CN210454020U - Aircraft floor of fiber/metal laminate composite material - Google Patents
Aircraft floor of fiber/metal laminate composite material Download PDFInfo
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- CN210454020U CN210454020U CN201920833845.7U CN201920833845U CN210454020U CN 210454020 U CN210454020 U CN 210454020U CN 201920833845 U CN201920833845 U CN 201920833845U CN 210454020 U CN210454020 U CN 210454020U
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Abstract
The utility model provides a fibre/metal laminate combined material's aircraft floor, it includes the metal decking layer, go up the antiskid nail nest that the punching press was provided with the equipartition on the metal decking layer, the inside packing in antiskid nail nest has resin fiber mixture layer, the lower terminal surface on resin fiber mixture layer and last metal decking layer is pasted and is had the fibre fabric layer, the lower terminal surface on fibre fabric layer is pasted and is had lower metal decking layer. The airplane floor manufactured by the material not only has the advantages of high strength ratio, rigidity ratio, designability and the like of the resin-based composite material, but also keeps good impact resistance and bending property of the metal material, and improves the anti-skid property of the airplane floor.
Description
Technical Field
The utility model relates to an aircraft floor technical field, concretely relates to aircraft floor with fibre/metal laminate combined material, more specifically relate to and replace the manufacturing approach on former aircraft floor with fibre/metal composite laminated board.
Background
Currently only two types of laminate composites, metal and fiber resin based, are used in aircraft flooring. As a traditional material, the metal material has the advantages of good impact resistance, isotropy, good bending property and the like, and has the defects of low specific strength, low specific rigidity, poor designability and the like, and as an airplane floor material, the metal material cannot meet the urgent requirements of airplanes on light high-strength materials. The fiber resin-based laminated board composite material as an advanced composite material has the advantages of high specific strength, specific rigidity, designability and the like, has the defects of poor impact resistance, anisotropy, poor bending property and the like, and cannot meet the requirement of a floor on impact resistance when being used as a floor material.
SUMMERY OF THE UTILITY MODEL
For solving above technical problem, the utility model provides a fibre/metal laminate combined material's aircraft floor utilizes the aircraft floor that this kind of material was made not only to have resin matrix combined material's high strength ratio, rigidity than and designability advantage such as good, still remains good shock resistance and bending property of metal material simultaneously, has improved aircraft floor's non-skid property.
In order to realize the technical characteristics, the purpose of the utility model is realized as follows: the aircraft floor made of the fiber/metal laminated plate composite material comprises an upper metal panel layer, wherein uniformly distributed anti-skid nail pits are punched on the upper metal panel layer, resin fiber mixture layers are filled in the anti-skid nail pits, fiber fabric layers are adhered to the lower end surfaces of the resin fiber mixture layers and the upper metal panel layer, and a lower metal panel layer is adhered to the lower end surface of each fiber fabric layer.
Pure resin is soaked in the fiber fabric layer.
The resin fiber mixture layer is formed by stirring and mixing epoxy resin and short fibers.
The fiber fabric layer is a glass fiber fabric layer or a carbon fiber fabric layer.
The fiber fabric layer adopts plain weave or twill weave.
And the upper metal panel layer and the fiber fabric layer as well as the fiber fabric layer and the lower metal panel layer are bonded and cured by adopting glue films.
The utility model discloses there is following beneficial effect:
the aircraft floor made of the fiber/metal laminated plate composite material is a composite material which is formed by layering the metal material and the fiber resin matrix composite material and then curing the layered composite material through an autoclave, integrates the advantages of the metal material and the fiber matrix composite material, and has high specific strength and specific stiffness; but also has better shock resistance; higher damage tolerance and good fatigue performance. Therefore, the composite material is incomparable with metal materials and fiber resin-based laminated plate composite materials in the aspects of safety reliability, weight reduction effect, designability of anti-skid performance and the like.
Drawings
The present invention will be further explained with reference to the drawings and examples.
Fig. 1 is a schematic cross-sectional view of an aircraft floor made of the fiber/metal laminate composite of the present invention.
Fig. 2 is a view of the apparatus for curing and forming the aircraft floor made of the fiber/metal laminate composite of the present invention.
Fig. 3 is a flow chart of a process for manufacturing an aircraft floor using the fiber/metal laminate composite of the present invention.
Fig. 4 is a cross-sectional view of an aircraft floor manufacturing process using the fiber/metal laminate composite of the present invention.
In the figure: the production process comprises the following steps of an upper metal panel layer 1, a resin fiber mixture layer 2, a fiber fabric layer 3, a lower metal panel layer 4, a glue absorbing material 5, a vacuum bag 6, a paving blank 7, an isolating film 8, an air-permeable felt 9, a pressure-sensitive adhesive tape 10, a mold 11, a plane mold 12 and a stop block 13.
Detailed Description
The following describes embodiments of the present invention with reference to the accompanying drawings.
