CN220865650U - Aircraft composite floor structure and aircraft cabin - Google Patents
Aircraft composite floor structure and aircraft cabin Download PDFInfo
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- CN220865650U CN220865650U CN202322858440.8U CN202322858440U CN220865650U CN 220865650 U CN220865650 U CN 220865650U CN 202322858440 U CN202322858440 U CN 202322858440U CN 220865650 U CN220865650 U CN 220865650U
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- 239000002131 composite material Substances 0.000 title claims abstract description 58
- 239000011162 core material Substances 0.000 claims abstract description 62
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 7
- 229920005989 resin Polymers 0.000 claims description 7
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- 229910000838 Al alloy Inorganic materials 0.000 claims description 6
- 239000006260 foam Substances 0.000 claims description 6
- 239000010425 asbestos Substances 0.000 claims description 4
- 239000000835 fiber Substances 0.000 claims description 4
- 229910052895 riebeckite Inorganic materials 0.000 claims description 4
- 238000009408 flooring Methods 0.000 claims description 3
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- 238000009413 insulation Methods 0.000 description 2
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- 229920005830 Polyurethane Foam Polymers 0.000 description 1
- 230000001680 brushing effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- 238000010107 reaction injection moulding Methods 0.000 description 1
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- Laminated Bodies (AREA)
Abstract
The utility model relates to the technical field of aircraft floors, and provides an aircraft composite floor structure and an aircraft cabin, wherein the aircraft composite floor structure comprises a first panel; a core material arranged at the bottom of the first panel; the second panel is arranged on one side of the core material away from the first panel; the embedded bushing penetrates through the core material, one end of the embedded bushing is connected with the first panel, the other end of the embedded bushing is connected with the second panel, and the embedded bushing is used for fixing the floor structure. According to the aircraft composite material floor structure and the aircraft cabin, the core material is arranged at the bottom of the first panel, the second panel is arranged at one side of the core material away from the first panel, and the core material is arranged to enable the overall strength and rigidity of the floor structure to be higher, so that consumed fuel is reduced during flight; moreover, the arrangement of the embedded bushing can ensure that the floor structure can be fixed conveniently.
Description
Technical Field
The utility model relates to the technical field of aircraft floor structures, in particular to an aircraft composite floor structure and an aircraft cabin.
Background
The aircraft floor is an important component of the aircraft, and the floor per square meter in the cargo hold of the aircraft can only bear a certain weight, and if the bearing capacity is exceeded, the floor and the aircraft structure can be damaged. Therefore, the load must not exceed the floor bearing limit.
In the prior art, the aircraft floor is usually formed by connecting an aluminum alloy plate and an extruded profile, or is an integrally machined aluminum alloy floor structure. However, the aluminum alloy floor structure has a heavy weight, and consumes a large amount of fuel during flight.
Disclosure of utility model
The utility model provides an aircraft composite material floor structure and an aircraft cabin, which are used for solving the defect of heavier structural weight of the aircraft floor structure in the prior art, and realizing better strength and rigidity and light weight.
The utility model provides an aircraft composite floor structure, comprising:
A first panel;
A core material arranged at the bottom of the first panel;
The second panel is arranged on one side of the core material away from the first panel;
The embedded bushing penetrates through the core material, one end of the embedded bushing is connected with the first panel, the other end of the embedded bushing is connected with the second panel, and the embedded bushing is used for fixing the floor structure.
According to the aircraft composite floor structure provided by the utility model, the core material is a foam core material or a honeycomb core material.
According to the aircraft composite floor structure provided by the utility model, the first panel and the second panel are both composite panels.
According to the aircraft composite floor structure provided by the utility model, the composite panel is a nonmetallic composite panel.
According to the aircraft composite floor structure provided by the utility model, the nonmetal composite panel is one of glass fiber, carbon fiber or asbestos fiber.
According to the aircraft composite floor structure provided by the utility model, the embedded bush and the core material, the embedded bush and the second panel and the embedded bush and the first panel are bonded through the adhesive film and are compacted and fixed under a vacuum condition.
According to the aircraft composite floor structure provided by the utility model, the outer periphery of the core material is provided with the resin layer.
