order to ensure the safety of aircraft flight, the materials used in the preparation of the leading edge of the horizontal tail have very strict requirements on size, performance and stability. According to its role in the aircraft structure and possible damage during use, it is currently believed that in addition to the basic high strength, light weight, corrosion resistance and other requirements for the preparation of the flat tail leading edge, the most important performance requirements are: ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/54
CPCB29C70/34
Inventor 余木火朱姝孙泽玉徐英凯姜正飞杨洋刘卫平姜丽萍袁象恺
Owner DONGHUA UNIV