Example 1:
referring to fig. 1, the aircraft floor made of the fiber/metal laminated plate composite material comprises an upper metal panel layer 1, wherein uniformly distributed anti-skid nail pits are punched on the upper metal panel layer 1, resin fiber mixture layers 2 are filled in the anti-skid nail pits, fiber fabric layers 3 are adhered to the lower end surfaces of the resin fiber mixture layers 2 and the upper metal panel layer 1, and a lower metal panel layer 4 is adhered to the lower end surface of the fiber fabric layer 3. According to the aircraft floor adopting the structure, the composite material formed by layering the fiber layer and the metal layer composite material and curing the composite material through the autoclave is adopted, the advantages of the metal material and the fiber-based composite material are integrated, and the aircraft floor has high specific strength and specific rigidity; but also has better shock resistance; higher damage tolerance and good fatigue performance. And then reach all required performance characteristics of aircraft floor, and then great improvement aircraft floor's security, reach and subtract heavy, anti-skidding effect.
Further, the fiber fabric layer 3 is impregnated with pure resin. The resin additive ensures the bonding capability between the metal layer and the limiting layer, and further ensures the reliability of interlayer bonding.
Further, the resin fiber mixture layer 2 is formed by stirring and mixing epoxy resin and short fibers. The resin fiber mixture layer 2 can fill the anti-skid nail pit on one hand, so that the impact resistance of the anti-skid nail pit is improved, on the other hand, the bonding surface area between the upper metal panel layer 1 and the fiber fabric layer 3 is increased, and the interlayer bonding strength is ensured.
Further, the fiber fabric layer 3 is a glass fiber fabric layer or a carbon fiber fabric layer. The fiber fabric layer 3 has high specific strength, specific rigidity and designability, and further well makes up for the defects of the adoption of a single metal layer.
Further, the fiber fabric layer 3 adopts plain weave fabric or twill weave fabric.
Further, the upper metal panel layer 1 and the fiber fabric layer 3 as well as the fiber fabric layer 3 and the lower metal panel layer 4 are bonded and cured by adopting glue films.
Further, the thickness of the upper metal panel layer 1 is preferably 0.5 mm.
Further, the thickness of the lower metal panel layer 4 is preferably 0.3 mm.
Further, the preferred fiber fabric layer 3 is a ± 45 ° warp knit.
Example 2:
referring to fig. 2-4, a method of manufacturing an aircraft floor of a fiber/metal laminate composite, comprising the steps of:
step one, manufacturing a stamping die: the die comprises a stamping die and a stamping needle; the stamping die is made of 45# steel, and after rough milling, stress relief annealing treatment is carried out; the punching needle is made of Cr12 die steel, and is subjected to quenching and tempering treatment after turning, wherein the hardness is HRC 48-52; the mould is mainly used for punching the upper metal panel layer 1 to form the anti-skid nail nest, so that the upper surface of the floor plays a good protection role;
step two, manufacturing the antiskid nail nest: selecting a TA2 titanium alloy plate as an upper metal panel layer 1, and adopting laser blanking according to the size of the floor; selecting a TA2 titanium alloy plate as a lower metal panel layer 4; placing the upper metal panel layer 1 on a press, and manufacturing an anti-skid nail nest by using the stamping die in the step one;
step three, surface treatment: carrying out sulfuric acid anodizing treatment on the upper metal panel layer 1 and the lower metal panel layer 4; the part must be transferred to a cleaning room within 2 hours after anodizing, and SY-D9 corrosion-inhibiting primer must be sprayed on the part adhesive surface within 8 hours, wherein the spraying primer amount is 200g/m2~250g/m2(ii) a The anodizing treatment is mainly used for increasing the surface adhesive property of the metal panel, so that the metal panel is well adhered to the adhesive film, and the adhesion reliability is guaranteed.
Step four, preparing a gluing mold: cleaning oil stain, dust and sundries on the surfaces of a plane die 12 and an anti-skid nail die 11, wiping the surfaces of the dies by using acetone, and uniformly coating a release agent; the reliability of subsequent gluing is ensured through the cleaning procedure.
Step five, paving: smoothly paving a SY-24C adhesive film on the upper metal panel layer 1 and the lower metal panel layer 4 in a clean room; the upper metal panel layer 1 is paved on a flat plate workbench by the gluing surface of the plate, and the anti-skid nail nest faces downwards; adding epoxy resin into the chopped carbon fiber, uniformly stirring, and filling into the antiskid nail nest; the fiber fabric layer 3 is flatly pasted on the gluing surface of the upper metal panel layer 1, and the gluing surface of the lower metal panel layer 4 is pasted on the fiber fabric layer 3;
step six, curing and forming: after paving, sequentially placing a plane mould 12, an isolating membrane 8, a stop block 13, a paving blank 7, the isolating membrane 8, an adhesive absorption material 5, a mould 11, an air felt 9, a vacuum bag 6 and a pressure sensitive adhesive tape 10; thermocouple paste in part length direction both ends edges, do the air tightness after the encapsulation and detect, close vacuum in vacuum bag 6 vacuum degree less than-0.092 Mpa, and the vacuum degree does not drop more than 0.01Mpa within 5min, otherwise roll the pressure sensitive tape 10 tightly one by one; performing air tightness retest before curing, closing vacuum, and keeping the vacuum degree in the vacuum bag 6 less than-0.092 Mpa and the vacuum degree not more than 0.01Mpa within 5min, otherwise rolling the sealing tapes one by one and compacting; heating to 80 deg.C at a rate of 1.0 deg.C/min, maintaining the temperature for 30min, pressurizing to 0.5Mpa, heating to 130 + -5 deg.C at a rate of 1.0 deg.C/min, maintaining the temperature and pressure for 120min, cooling to 40 deg.C at a rate of 1.0 deg.C/min, releasing pressure, and opening the tank.
