Composite paper structure and structural system of aircraft

Abstract

The embodiment of the utility model provides a composite paper structure and a structure system of an aircraft. The composite paper structure is applied to at least one structural system of an aircraft and comprises a main body structure and surface paper, the main body structure comprises at least two layers of honeycomb structures and at least one supporting plate; the honeycomb structures are stacked; the supporting plates are connected between the adjacent layers of honeycomb structures; the surface paper comprises at least one layer and is attached to at least one side outside the main body structure. The composite paper structure provided by the embodiment of the utility model meets the safety performance required by a structural system of an aircraft, and the honeycomb structure can effectively absorb collision energy and also can improve the safety and reliability of the structural system. In addition, due to the characteristics of the composite paper structure and the arrangement of the honeycomb structure, lightweight development of an aircraft structure system is facilitated.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of structural system of aircraft, in particular, the present application relates to a composite paper structure and a structural system of aircraft. BACKGROUND

[0002] The structural system (such as fuselage, wing and other structures) of the conventional aircraft is mostly made of metal or part of composite materials to achieve the safety and reliability required by the structural system.

[0003] However, metal or part of composite materials depends on limited mineral resources, has high cost and is difficult to recycle, resulting in poor resource sustainability development of the structural system of the existing aircraft. CONTENT OF THE INVENTION

[0004] The present application aims at the shortcomings of the prior art, and provides a composite paper structure and a structural system of aircraft to solve the technical problems that metal or part of composite materials depends on limited mineral resources, has high cost or poor resource sustainability development.

[0005] In a first aspect, the embodiments of the present application provide a composite paper structure applied to at least one structural system of an aircraft, comprising:

[0006] A main structure comprising: at least two layers of honeycomb structures and at least one support plate; each honeycomb structure is arranged in layers; and the support plate is connected between the adjacent layers of honeycomb structures;

[0007] A face paper, at least one layer, is attached to at least one side of the main structure.

[0008] In some possible embodiments, the honeycomb structure comprises: a plurality of hole units connected in sequence.

[0009] The composite paper structure is in a flat state, and the edge of the hole unit is in a closed graph on the face paper.

[0010] In the same honeycomb structure, the closed graph of each hole unit is the same.

[0011] In some possible embodiments, the same honeycomb structure comprises at least two kinds of hole units.

[0012] The closed graph of each hole unit is different.

[0013] In some possible embodiments, the composite paper structure further comprises at least one of the following:

[0014] The closed graph of the hole unit of the honeycomb structure comprises a regular geometric graph.

[0015] The closed graph comprises an irregular polygon.

[0016] At least one side of the closed figure is curved.

[0017] Opposite sides of the closed figure are hyperbolic.

[0018] In some possible embodiments, the closed figure comprises a regular hexagon.

[0019] The honeycomb structure further comprises a reinforcing wall arranged in the at least one cell in the first direction, the edge being connected to the inner wall of the cell.

[0020] The first direction is perpendicular to the flattened composite paper structure.

[0021] In some possible embodiments, the at least two layers of honeycomb structures comprise a first honeycomb panel and a second honeycomb panel; the closed figure of the cell of the first honeycomb panel is a hexagon; and the material of the first honeycomb panel comprises carbon fiber.

[0022] The closed figure of the cell of the second honeycomb panel is a rhombus; and the material of the second honeycomb panel comprises aramid fiber.

[0023] In some possible embodiments, the composite paper structure is in a flattened state, and the orthographic projection of the cell of the at least two layers of honeycomb structures on the face paper partially overlaps.

[0024] In some possible embodiments, the composite paper structure further comprises an adhesive layer.

[0025] The adhesive layer is arranged between the main structure and the face paper, and / or between the honeycomb structure and the support plate.

[0026] In some possible embodiments, the support plate comprises a base paper and a coating layer coated on the surface of the base paper.

[0027] In a second aspect, the embodiments of the present application further provide a structural system of an aircraft, comprising any composite paper structure provided in the first aspect.