According to the aircraft composite floor structure provided by the utility model, one end of the embedded bushing is provided with the countersink, and the countersink is used for being matched with the fastener so that the top surface of the fastener is level with the first panel.
According to the aircraft composite floor structure provided by the utility model, the embedded bushing is an aluminum alloy bushing.
The utility model also provides an aircraft cabin comprising: an aircraft composite floor structure according to any preceding claim.
According to the aircraft composite material floor structure, the core material is arranged at the bottom of the first panel, the second panel is arranged at one side of the core material away from the first panel, and the core material is arranged to enable the overall strength and rigidity of the floor structure to be higher, so that consumed fuel is reduced during flight; moreover, the arrangement of the embedded bushing can ensure that the floor structure can be fixed conveniently.
The core material adopts a foam core material or a honeycomb material core material, and the foam material is a polymer material formed by dispersing a large number of gas micropores in solid plastic, and has the characteristics of light weight, heat insulation, sound absorption, shock absorption and the like. The honeycomb material is a composite material, and is a sandwich structure, its sandwich layer is formed from a series of hexagonal, quadrilateral or gas-shaped honeycomb-like cells, and on the upper and lower surfaces of the sandwich layer the thin skin is adhered or soldered, so that the honeycomb material has high rigidity and strength, and can make the whole floor structure have lighter weight and better strength and rigidity.
The first panel and the second panel are both composite material panels, and specifically, the composite material panels are one of glass fibers, carbon fibers or asbestos fibers, and have higher strength and fracture toughness, so that the structural strength and rigidity of the whole floor are better.
The present utility model also provides an aircraft cabin having various advantages as described above due to the inclusion of an aircraft composite floor structure as described above.
Drawings
In order to more clearly illustrate the utility model or the technical solutions of the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the utility model, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the exterior construction of an aircraft composite flooring structure provided by the present utility model;
FIG. 2 is an enlarged schematic view at A in FIG. 1;
FIG. 3 is a partial cross-sectional view of an aircraft composite flooring structure provided by the present utility model;
reference numerals:
1. a first panel; 2. a core material; 3. a second panel; 4. embedding a bushing; 5. a resin layer; 6. and (5) sinking the holes.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present utility model, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
In the description of the embodiments of the present utility model, it should be noted that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the embodiments of the present utility model and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the embodiments of the present utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The aircraft composite floor structure of the utility model is described below in connection with fig. 1 to 3.
As shown in fig. 1 to 3, a first aspect of the present utility model is to provide an aircraft composite floor structure, which includes a first panel 1, a core 2, a second panel 3 and a pre-embedded liner 4, wherein the first panel 1 and the second panel 3 are oppositely disposed at two sides of the core 2, that is, the first panel 1 is generally horizontally disposed, the core 2 is disposed at the bottom of the first panel 1, and the second panel 3 is disposed at the bottom of the core 2; the embedded bush 4 penetrates through the core material 2 along the thickness direction of the core material 2, one end of the embedded bush 4 is connected with the first panel 1, the other end of the embedded bush 4 is connected with the second panel 3, and the embedded bush 4 is used for fixing the floor structure.
According to the aircraft composite material floor structure provided by the utility model, the core material 2 is arranged at the bottom of the first panel 1, the second panel 3 is arranged at one side of the core material 2 far away from the first panel 1, and the core material 2 is arranged, so that the overall strength and rigidity of the floor structure are higher, and the consumed fuel is reduced during flight; moreover, the arrangement of the embedded bushing 4 can ensure that the floor structure can be fixed conveniently.
In general, the first panel 1 may be understood as an upper panel and the second panel 3 may be understood as a lower panel.
Specifically, when the embedded bushing 4 is installed, the core material 2 can be firstly hollowed, the embedded bushing 4 and the first panel 1, the embedded bushing 4 and the second panel 3, and the embedded bushing 4 and the core material 2 can be preliminarily connected and fixed through an adhesive film, in order to ensure the positioning accuracy of the embedded bushing 4, laser positioning can be used during paving, after the embedded bushing 4 is fixed, carbon fiber or glass fiber prepreg is paved on the upper part of the embedded bushing 4, after the paving is finished, the floor is solidified, the carbon fiber or glass fiber prepreg is solidified to form the first panel 1 or the second panel 3, and finally a countersink is formed, so that a countersink is formed, the flatness of the floor after the fastener is connected with the floor and other components is ensured, and finally, a resin layer 5 is brushed on the periphery of the core material 2 to avoid long-term exposure of the core material 2.
