Airplane cargo hold floor with glass fiber reinforced panel aramid fiber honeycomb core sandwich structure

Abstract

The utility model discloses a glass fiber reinforced panel aramid fiber honeycomb core sandwich structure aircraft cargo hold floor, which comprises an upper skin, a honeycomb core and a lower skin, the upper skin and the lower skin are both formed by paving multiple layers of phenolic resin glass fiber fabric prepregs, the number of the prepregs of the upper skin is larger than that of the prepregs of the lower skin, and the honeycomb core is arranged in the honeycomb core. The honeycomb core is an aramid fiber honeycomb core, and the upper skin, the lower skin and the honeycomb core are bonded through adhesive film layers. The honeycomb core sandwich structure has the advantages that each layer of material of the honeycomb core sandwich structure and the adhesive film layer are formed through co-curing, a single part does not need to be cured and then glued, the product structure is stable, the strength is improved, the material performance of the raw material skin, the honeycomb core and the adhesive film layer is excellent, and the quality of the manufactured product reaches or exceeds the same level of imported products; and localization is realized, raw material cost is effectively controlled, manufacturing and management cost is greatly reduced, and controllable production is realized.

Description

Technical Field

[0001] This utility model relates to the field of non-metallic materials technology, and in particular to an aramid honeycomb core sandwich structure material for aircraft cargo hold flooring. Background Technology

[0002] With the development of my country's civil aircraft, more and more components have been localized. However, most of the cargo hold floors of aircraft are imported from abroad, which leads to problems such as long procurement cycles, uncontrollable prices, untimely after-sales service, and uncontrollable costs for users. Therefore, achieving localization of such products is conducive to reducing the bottlenecks in the development of my country's aircraft manufacturing industry and improving product performance through improvements. Utility Model Content

[0003] Purpose of this utility model: The purpose of this application is to provide an aramid honeycomb core sandwich structure material for aircraft cargo hold floors, which improves product performance and reduces costs.

[0004] Technical solution: A glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo compartment floor, comprising an upper skin, a honeycomb core, and a lower skin. The upper skin and the lower skin are both composed of multi-layer phenolic resin glass fiber fabric prepreg, with the upper skin having more prepreg layers than the lower skin. The honeycomb core is an aramid honeycomb core, and the upper skin, the lower skin, and the honeycomb core are all bonded together with an adhesive film layer.

[0005] Furthermore, the upper skin has 5 prepreg layers, and the lower skin has 3 prepreg layers. The upper skin has more prepreg layers than the lower skin for two reasons: firstly, to better distinguish the load-bearing surfaces, with the upper skin being the primary load-bearing surface; and secondly, to calculate and design the layered structure based on the selected materials.

[0006] Furthermore, all five layers of prepreg in the upper skin have their weft yarn face downwards towards the honeycomb core, and all three layers of prepreg in the lower skin have their weft yarn face upwards towards the honeycomb core. The weft yarn surface increases the contact area between the honeycomb core and the prepreg, improving the overall peel strength of the cargo hold floor.

[0007] Furthermore, the laying angle of the five layers of prepreg in the upper skin is 0° / 90°, and the laying angle of the three layers of prepreg in the lower skin is 0° / 90°.

[0008] Furthermore, the prepreg is a fabric with a warp angle of 0° and a weft angle of 90°.

[0009] Furthermore, the honeycomb core is a high-density aramid honeycomb core with a density of 144±6 kg / m³. 3 .

[0010] Furthermore, the adhesive film layer is a modified epoxy resin adhesive.

[0011] Furthermore, the upper skin, adhesive film layer, honeycomb core, adhesive film layer, and lower skin are heat-pressed and cured to obtain a sandwich structure.

[0012] Beneficial effects: The advantages of this utility model are: the materials of each layer of the honeycomb core sandwich structure and the adhesive film layer are co-cured and formed, eliminating the need for curing and bonding individual parts. The product structure is stable and the strength is improved. The material properties of the raw materials skin, honeycomb core and adhesive film layer are excellent. The quality of the product reaches or exceeds the same level as imported products. It realizes localization, effectively controls the cost of raw materials, greatly reduces manufacturing and management costs, and achieves controllable production. Attached Figure Description

[0013] Figure 1 This is an exploded view of the product structure of this utility model. Detailed Implementation

[0014] The present invention will be further explained below with reference to the accompanying drawings and specific embodiments.

[0015] A glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo compartment floor, as shown below. Figure 1 As shown, it includes an upper skin 1, a film layer 4, a honeycomb core 2, a film layer 4, and a lower skin 3.

[0016] The lower skin 3 is composed of three layers of phenolic resin fiberglass fabric prepreg, each layer being designated as PL01, PL02, and PL03. Each prepreg layer is a 0° warp × 90° weft fabric. When laying the three prepreg layers, the weft side faces upward toward the lower surface of the honeycomb core 2, and the warp side faces downward. During product manufacturing, it is bonded to the molding fixture. The laying angle of the three prepreg layers is 0° / 90°.

[0017] The upper skin 1 is composed of 5 layers of phenolic resin glass fiber fabric prepreg, each layer is designated as PL04, PL05, PL06, PL07 and PL08 respectively. Each layer of prepreg is a 0° warp × 90° weft fabric. When laying the 5 layers of prepreg, the weft side faces down towards the upper surface of the honeycomb core 2 and the warp side faces up. The laying angle of the 5 layers of prepreg is 0° / 90°.

