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Composite wallboard structure of impact-resistant foam metal composite material for aircraft manufacturing

A foam metal and aircraft manufacturing technology, applied in the fuselage bulkhead, fuselage insulation, etc., can solve the problems of poor impact resistance and sound insulation performance, affecting the comfort of cabin members, and heavy structural weight, etc., to achieve good deformation and Energy absorption performance, improve low-frequency sound absorption effect, and improve the effect of sound insulation

Active Publication Date: 2022-07-22
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At the same time, the area where the propeller blade tip is closest to the fuselage has the loudest noise, which seriously affects the comfort of cabin crew members. Therefore, composite panels with impact resistance and high sound insulation performance are required to meet the requirements.
[0003] The existing turboprop composite panel structure adopts a "typical panel + damping + sound-absorbing cotton + decorative panel" structure, with an area density of 6.01kg / m 2 , the total sound insulation is 37.3 dB, and the sound insulation in the 125Hz frequency band is 25.2dB. Its structure is heavy, and its impact resistance and sound insulation performance are poor. Therefore, there is an urgent need for a sound insulation and impact resistance. Lightweight composite siding construction

Method used

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  • Composite wallboard structure of impact-resistant foam metal composite material for aircraft manufacturing
  • Composite wallboard structure of impact-resistant foam metal composite material for aircraft manufacturing
  • Composite wallboard structure of impact-resistant foam metal composite material for aircraft manufacturing

Examples

Experimental program
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Effect test

Embodiment 1

[0035] like figure 1 , 2 As shown, a composite wall panel structure of an impact-resistant foam metal composite material for aircraft manufacturing includes a sound-absorbing core material 1, a transition connecting layer 2 arranged at the upper and lower ends of the sound-absorbing core material 1, and a transition connecting layer 2 on the transition connecting layer 2 away from the absorbing material. The glass fiber protective layer 3 connected on one side of the acoustic core material 1, and the outer skin 4 connected with the glass fiber protective layer 3 on the side away from the transition connecting layer 2;

[0036] The sound-absorbing core material 1 includes a first substrate layer 11 and a second substrate layer 12 formed by 30 umbrella-shaped hollow tube frames 10 arranged in a matrix. The first substrate layer 11 and the second substrate layer 12 are symmetrically distributed up and down and each The opening of the umbrella-shaped hollow pipe frame 10 faces th...

Embodiment 2

[0045] What this embodiment records is the preparation method of the open-cell aluminum foam in Example 1, comprising the following steps:

[0046] S1. Use a supersonic gas atomizing furnace to prepare aluminum alloy powder, and use an ultrasonic vibrating screen to sieve to obtain a powder with a particle size of -100 mesh;

[0047] S2, place the above-mentioned aluminum alloy powder and sodium chloride particles in a mixer in a ratio of 1:5 by weight, and mix and stir for 2h at a rate of 450r / min to obtain a mixture;

[0048] S3. Put the mixture into an aluminum casing, and use a vacuum pump to degas until the degree of vacuum is less than 5×10 - 3 Pa, and then, under the conditions of a temperature of 450 ° C and a pressure of 120 MPa, using a hot isostatic pressing machine for hot isostatic pressing for 2 hours to obtain a hot compact;

[0049] S4, take out the hot compact from the mold of the hot isostatic press, and at room temperature, use ultrasonic cleaning for 2 ho...

Embodiment 3

[0054] What is described in this example is also the preparation method of the open-cell aluminum foam in Example 1. The difference between this example and Example 2 is that the parameters are different, which specifically includes the following steps:

[0055] S1. Use a supersonic gas atomizing furnace to prepare aluminum alloy powder, and use an ultrasonic vibrating screen to sieve to obtain a powder with a particle size of 200 meshes;

[0056] S2, place the above-mentioned aluminum alloy powder and sodium chloride particles in a mixer in a ratio of 1:5 by weight, and mix and stir at a rate of 480r / min for 2.5h to obtain a mixture;

[0057] S3. Put the mixture into an aluminum casing, and use a vacuum pump to degas until the degree of vacuum is less than 5×10 - 3 Pa, and then, under the conditions of a temperature of 480 ° C and a pressure of 140 MPa, a hot isostatic pressing process is performed for 3 hours using a hot isostatic pressing machine to obtain a hot compact; ...

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Abstract

The invention provides a composite wallboard structure of an anti-impact foam metal composite material for aircraft manufacturing, and belongs to the technical field of aircraft manufacturing. Comprising a sound absorption core material, transition connection layers arranged at the upper end and the lower end of the sound absorption core material, two glass fiber protection layers connected with the sides, away from the sound absorption core material, of the transition connection layers, and outer skin connected with the sides, away from the transition connection layers, of the glass fiber protection layers. Components among the sound absorption core material, the transition connection layer, the glass fiber protection layer and the outer skin are connected compactly, the overall mechanical strength of the composite wall plate structure is high, the impact resistance characteristic is good, meanwhile, the open-cell foamed aluminum with the high porosity is adopted, the low-frequency sound absorption effect of the composite wall plate structure can be improved, and meanwhile the composite wall plate structure can be used for sound absorption. And the weight of the composite wall plate structure can be reduced, and the comfort in a cabin of an airplane is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft manufacturing, in particular to a composite wall plate structure of an impact-resistant foam metal composite material for aircraft manufacturing. Background technique [0002] A turboprop is an aircraft powered by a turboprop engine, and the fuselage panels near the tips of the propeller blades must be strong and rigid enough to withstand the effects of propeller-induced vibration and propeller ice throwing. At the same time, the area where the propeller blade tip is closest to the fuselage is the loudest, which seriously affects the comfort of cabin crew members. Therefore, composite wall panels with impact resistance and high sound insulation performance are required to meet the requirements. [0003] The existing turboprop composite siding structure adopts the "typical siding + damping + sound-absorbing cotton + decorative panel" structure, with an areal density of 6.01kg / m 2 , the total soun...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/10B64C1/40
CPCB64C1/10B64C1/40B64C2001/0072Y02T50/40
Inventor 王鑫刘小川白春玉王彬文何石
Owner CHINA AIRPLANT STRENGTH RES INST
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