[0028] The technical scheme provided by the embodiments of the present application has the beneficial technical effects including:

[0029] The composite paper structure is provided in the embodiments of the present application, which is used to manufacture a structural system of an aircraft. The composite paper structure comprises at least two layers of honeycomb structures and at least one support plate. The honeycomb structure has high hardness and strength, and good shear resistance, and can effectively disperse loads. The support plate is arranged between any two adjacent layers of the honeycomb structures, and plays a role of supporting and uniformly dispersing loads. The composite structure of the honeycomb structure and the support plate can improve the overall strength and stability of the composite paper structure, meet the safety performance required by the structural system of the aircraft, effectively absorb collision energy, and improve the safety and reliability of the structural system. In addition, the composite paper structure is beneficial to the lightweight development of the structural system of the aircraft due to the hollow feature and the arrangement of the honeycomb structure. In addition, the composite paper structure can be flexibly applied to manufacture a structural system with a complex shape, thereby having strong versatility, being capable of being used to manufacture various structural systems, and having a simple manufacturing process, easy recycling, and improved economic efficiency and resource sustainable development.

[0030] Additional aspects and advantages of the present application will be made apparent from the following description, which will be given in the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0031] The above and / or additional aspects and advantages of the present application will become apparent and be readily appreciated from the following description, taken in conjunction with the accompanying drawings, in which:

[0032] Figure 1 A perspective view of a structure of a composite paper structure provided in the embodiments of the present application is shown;

[0033] Figure 2 A side view of a structure of a composite paper structure provided in the embodiments of the present application is shown;

[0034] Figure 3 An exploded view of a structure of a composite paper structure provided in the embodiments of the present application is shown.

[0035] Reference Signs:

[0036] 100 - composite paper structure;

[0037] 10 - main body structure; 11 - honeycomb structure; 110 - hole unit; 12 - support plate;

[0038] 20 - surface paper;

[0039] 30 - adhesive layer. DETAILED DESCRIPTION

[0040] The embodiments of the present application will be described below in conjunction with the accompanying drawings. It should be understood that the embodiments described below in conjunction with the accompanying drawings are exemplary descriptions of the technical solutions of the embodiments of the present application, and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0041] Those skilled in the art can understand that the singular forms "a", "an" and "the" used herein include plural forms, unless specifically stated otherwise. It should be understood that the phrase "comprising" used in the specification of the present application means that the features, integers, steps, operations, elements and / or components exist, but does not exclude other features, information, data, elements, components and / or combinations thereof supported by the present technology. It should be understood that when we say that an element is "connected" or "coupled" to another element, the element can be directly connected or coupled to the other element, or can mean that the element and the other element are connected through an intermediate element. The term "and / or" used herein means that at least one of the items defined in the term, for example, "A and / or B" can be implemented as "A", or as "B", or as "A and B".

[0042] In order to make the purpose, technical solutions and advantages of the present application clearer, the embodiments of the present application will be described in further detail below in conjunction with the accompanying drawings.

[0043] The applicant found that the structure system of the traditional aircraft includes the fuselage, the wing, the engine or the fairing structure, and the main structure of these structures is mostly made of metal or part of composite materials to achieve the safety and reliability required by the structure system.

[0044] However, metal or part of composite materials rely on limited mineral resources, have high raw material costs, are difficult to process, and are difficult to maintain. Metal is heavy, has high transportation costs, and also increases the weight burden of the structure system, thereby reducing fuel efficiency and increasing operating costs. The acquisition and processing of part of the composite material are also more complex and difficult to recycle, thereby leading to poor resource sustainability development of the structure system of the existing aircraft.

[0045] The composite paper structure and the structure system of the aircraft provided by the present application aim to solve the above technical problems of the prior art.

[0046] The technical solutions of the present application and how the technical solutions of the present application solve the above technical problems will be described in detail below with specific embodiments. It should be pointed out that the following embodiments can be mutually referenced, borrowed or combined, and the same terms, similar features and similar implementation steps in different embodiments will not be described repeatedly.

[0047] The embodiment of the present application provides a composite paper structure 100, which is applied to at least one structural system of an aircraft, such as Figure 1 As shown in the figure, the composite paper structure 100 comprises a main body structure 10 and a surface paper 20.

[0048] The main body structure 10 comprises at least two layers of honeycomb structures 11 and at least one support plate 12; each honeycomb structure 11 is arranged in a stacked mode; and the support plate 12 is connected between the adjacent layers of the honeycomb structures 11.

[0049] The surface paper 20 has at least one layer and is attached to at least one side of the main body structure 10.