[0018] Honeycomb core 2 is a high-density aramid honeycomb core with a density of 144±6 kg / m³. 3 .

[0019] The upper skin 1 is bonded to the upper surface of the honeycomb core 2 with an adhesive film layer 4, and the lower skin 3 is bonded to the lower surface of the honeycomb core 2 with an adhesive film layer 4. The adhesive film layer 4 is a modified epoxy resin adhesive, which can enhance the overall peel strength, flexural strength, and shear strength of the cured cargo hold floor.

[0020] The prepreg used is a flame-retardant phenolic resin glass fiber fabric prepreg (model ML6035 / 300F) made by Jiangsu Meilong Aviation Components Co., Ltd. Its physical properties, mechanical properties, formaldehyde release and flame retardant properties are listed in Tables 1 to 4.

[0021] Table 1

[0022]

[0023] Table 2

[0024]

[0025]

[0026] Table 3

[0027]

[0028] Table 4

[0029]

[0030] The properties of the adhesive film layer are listed in Table 5.

[0031] Table 5

[0032]

[0033] The room temperature mechanical properties of the honeycomb core are listed in Table 6.

[0034]

[0035] Table 6

[0036] The preparation method of the above-mentioned glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo compartment floor is as follows:

[0037] S10: Cut the honeycomb core according to the product dimensions and clean it;

[0038] S20: Drying the honeycomb core;

[0039] S30: Cut the prepreg and film layers according to the product dimensions (one standard dimension: 1240mm in the L direction × 2440mm in the W direction, length and width tolerance: (-0, +10)mm), with a total of 8 layers of prepreg cut;

[0040] S40: Layup preparation. Place a flat plate on the workbench with wheels to support the uncured cargo hold floor product and prevent the prepreg and honeycomb core from shifting or twisting during placement and transportation. Lay a layer of release paper on the flat plate to protect the honeycomb core surface from contamination and subsequent demolding. Then move it to the clean room.

[0041] S50: Lay the prepreg and honeycomb core together to form the prefabricated body. During the layup, each layer of prepreg PL01 laid on the molding fixture, prepreg PL04 ​​laid on the upper surface of the honeycomb core, and prepregs PL02, PL03, PL05, and PL06 is vacuum compacted. The vacuum degree during compaction is not lower than -0.06MPa, and the time is not less than 5 minutes. After the honeycomb core is positioned, the vacuum degree during compaction does not exceed -0.034MPa to prevent the honeycomb core from slipping. Prepreg splicing requirements: overlap 12mm-19mm; Adhesive film splicing requirements: maximum overlap 6mm, maximum gap 1.5mm; the adhesive film extends to the edge of the honeycomb core or exceeds the edge of the honeycomb core by a maximum of 13mm.

[0042] S60: Transfer the preform to the hot press workbench for integral curing;

[0043] S70: After curing, demolding, trimming of flash, and removal of burrs are performed to obtain a sandwich structure aircraft cargo hold floor product.

[0044] The glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo floor of this application adopts co-curing molding, eliminating the need for curing individual parts and then gluing them together. This is beneficial to the structural stability and strength of the product. All raw materials are domestically produced, effectively controlling raw material costs and greatly reducing manufacturing and management costs, thus achieving controllable production. The resulting product has been tested and shows excellent performance, which is listed in Table 7.

[0045] Table 7

[0046]

[0047] The glass fiber reinforced panel aramid honeycomb core sandwich structure of this application has excellent performance in aircraft cargo compartment flooring.

Claims

1. A glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo hold floor, characterized in that: It includes an upper skin (1), a honeycomb core (2), and a lower skin (3). The upper skin (1) and the lower skin (3) are both composed of multilayer phenolic resin glass fiber fabric prepreg. The number of prepreg layers in the upper skin (1) is greater than the number of prepreg layers in the lower skin (3). The honeycomb core (2) is an aramid honeycomb core. The upper skin (1), the lower skin (3), and the honeycomb core (2) are all bonded together with an adhesive film layer (4).

2. The glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo hold floor according to claim 1, characterized in that: The upper skin (1) has 5 layers of prepreg, and the lower skin (3) has 3 layers of prepreg.

3. The glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo hold floor according to claim 1, characterized in that: The five layers of prepreg in the upper skin (1) are all weft-side down facing the honeycomb core (2), and the three layers of prepreg in the lower skin (3) are all weft-side up facing the honeycomb core (2).

4. The glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo hold floor according to claim 1, characterized in that: The laying angle of the five layers of prepreg in the upper skin (1) is 0° / 90°, and the laying angle of the three layers of prepreg in the lower skin (3) is 0° / 90°.

5. The glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo hold floor according to claim 1, characterized in that: The prepreg is a fabric with a warp angle of 0° and a weft angle of 90°.

6. The glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo hold floor according to claim 1, characterized in that: The honeycomb core (2) is a high-density aramid honeycomb core with a density of 144±6 kg / m³. 3 .

7. The glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo hold floor according to claim 1, characterized in that: The adhesive film layer (4) is a modified epoxy resin adhesive.

8. The glass fiber reinforced panel aramid honeycomb core sandwich structure aircraft cargo hold floor according to claim 1, characterized in that: The upper skin (1), adhesive film layer (4), honeycomb core (2), adhesive film layer (4), and lower skin (3) are heat-pressed and cured to obtain a sandwich structure.

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