In one possible embodiment of the utility model, the core material 2 is a foam core material or a honeycomb core material. Specifically, the core material 2 is a foam core material or a honeycomb core material.
Wherein, the foam material is a polymer material formed by dispersing a large number of gas micropores in solid plastic, and has the characteristics of light weight, heat insulation, sound absorption, shock absorption and the like. The foamed plastic prepared by blending, filling, reinforcing and other modified plastics has better comprehensive performance and can meet the needs of various special purposes. For example, glass fiber reinforced polyurethane foam produced by reaction injection molding can be used as structural members for aircraft, automobiles, computers, and the like. Therefore, the core material 2 of the present utility model is a foam core material, which can reduce the weight and has high strength and rigidity.
The honeycomb material is a composite material, and is a sandwich structure, its sandwich layer is formed from a series of hexagonal, quadrilateral or gas-shaped honeycomb-like cells, and on the upper and lower surfaces of the sandwich layer the thin skin is adhered or soldered, so that the honeycomb material has high rigidity and strength, and can make the whole floor structure have lighter weight and better strength and rigidity. Therefore, the core material 2 of the present utility model is made of a honeycomb material, and can be reduced in weight and has high strength and rigidity.
In one possible embodiment of the utility model, both the first panel 1 and the second panel 3 are composite panels. The composite material is a material with new performance formed by two or more materials with different properties in a macroscopic manner through a physical or chemical method, and the materials complement each other in performance to generate a synergistic effect, so that the comprehensive performance of the composite material is superior to that of the original material to meet different requirements. In this embodiment, the composite material panels are adopted by the first panel 1 and the second panel 3, so that the comprehensive performance of the first panel 1 and the second panel 3 can be enhanced, and the strength and the rigidity of the floor structure can be improved.
In one possible embodiment of the utility model, the composite panel is a non-metallic composite panel, the non-metallic matrix being primarily synthetic resin, rubber, ceramic, graphite, carbon, or the like.
In a possible embodiment of the present utility model, the nonmetallic composite panel is one of glass fiber, carbon fiber or asbestos fiber, and the materials of the first panel 1 and the second panel 3 may be the same or different.
In one possible embodiment of the utility model, the pre-buried bush 4 and the core material 2, the pre-buried bush 4 and the second panel 3 and the pre-buried bush 4 and the first panel 1 are bonded by adhesive films and are compacted and fixed under vacuum condition.
As shown in fig. 3, in one possible embodiment of the present utility model, the outer periphery of the core material 2 is provided with a resin layer 5, i.e., the core material 2 is brushed with the resin layer 5 between the first panel 1 and the second panel 3 in the width direction thereof.
As shown in fig. 2 and 3, in a possible embodiment of the present utility model, a countersink 6 is formed at one end of the pre-buried bush 4, and the countersink 6 is adapted to be matched with a fastener, so that the top surface of the fastener is flush with the first panel 1, and the flatness of the floor structure after connection and installation is ensured.
According to the aircraft composite material floor provided by the utility model, the first panel 1, the second panel 3, the core material 2 and the embedded lining 4 are integrally formed through paving, and the core material 2 can be a foam material core material or a honeycomb material core material, so that the overall strength and rigidity of the floor are improved, the embedded lining 4 is convenient to connect as a traditional floor, countersinking is carried out in the area of the embedded lining 4 after paving is finished, and the flatness of the floor after connecting a fastener is ensured.
The processing process of the aircraft composite floor structure provided by the utility model comprises the steps of digging holes in the area of the core material 2 corresponding to the embedded lining 4, connecting the embedded lining 4 with the first panel 1, the core material 2 and the second panel 3 through an adhesive film, paving carbon fiber prepreg or glass fiber prepreg on the upper part of the embedded lining 4 after the embedded lining 4 is fixed, putting the embedded lining into a vacuum bag for vacuumizing and solidifying after the embedded lining is paved, forming the first panel 1 or the second panel 3 through the carbon fiber prepreg or the glass fiber prepreg, countersinking the holes to ensure the flatness of the floor after the fastening piece and the sliding rail are connected, and brushing a layer of resin on the position of the peripheral core material 2 to avoid long-term exposure of the core material 2.
