Pressurizing calandria sandwich skin structure and aircraft

Abstract

The utility model provides a pressurizing calandria sandwich skin structure and an aircraft, the pressurizing calandria sandwich skin structure comprises an upper panel, a lower panel and at least one layer of pressurizing calandria limited between the upper panel and the lower panel, each layer of pressurizing calandria is formed by tightly arranging a plurality of pipe fittings with circular sections, and the pipe fittings are filled with gas with set pressure. According to the pressurizing calandria sandwich skin structure, loads are transmitted through gas, the whole structure is evenly stressed, the interior of the sandwich skin is basically hollow, the light weight requirement can be fully met, the pressurizing calandria sandwich skin is adopted to replace a traditional solid structure, the structural weight is reduced, and meanwhile the structural rigidity requirement is met.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft structures and relates to an aircraft skin structure, in particular to a pressurized tube sandwich skin structure and an aircraft. Background Art

[0002] Under high-speed flight conditions, in order to meet the requirements of aircraft lightweighting, load bearing and surface aerodynamic shape, and to ensure the normal operation of the fuselage structure and cabin equipment, an ultra-light, load-bearing integrated skin is required to maintain the structural shape.

[0003] As aircraft speeds increase and flight times lengthen, higher requirements are placed on the lightweight structure and load-bearing capacity of the outer skin, which currently cannot be met by commonly used outer skin structures. This is because long-term, high-speed flight leads to more significant aerodynamic heating. If existing skin solutions are used, thicker insulation layers are required, which in turn increases the weight of the skin structure. In addition, reusable aircraft not only place higher demands on lightweight structure and fuel storage space, but also on reusability, which currently cannot be met by commonly used skin structures. Summary of the Invention

[0004] The purpose of the utility model is to provide a pressurized tube sandwich skin structure and an aircraft, so as to solve the current problems of lightweight and load-bearing of the skin of high-speed aircraft.

[0005] The technical solutions adopted by the utility model to achieve the above-mentioned purpose are as follows:

[0006] A pressurized calandria sandwich skin structure comprises an upper panel, a lower panel, and at least one layer of pressurized calandria limited between the upper and lower panels. Each layer of the pressurized calandria is composed of a number of closely arranged pipes with circular cross-sections, and the pipes are filled with a set pressure gas.

[0007] Furthermore, the sandwich skin structure is made of non-metallic composite materials and adopts an integrated braiding molding process;

[0008] Alternatively, the sandwich skin structure is made of metal material and is formed using a 3D printing process;

[0009] Alternatively, the sandwich skin structure is made of non-metallic material, and the pressurized pipes are bonded and fixed to the upper and lower panels;

[0010] Alternatively, the sandwich skin structure is made of metal material, and the pressurized pipe is welded and fixed to the upper and lower panels;

[0011] Alternatively, the sandwich skin structure is made of a polymer film material or a metal thin material with a thickness of less than 0.1 mm, and the pressurized discharge pipe is welded and fixed to the upper and lower panels.

[0012] Furthermore, each pipe of the pressurized discharge pipe is independent and not interconnected, and each pipe is filled with gas at the same or different pressures.

[0013] Furthermore, the pipes of the pressurized drainage pipes are filled with condensed liquid or gas.

[0014] Furthermore, the pressure charging pipes are arranged at an inclined angle.

[0015] Furthermore, the pressurized discharge pipes include two layers, and the upper and lower axes of the two layers of pressurized discharge pipes are aligned; or the upper and lower axes of the two layers of pressurized discharge pipes are staggered, and the axis of each pipe in the upper layer is located on the tangent plane of the two pipes in the lower layer; or the axes of the two adjacent layers of pressurized discharge pipes are perpendicular.

[0016] Furthermore, the pressure-charging pipes are provided in at least three layers, the axes of the pressure-charging pipes in each layer are parallel, and the diameters of the pipes in each layer are different.

[0017] Furthermore, the sandwich skin structure is prepared into modules with different structural parameters, including single-layer pressurized tube sandwich skin module, double-layer pressurized tube sandwich skin module, and multi-layer pressurized tube sandwich skin module, which are spliced ​​to form a large-area skin.

[0018] An aircraft, the aircraft skin of which adopts the above-mentioned pressurized tube sandwich skin structure.

[0019] The beneficial effects of this utility model compared with the prior art are:

[0020] This new design provides a pressurized calandria core sandwich skin structure that utilizes gas to transfer loads, ensuring uniform stress distribution throughout the structure. Furthermore, compared to existing aircraft skins, this new sandwich skin is essentially hollow, fully achieving lightweighting requirements. Replacing traditional solid structures with a pressurized calandria core sandwich skin not only reduces structural weight but also meets structural rigidity requirements. Furthermore, the different pressurized calandria core layout designs facilitate the finalization and maintenance of the exterior shape.