[0050] In the embodiment, the structural system of the aircraft is manufactured by using the composite paper structure 100, the composite paper structure 100 comprises at least two layers of honeycomb structures 11 and at least one support plate 12, the honeycomb structure 11 has high hardness and strength and good shear resistance, and can effectively disperse the load; the support plate 12 is arranged between any two adjacent layers of the honeycomb structures 11 and plays a role of supporting and uniformly dispersing the load. The composite structure of the honeycomb structure 11 and the support plate 12 can improve the overall strength and stability of the composite paper structure 100, meet the safety performance required by the structural system of the aircraft, effectively absorb the collision energy, and improve the safety and reliability of the structural system. Moreover, due to the hollow characteristics of the composite paper structure 100 and the arrangement of the honeycomb structure 11, the lightweight development of the structural system of the aircraft is facilitated. In addition, the composite paper structure 100 can be flexibly applied to the manufacture of the structural system with a complex shape, thereby having strong universality, being capable of being used to manufacture various structural systems, and having a simpler manufacturing process, easy recycling, and thereby improving the economy and resource sustainable development of the structural system.

[0051] Optionally, the surface paper 20 is attached to two sides of the main body structure 10.

[0052] Optionally, the honeycomb structure 11 has three or more layers, and the support plate 12 is arranged between the adjacent honeycomb structures 11. The support plate 12 is made of high-strength special paperboard and has high strength and rigidity, which can provide additional support for the hollow honeycomb structure 11, so that the multi-layer honeycomb structure 11 always maintains a relatively stable positional relationship under stress and is not prone to dislocation, thereby enhancing the stability of the structure. Moreover, when the multi-layer honeycomb structure 11 bears external load, the high-strength special paperboard can uniformly transmit the load to each honeycomb layer, avoid the load from being concentrated in some local areas, and cause the honeycomb structure 11 to be damaged too early, thereby fully exerting the load-bearing capacity of each layer of the honeycomb structure 11 and improving the load-bearing performance of the whole structure.

[0053] In addition, the high-strength special paperboard itself has certain elasticity and buffering performance, and plays a role of a buffer pad between the multiple honeycomb structures 11. The high-strength special paperboard can absorb and dissipate the vibration and impact force generated in the use process, reduce the propagation of vibration in the honeycomb structure 11, reduce the risk of fatigue damage of the structure due to vibration, and prolong the service life of the structure. Different layers of honeycomb structures 11 can also be isolated to prevent direct contact between the honeycomb structures 11 to generate friction, wear or mutual interference. At the same time, it can also protect the honeycomb structure 11 from external factors such as moisture, dust, chemicals and the like, and improve the durability of the structure. The high-strength special paperboard can also provide certain heat insulation, sound insulation and the like. The addition of the high-strength special paperboard as an isolation layer in the multiple honeycomb structures 11 can further improve the heat insulation and sound insulation effect of the entire structure, and meet the requirements of different application scenarios on the above performance.

[0054] In some possible embodiments, please refer to Figure 3 The honeycomb structure 11 comprises a plurality of hole units 110, and the plurality of hole units 110 are sequentially connected.

[0055] The composite paper structure 100 is in a flat state, and the edge of the hole unit 110 has a closed figure on the orthographic projection of the face paper 20.

[0056] In the same honeycomb structure 11, the closed figures of the hole units 110 are the same.

[0057] In the present embodiment, the honeycomb structure 11 is plate-shaped, and the specific structures of the plurality of honeycomb structures 11 can be the same. For example, the honeycomb structure 11 comprises a plurality of arrayed hole units 110, and the hole unit 110 structures of different honeycomb structures 11 are the same, that is, the orthographic projections on the face paper 20 are the same, which can be manufactured by the same processing method, thereby reducing the production cost. Moreover, the mechanical research of the same honeycomb structure 11 can also be shared, thereby further reducing the research and development cost.

[0058] In some possible embodiments, the hole unit 110 structures of different honeycomb structures 11 are the same, but the sizes are different, so that the composite paper structure 100 composed of the plurality of honeycomb structures 11 has more possible performance.

[0059] In some possible embodiments, the same honeycomb structure 11 comprises at least two hole units 110.

[0060] The closed figures of each hole unit 110 are different.

[0061] In the present embodiment, as Figures 2-3As shown, the honeycomb structure 11 is plate-shaped, and the specific structure of the plurality of honeycomb structures 11 can be different. For example, the honeycomb structure 11 comprises a plurality of arrayed hole units 110, and the hole units 110 of different honeycomb structures 11 have different structural shapes, that is, the orthographic projections on the surface paper 20 are different, thereby making the composite paper structure 100 composed of the plurality of honeycomb structures 11 have rich diversity, and the application scenarios of the composite paper structure 100 can be improved.