The glue absorbing material 5, the vacuum bag 6, the paving blank 7, the isolating membrane 8, the air-permeable felt 9, the pressure-sensitive adhesive tape 10, the mold 11, the plane mold 12 and the stop block 13 form a vacuum pumping structure together, so that complete gluing, curing and molding among the upper metal panel layer 1, the resin fiber mixture layer 2, the fiber fabric layer 3 and the lower metal panel layer 4 are ensured. The glue joint molding is realized by mainly adopting the principle of vacuum pumping and negative pressure.
Claims (6)
1. An aircraft floor of a fibre/metal laminate composite characterised in that: the anti-skid nail nest structure comprises an upper metal panel layer (1), wherein an anti-skid nail nest uniformly distributed is arranged on the upper metal panel layer (1) in a stamping mode, a resin fiber mixture layer (2) is filled in the anti-skid nail nest, a fiber fabric layer (3) is pasted on the lower end faces of the resin fiber mixture layer (2) and the upper metal panel layer (1), and a lower metal panel layer (4) is pasted on the lower end face of the fiber fabric layer (3).
2. An aircraft floor of a fiber/metal laminate composite according to claim 1 wherein: pure resin is soaked in the fiber fabric layer (3).
3. An aircraft floor of a fiber/metal laminate composite according to claim 1 wherein: the resin fiber mixture layer (2) is formed by stirring and mixing epoxy resin and short fibers.
4. An aircraft floor of a fiber/metal laminate composite according to claim 1 wherein: the fiber fabric layer (3) adopts a glass fiber fabric layer or a carbon fiber fabric layer.
5. An aircraft floor of a fibre/metal laminate composite according to claim 1 or 2 or 3, characterised in that: the fiber fabric layer (3) adopts plain weave or twill weave.
6. An aircraft floor of a fiber/metal laminate composite according to claim 1 wherein: and the upper metal panel layer (1) and the fiber fabric layer (3) as well as the fiber fabric layer (3) and the lower metal panel layer (4) are bonded and cured by adopting glue films.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920833845.7U CN210454020U (en) | 2019-06-04 | 2019-06-04 | Aircraft floor of fiber/metal laminate composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920833845.7U CN210454020U (en) | 2019-06-04 | 2019-06-04 | Aircraft floor of fiber/metal laminate composite material |
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| Publication Number | Publication Date |
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| CN210454020U true CN210454020U (en) | 2020-05-05 |
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| CN201920833845.7U Active CN210454020U (en) | 2019-06-04 | 2019-06-04 | Aircraft floor of fiber/metal laminate composite material |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110181905A (en) * | 2019-06-04 | 2019-08-30 | 中国人民解放军第五七一零工厂 | Fiber/metal laminate composite material airplane floor and manufacturing method |
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2019
- 2019-06-04 CN CN201920833845.7U patent/CN210454020U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110181905A (en) * | 2019-06-04 | 2019-08-30 | 中国人民解放军第五七一零工厂 | Fiber/metal laminate composite material airplane floor and manufacturing method |
| CN110181905B (en) * | 2019-06-04 | 2024-01-23 | 凌云(宜昌)航空装备工程有限公司 | Aircraft floor made of fiber/metal laminate composite material and manufacturing method |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200702 Address after: No.1 Lingyun Road, Yuyang office, Dangyang city, Yichang City, Hubei Province Patentee after: Lingyun (Yichang) aviation equipment Engineering Co., Ltd Address before: 444100 98 Yuen Nan Road, Yuyang office, Dangyang city, Yichang, Hubei Patentee before: NO.5710 FACTORY OF PLA |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200820 Address after: No.1 Lingyun Road, Yuyang office, Dangyang city, Yichang City, Hubei Province Co-patentee after: LINGYUN SCIENCE & TECHNOLOGY GROUP Co.,Ltd. Patentee after: Lingyun (Yichang) aviation equipment Engineering Co., Ltd Address before: No.1 Lingyun Road, Yuyang office, Dangyang city, Yichang City, Hubei Province Patentee before: Lingyun (Yichang) aviation equipment Engineering Co., Ltd |
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| TR01 | Transfer of patent right | ||
| CB03 | Change of inventor or designer information |
Inventor after: Wang Yuya Inventor after: Wan Shaoqin Inventor after: Lu Guangtao Inventor after: Lai Jianzheng Inventor after: Li Qiangxuan Inventor after: Li Fangyu Inventor before: Wan Shaoqin Inventor before: Lu Guangtao Inventor before: Lai Jianzheng Inventor before: Li Qiangxuan Inventor before: Li Fangyu |
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| CB03 | Change of inventor or designer information |