[0021] The interior of the pressurized discharge pipe of the utility model can be filled with condensed liquid or gas. The specific heat capacity of liquid is higher than that of solid, ensuring that the heating speed of the skin structure is lower than that of the solid skin structure in a high temperature environment, and the heat insulation effect is better than that of the solid skin structure.

[0022] The pressurized discharge pipe of the utility model can increase the rigidity of the skin, make the structure more resistant to deformation, be able to withstand greater loads, and significantly increase the service life of the skin, meeting the demand for reusability.

[0023] Different arrangements of the pressurized pipes of the present invention can provide stiffness additions in different directions for the overall structure. Selecting targeted arrangements of the pressurized pipes according to different external load environments can maintain the structural shape in a targeted manner.

[0024] The utility model can use general materials (metal / non-metal), flexible materials and rigid materials, and has a simple connection structure. In addition, the sandwich skin structure can be integrated by 3D printing or integrated weaving.

[0025] Flexible materials can deform according to changes in inflation pressure in the tubes, changing the wing shape to adapt to changes in external load conditions (such as takeoff, level flight, and descent). Rigid materials enable the structure to maintain its shape under load.

[0026] The pressurized pipes and upper and lower panels of the utility model can increase the rigidity of the skin structure, so that the structure can withstand greater loads; each pipe is independent of each other and not interconnected, thereby improving the overall damage resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The accompanying drawings are included to provide a further understanding of the embodiments of the present invention, constitute a part of the specification, illustrate the embodiments of the present invention, and together with the written description, explain the principles of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without inventive work.

[0028] Figure 1 This is an overall schematic diagram of a pressurized tube sandwich skin structure provided by a specific embodiment of the present utility model;

[0029] Figure 2 Schematic diagram of sandwich tube arrangement at different angles (90° and 45°) provided by a specific embodiment of the present invention;

[0030] Figure 3 A schematic diagram of a double-layer straight tube sandwich structure provided by a specific embodiment of the present utility model;

[0031] Figure 4 A schematic diagram of a double-layer staggered tube sandwich structure provided by a specific embodiment of the present utility model;

[0032] Figure 5 A schematic diagram of a double-layer orthogonal tube sandwich structure provided by a specific embodiment of the utility model;

[0033] Figure 6 This is a schematic diagram of a multi-layer tube sandwich structure provided by a specific embodiment of the present utility model. DETAILED DESCRIPTION

[0034] The specific embodiments of the present invention are described in detail below. In the following description, for the purpose of explanation and not limitation, specific details are set forth to help fully understand the present invention. However, it is obvious to those skilled in the art that the present invention can also be practiced in other embodiments that depart from these specific details.

[0035] It should be noted here that, in order to avoid obscuring the present invention due to unnecessary details, the accompanying drawings only show the equipment structure and / or processing steps closely related to the solution of the present invention, while omitting other details that are not closely related to the present invention.

[0036] The utility model provides a pressurized tube sandwich skin structure, comprising upper and lower panels and a middle sandwich tube. Figure 1 As shown, the sandwich tube arrangement is composed of several slender circular cross-section tubes arranged closely, and several circular tubes are connected side by side to form a plane, and the upper and lower surfaces of the plane are respectively fitted with upper and lower panels.

[0037] Based on the actual load conditions of the skin structure under real-world conditions, the force response and deformation of the skin structure were simulated and calculated, and the preliminary structural design was carried out based on the calculation results. Regarding the structural parameters, the tube radius was approximately 1mm, and subsequent modifications were made based on the simulation results.

[0038] The pressurized tube sandwich skin structure of the utility model can be formed by different methods according to the needs:

[0039] (1) The upper and lower panels and the sandwich tubes are made of non-metallic composite materials and adopt integrated weaving molding technology;

[0040] (2) The upper and lower panels and the sandwich tubes are made of metal materials and 3D printing technology;

[0041] (3) The upper and lower panels and the sandwich tubes are made of non-metallic materials, and the sandwich tubes are bonded and fixed to the upper and lower panels;

[0042] (4) The upper and lower panels and the sandwich tubes are made of metal materials, and the sandwich tubes are welded and fixed to the upper and lower panels;

[0043] (5) The upper and lower panels and the sandwich tubes are made of flexible materials (such as polymer film materials, metal thin materials below 0.1 mm, etc.), and the sandwich tubes are welded and fixed to the upper and lower panels; the flexible materials can deform according to the changes in the inflation pressure of the tubes, and change the wing shape to adapt to changes in the external load environment under different conditions (such as takeoff, level flight and descent stages of the aircraft).