[0062] In some possible embodiments, the closed graph of the hole unit 110 of the honeycomb structure 11 comprises a regular geometric pattern.

[0063] In this embodiment, the hole unit 110 of the honeycomb structure 11 is a regular geometric pattern such as a rectangle, a rhombus, a parallelogram or a circle, and such a honeycomb structure 11 can simplify mechanical calculation, facilitate accurate engineering design and analysis, and can also bear force uniformly.

[0064] Moreover, the processing technology of the regular pattern is relatively simple, easy to realize high-precision processing, and can thereby reduce manufacturing cost.

[0065] Some possible implementations of the honeycomb structure 11 are provided in the present application.

[0066] In some possible implementations, the honeycomb structure 11 is a triangular honeycomb structure 11, has high strength and stability, and is suitable for positions requiring high compression resistance. For example, in the lightweight structure design of some unmanned aerial vehicles, the triangular honeycomb structure 11 is used as a sandwich material in the interior of a wing or a fuselage, so as to improve the rigidity and impact resistance of the structure.

[0067] In some possible implementations, the honeycomb structure 11 is a square honeycomb structure 11, which is relatively simple in manufacturing and processing, and has good isotropic performance. The square honeycomb structure 11 is applied in some aviation interior parts or non-main load-bearing structures, such as the interior lining of an aircraft door or the seat support structure.

[0068] In some possible implementations, the honeycomb structure 11 is a tubular honeycomb structure 11, which is composed of continuous tubular units and has high compression resistance and shear resistance. The tubular honeycomb structure 11 is used in some special applications, such as a heat-insulating and sound-absorbing material for an engine nacelle.

[0069] In some possible embodiments, the closed graph comprises an irregular polygon.

[0070] In this embodiment, the hole unit 110 of the honeycomb structure 11 is an irregular polygon, such as a quadrilateral with different side lengths, and is suitable for positions with relatively complex structures, while various different performances are taken into account.

[0071] In some possible embodiments, the honeycomb structure 11 is an over-stretched honeycomb structure 11, which is manufactured by a special stretching process, and the cell 110 is generally over-stretched rectangular. Such structure has high flexibility and fatigue resistance, and is suitable for parts requiring bending or complex shape, such as the fairing or the wing trailing edge of an airplane.

[0072] In some possible embodiments, at least one side of the closed figure is hyperbolic.

[0073] In the present embodiment, the honeycomb structure 11 can be a single-curved flexible honeycomb structure 11, which has a low equivalent elastic modulus and a significant deformation capacity when stretched in the plane, thereby achieving good flexibility and deformation capacity while ensuring structural strength. The single-curved flexible honeycomb structure 11 can be used to manufacture lightweight and high-deformation-capacity structural components, such as wings, fuselages, etc., thereby significantly reducing the structural weight and improving fuel efficiency.

[0074] In some possible embodiments, opposite two sides of the closed figure are hyperbolic.

[0075] In the present embodiment, the honeycomb structure 11 can be a double-curved flexible honeycomb structure 11, which has a curved cell shape and can provide good flexibility and deformation resistance in multiple directions, and is suitable for complex curved structures, such as the wing leading edge or the curved surface of the fuselage of an airplane.

[0076] In some possible embodiments, the closed figure comprises a regular hexagon.

[0077] The honeycomb structure 11 further comprises a reinforcing wall arranged in the first direction in at least one cell 110, and the edge is connected to the inner wall of the cell 110.

[0078] The first direction is perpendicular to the flattened composite paper structure 100.

[0079] In the present embodiment, the reinforcing wall comprises at least one vertical wall arranged in the cell 110, which can enhance the strength of the cell 110.

[0080] For example, the honeycomb structure 11 is a reinforced regular hexagonal honeycomb structure 11, which is improved on the basis of the traditional regular hexagonal honeycomb by adding additional reinforcing walls to improve the strength. Such structure is applied in some high-performance aviation composites, such as the main load-bearing structure of an airplane.