Wherein, in order to ensure the accuracy of the positioning of the embedded bushing 4, the laser positioning can be adopted during paving.
In one possible embodiment of the utility model, the pre-buried liner 4 may be an aluminum alloy liner.
The aircraft cabin provided by the utility model is described below, and the aircraft cabin described below and the aircraft composite floor structure described above can be referred to correspondingly.
A second aspect of the utility model is an embodiment of an aircraft cabin comprising an aircraft composite floor structure as in any one of the embodiments above.
The aircraft cabin provided by the utility model has better strength and rigidity and lighter weight compared with the traditional aircraft cabin due to the aircraft composite material floor structure.
In describing embodiments of the present utility model, it should be noted that, unless explicitly stated and limited otherwise, the terms "coupled," "coupled," and "connected" should be construed broadly, and may be either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the embodiments of the present utility model will be understood by those of ordinary skill in the art according to specific circumstances.
In the description of the present specification, reference to the terms "one embodiment," "some embodiments," "manner," "particular modes," or "some modes," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or mode is included in at least one embodiment or mode of the embodiments of the present utility model. In this specification, the schematic representations of the above terms are not necessarily directed to the same embodiment or manner. Furthermore, the particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or ways. Furthermore, various embodiments or modes and features of various embodiments or modes described in this specification can be combined and combined by those skilled in the art without mutual conflict.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present utility model, and are not limiting; although the utility model has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present utility model.
Claims (10)
1. An aircraft composite floor structure, comprising:
A first panel (1);
A core material (2) provided at the bottom of the first panel (1);
A second panel (3) disposed on a side of the core material (2) away from the first panel (1);
The embedded lining (4) penetrates through the core material (2), one end of the embedded lining (4) is connected with the first panel (1), the other end of the embedded lining is connected with the second panel (3), and the embedded lining (4) is used for fixing the floor structure.
2. Aircraft composite floor structure according to claim 1, characterized in that the core (2) is a foam core or a honeycomb core.
3. Aircraft composite floor structure according to claim 1, characterized in that the first panel (1) and the second panel (3) are both composite panels.
4. An aircraft composite floor structure according to claim 3, wherein the composite panels are non-metallic composite panels.
5. The aircraft composite flooring structure of claim 4, wherein the non-metallic composite panel is one of fiberglass, carbon fiber, or asbestos fiber.
6. Aircraft composite floor structure according to claim 1, characterized in that between the pre-buried bush (4) and the core material (2), between the pre-buried bush (4) and the second panel (3), between the pre-buried bush (4) and the first panel (1) are glued by means of glue films and are compacted and fixed under vacuum conditions.
7. Aircraft composite floor structure according to claim 1, characterized in that the outer periphery of the core (2) is provided with a resin layer (5).
8. Aircraft composite floor structure according to claim 1, characterized in that one end of the pre-buried bushing (4) is provided with a countersink (6), the countersink (6) being adapted to a fastener so that the top surface of the fastener is flush with the first panel (1).
9. Aircraft composite floor structure according to claim 1, characterized in that the pre-buried bushings (4) are aluminium alloy bushings.
10. An aircraft cabin comprising an aircraft composite floor structure according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322858440.8U CN220865650U (en) | 2023-10-24 | 2023-10-24 | Aircraft composite floor structure and aircraft cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322858440.8U CN220865650U (en) | 2023-10-24 | 2023-10-24 | Aircraft composite floor structure and aircraft cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220865650U true CN220865650U (en) | 2024-04-30 |
Family
ID=90816010
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322858440.8U Active CN220865650U (en) | 2023-10-24 | 2023-10-24 | Aircraft composite floor structure and aircraft cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220865650U (en) |
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2023
- 2023-10-24 CN CN202322858440.8U patent/CN220865650U/en active Active
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