[0044] The utility model adopts a sandwich tube with a circular cross-section, which has a simpler manufacturing process and lower cost than a square cross-section. The circular cross-section tube can evenly distribute the force when under pressure and has a higher pressure-bearing capacity. It is easy to bend, twist and overlap.

[0045] Furthermore, the sandwich tube structure of this utility model is pressurized. Each tube in this pressurized tube structure is independent and disconnected. Each tube can be filled with gas at different pressures, with the inflation pressure set based on load and other simulation results. This approach improves the overall damage resistance. If one tube or part of the tube is damaged or leaks, the other tubes are unaffected and maintain their load-bearing capacity.

[0046] The pressurized structure consists of a circular cross-section sandwich tube filled with gas and upper and lower panels. The sandwich tube can be arranged in a single layer or multiple layers. The inflated gas is a light gas, such as helium, which reduces the mass of the skin structure.

[0047] The interior of the sandwich tube can be filled with condensed liquid or gas. The specific heat capacity of liquid is higher than that of solid, which ensures that the heating rate of the skin structure is lower than that of the solid skin structure in a high temperature environment, and the thermal insulation effect is better than that of the solid skin structure.

[0048] Furthermore, the sandwich tube structure of the present invention can be designed as a multi-angle sandwich structure, such as Figure 2 shown.

[0049] The sandwich tube structure is designed with a multi-angle arrangement. This design can make the overall skin structure exhibit anisotropic properties. The arrangement angle of the sandwich tubes is adjusted according to different loads, which increases the stiffness in a specific direction and reduces structural deformation.

[0050] Furthermore, the sandwich tube structure of the present invention can be designed as a double-layer straight tube sandwich structure, such as Figure 3 shown.

[0051] The upper and lower axes of the two layers of straight tubes are aligned and the tubes are connected by bonding. This structure has a simple manufacturing process and can significantly improve the in-plane shear strength of the sandwich structure.

[0052] Furthermore, the sandwich tube structure of the present invention can be designed as a double-layer cross-tube sandwich structure, such as Figure 4 shown.

[0053] The upper linear axes of the tubes in the double-layer cross-tube sandwich structure are staggered, and the axis of each tube in the upper layer is displaced on the tangent plane of the two tubes in the lower layer. This structure can reduce the gap, make full use of materials, and reduce the thickness of the overall structure.

[0054] Furthermore, the sandwich tube structure of the present invention can be designed as a double-layer orthogonal tube sandwich structure, such as Figure 5 shown.

[0055] The two layers of sandwich tubes in the double-layer orthogonal structure are axially perpendicular, relatively and parallel to each other. The orthogonal structure provides rigidity for the structure in two orthogonal directions and can maintain the shape of the skin when subjected to lateral loads.

[0056] Furthermore, the sandwich tube structure of the present invention can be designed as a multi-level tube sandwich structure, such as Figure 6 shown.

[0057] The number of layers and tube diameters can be determined based on load requirements. The tube diameters of each layer in a multi-layer structure can be different, allowing for flexible structural design adjustments based on varying operating conditions, offering strong adaptability.

[0058] It should be noted that the charging and discharging pipes of the same layer can be provided with parallel charging ports at the same end to facilitate the simultaneous charging of gas of set pressure; for multi-layer charging and discharging pipes, the connection method of the charging ports can be adjusted according to the direction of the pipes and the pressure requirements to simplify the charging operation.

[0059] Furthermore, the skin structure of the present invention adopts a modular design, including a single-layer pressurized tube sandwich skin module, a double-layer pressurized tube sandwich skin module, and a multi-layer pressurized tube sandwich skin module. The structural parameters of each skin module are different. The appropriate skin module is determined according to the surface load distribution of the aircraft.

[0060] This new design provides a pressurized tube sandwich skin structure that utilizes gas to transfer loads, ensuring uniform stress distribution throughout the structure. Furthermore, compared to existing aircraft skins, this new sandwich skin is essentially hollow, fully achieving lightweight requirements. Replacing traditional solid structures with a pressurized tube sandwich skin not only reduces structural weight but also meets structural rigidity requirements. Furthermore, the different sandwich core layouts facilitate the finalization and maintenance of the exterior shape.