[0081] In some possible embodiments, the hole units 110 of the same honeycomb structure 11 have multiple different shapes, forming a composite-shaped honeycomb structure 11. For example, the hole units 110 of the same honeycomb structure 11 include hexagons and rhombuses. Such a honeycomb structure 11 combines hexagons and rhombuses, which can optimize the mechanical properties and weight distribution of the structure.

[0082] In some possible embodiments, as shown in FIG. 1, the at least two layers of honeycomb structures 11 include a first honeycomb panel and a second honeycomb panel; the closed figures of the hole units 110 of the first honeycomb panel are hexagons; and the material of the first honeycomb panel includes carbon fibers. Figure 3

[0083] The closed figures of the hole units 110 of the second honeycomb panel are rhombuses; and the material of the second honeycomb panel includes aramid fibers.

[0084] In the present embodiment, the upper-layer honeycomb structure 11 is the first honeycomb panel, and the lower-layer honeycomb structure 11 is the second honeycomb panel. The first honeycomb panel and the second honeycomb panel are stacked and spaced apart by a support plate 12, providing a certain supporting effect. The first honeycomb panel and the second honeycomb panel have different structural shapes and are made of different materials, for example, the manufacturing material of the first honeycomb panel includes carbon fibers, and the manufacturing material of the second honeycomb panel includes aramid fibers. The first honeycomb panel is a hexagonal honeycomb structure 11, which has high strength, high rigidity, and good shear resistance. The hexagonal structure of the first honeycomb panel can effectively disperse the load and improve the overall strength and stability of the material. At the same time, the weight is extremely light, meeting the requirements of lightweight in the aviation field. The second honeycomb panel is a rhombic honeycomb structure 11, which has higher shear strength in certain specific directions and is suitable for parts that need to be reinforced in specific directions. The mechanical properties can also be optimized by adjusting the angle and size of the rhombic hole units 110 to adapt to different design requirements. Moreover, the rhombic honeycomb structure 11 has higher flexibility in manufacturing complex shapes, can better adapt to the complex structure of the aircraft, can effectively absorb energy when impacted, and can improve the safety and reliability of the structure.

[0085] Therefore, the stacking of the first honeycomb panel and the second honeycomb panel can significantly improve the performance and economic requirements of the aviation structure based on the excellent mechanical properties, lightweight characteristics, and flexibility of the manufacturing process of each.

[0086] In some possible embodiments, the composite paper structure 100 is in a flat state, and the orthographic projection parts of the hole units 110 of the at least two layers of honeycomb structures 11 on the face paper 20 overlap.

[0087] ​In the embodiment, the orthographic projection of the hole units 110 of the two-layer honeycomb structure 11 on the surface paper 20 is partially overlapped, that is, the honeycomb structures 11 of at least two different layers are arranged in a staggered manner, and the hole units 110 of the respective layers have overlapped and non-overlapped portions in the vertical direction, so that the stress can be better dispersed, and the fatigue resistance and overall stability of the structure can be improved.

[0088] In some possible embodiments, please refer to Figures 1-3 The composite paper structure 100 further comprises an adhesive layer 30.

[0089] The adhesive layer 30 is arranged between the main structure 10 and the surface paper 20, and / or between the honeycomb structure 11 and the support plate 12.

[0090] In the embodiment, the honeycomb structure 11, the support plate 12 and the surface paper 20 can all be regarded as paperboards, and the adjacent paperboards are bonded by the adhesive layer 30, so that the processing is simple and economical.

[0091] For example, the adhesive layer 30 comprises a protein glue. Specifically, a suitable protein glue and paperboards are selected, and the protein glue is uniformly coated on the paperboards by a coater to form a thin glue film with a uniform thickness, and the amount of the protein glue is controlled to be 40-60 milliliters per square meter. Then, the paperboards coated with the protein glue are stacked according to a predetermined order and number of layers. The stacked paperboards are preliminarily compacted by a pair of compression rollers, so that the paperboards are preliminarily bonded together under the action of the protein glue, the air between the paperboards is discharged, and the compactness of the paperboards is improved. Then, the preliminarily compacted paperboards are placed on a flat-bed laminator, and are subjected to hot-pressing lamination under a certain temperature and pressure. The temperature, pressure and time and other parameters need to be controlled during the lamination to ensure the performance and quality of the composite material. The temperature, pressure and time are adjusted according to different paperboards and order structures, and the temperature is generally controlled to be 40-60 degrees Celsius, the pressure is generally controlled to be 1-3 MPa, and the time is several minutes to tens of minutes, so that the paperboards are firmly bonded together by the protein glue to form the composite paper structure 100.