[0061] The interior of the pressure charging tube of the utility model can be filled with condensed liquid or gas. The specific heat capacity of liquid is higher than that of solid, which ensures that the heating speed of the skin structure is lower than that of the solid skin structure in a high temperature environment, and the heat insulation effect is better than that of the solid skin structure.

[0062] The pressure-charging tube of the utility model can increase the rigidity of the skin, make the structure more resistant to deformation, be able to withstand greater loads, and significantly increase the service life of the skin, meeting the demand for reusability.

[0063] Different sandwich tube arrangements of the present invention can provide stiffness additions in different directions for the overall structure. Selecting targeted sandwich tube arrangements according to different external load environments can maintain the structural shape in a targeted manner.

[0064] The utility model can select general materials (metal / non-metal), flexible materials and rigid materials, and has a simple connection structure.

[0065] Flexible materials can deform according to changes in inflation pressure in the tubes, changing the wing shape to adapt to changes in external load conditions (such as takeoff, level flight, and descent). Rigid materials enable the structure to maintain its shape under load.

[0066] The pressurized pipes and upper and lower panels of the utility model can increase the rigidity of the skin structure, so that the structure can withstand greater loads; each pipe is independent of each other and not interconnected, thereby improving the overall damage resistance.

[0067] Features described and / or illustrated above for one embodiment may be used in the same or similar manner in one or more other embodiments, and / or combined with or used in place of features in other embodiments.

[0068] It should be emphasized that the term "include / comprises" when used herein refers to the presence of features, integers, steps or components, but does not exclude the presence or addition of one or more other features, integers, steps, components or combinations thereof.

[0069] The many features and advantages of these embodiments are apparent from this detailed description, and thus, the appended claims are intended to cover all such features and advantages of these embodiments that fall within the true spirit and scope thereof. Furthermore, since numerous modifications and changes will readily occur to those skilled in the art, it is not intended that the embodiments of the present invention be limited to the exact construction and operation illustrated and described, but rather that all suitable modifications and equivalents fall within the scope thereof.

[0070] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that the present invention is susceptible to various modifications and variations. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

[0071] The parts of the present invention that are not described in detail are well known to those skilled in the art.

Claims

1. A pressurized tube sandwich skin structure, characterized in that: It includes an upper panel, a lower panel and at least one layer of pressurized discharge pipes limited between the upper and lower panels. Each layer of pressurized discharge pipes is composed of several closely arranged pipes with circular cross-sections, and the pipes are filled with set pressure gas.

2. The sandwich skin structure according to claim 1, characterized in that: The sandwich skin structure is made of non-metallic composite materials and adopts an integrated braiding molding process; Alternatively, the sandwich skin structure is made of metal material and is formed using a 3D printing process; Alternatively, the sandwich skin structure is made of non-metallic material, and the pressurized pipes are bonded and fixed to the upper and lower panels; Alternatively, the sandwich skin structure is made of metal material, and the pressurized pipe is welded and fixed to the upper and lower panels; Alternatively, the sandwich skin structure is made of a polymer film material or a metal thin material with a thickness of less than 0.1 mm, and the pressurized discharge pipe is welded and fixed to the upper and lower panels.

3. The sandwich skin structure according to claim 1, characterized in that: Each pipe fitting of the pressurized discharge pipe is independent and not interconnected, and each pipe fitting is filled with gas of the same or different pressures.

4. The sandwich skin structure according to claim 1, characterized in that: The pipe fittings of the pressurized discharge pipe are filled with condensed liquid or gas.

5. The sandwich skin structure according to claim 1, characterized in that: The pressure charging pipes are arranged at a set angle.

6. The sandwich skin structure according to claim 1, characterized in that: The pressurized drainage pipes include two layers, and the upper and lower axes of the two layers are aligned; or the upper and lower axes of the two layers are staggered, and the axis of each pipe in the upper layer is located on the tangent plane of the two pipes in the lower layer; or the axes of the two adjacent layers of pressurized drainage pipes are perpendicular.

7. The sandwich skin structure according to claim 1, characterized in that: The pressurized pipes are at least three layers in length, the axes of the pressurized pipes in each layer are parallel, and the pipe diameters of the pressurized pipes in each layer are different.

8. The sandwich skin structure according to any one of claims 1 to 7, characterized in that: The sandwich skin structure is prepared into modules with different structural parameters, including single-layer pressurized tube sandwich skin module, double-layer pressurized tube sandwich skin module, and multi-layer pressurized tube sandwich skin module, which are spliced ​​to form a large-area skin.

9. An aircraft, characterized in that: The aircraft skin adopts the sandwich skin structure according to any one of claims 1 to 5.

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