[0092] In some possible embodiments, the support plate 12 comprises a base paper and a coating layer coated on the surface of the base paper.

[0093] In the embodiment, the composite paperboard is used as the support plate 12. The base paper is the main body of the support plate 12, and the coating layer can enhance the mechanical properties of the main body of the support plate 12.

[0094] Optionally, the base paper can be made of plant fibers, and the coating layer can be made of whisker material, which is coated on the surface of the base paper to form the support plate 12. Compared with the ordinary base paper, the support plate 12 with the whisker coating layer has at least the following advantages: a. It can improve the tensile strength and folding resistance, thereby enhancing the mechanical properties; b. It can enhance the gas barrier property and improve the liquid barrier property, thereby playing a good barrier role; c. It can improve the printing suitability and improve the printing effect; d. It can increase the stability and dimensional accuracy of the paperboard.

[0095] It should be noted that the various structures of the composite paper structure 100 provided in the embodiments of the present application are all made of existing materials, such as plant fibers or artificial fibers, which are easy to obtain and have mature technology and high feasibility.

[0096] Based on the same inventive concept, the embodiments of the present application also provide a structural system of an aircraft, which comprises any of the composite paper structures 100 provided in the foregoing embodiments.

[0097] The structural system of the aircraft provided in the embodiments comprises any of the composite paper structures 100 provided in the foregoing embodiments, and the implementation principles are similar, which will not be described here. In the embodiments, the structural system of the aircraft is manufactured by using the composite paper structure 100, which comprises at least two layers of the honeycomb structure 11 and at least one support plate 12. The honeycomb structure 11 has high hardness and strength and good shear resistance, and can effectively disperse the load. The support plate 12 is arranged between the honeycomb structures 11 and plays a supporting role. The composite structure of the honeycomb structure 11 and the support plate 12 can improve the overall strength and stability of the composite paper structure 100, and meet the safety performance required by the structural system of the aircraft. Moreover, due to the characteristics of the composite paper structure 100 and the arrangement of the honeycomb structure 11, the lightweight development of the structural system of the aircraft is facilitated. At the same time, the composite paper structure 100 has higher flexibility when manufacturing a structural system with a complex shape, thereby having strong versatility and being capable of being used to manufacture various structural systems, and the manufacturing process is more simple, thereby improving the economy of the structural system. In addition, the honeycomb structure 11 can effectively absorb collision energy, and can improve the safety and reliability of the structural system.

[0098] Optionally, the aircraft can include an airplane, and the structural system of the aircraft can include a wing, a fuselage, a fairing, an engine, or a main load-bearing structure of the airplane.

[0099] By applying some embodiments of the present application, the following beneficial effects can be achieved:

[0100] The composite paper structure 100 is used to manufacture a structural system of an aircraft, the composite paper structure 100 comprises at least two layers of honeycomb structures 11 and at least one support plate 12, the honeycomb structure 11 has high hardness and strength and good shear resistance, and can effectively disperse the load; the support plate 12 is arranged between any two adjacent honeycomb structures 11, and plays a role of supporting and uniformly dispersing the load. The composite structure of the honeycomb structure 11 and the support plate 12 can improve the overall strength and stability of the composite paper structure 100, meet the safety performance required by the structural system of the aircraft, the honeycomb structure 11 can effectively absorb collision energy, and also improve the safety and reliability of the structural system. Moreover, due to the hollow characteristics of the composite paper structure 100 itself and the arrangement of the honeycomb structure 11, the lightweight development of the structural system of the aircraft is facilitated. In addition, it can be flexibly applied to the manufacture of a structural system with complex shape, thereby making the composite paper structure 100 have strong versatility, can be used to manufacture various structural systems, and the manufacturing process is more simple, easy to recycle, thereby improving the economy and resource sustainable development of the structural system. In the description of the present application, the directions or positional relationships indicated by the words "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like are exemplary directions or positional relationships shown based on the drawings, and are used for the convenience of description or simplification of the description of the embodiments of the present application, and are not intended to indicate or imply that the devices or components indicated must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0101] The terms "first", "second", "third", etc. are used only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined as "first", "second", etc. can explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise stated, the meaning of "a plurality of" is two or more.

[0102] In the description of the present application, specific features, structures, materials or characteristics can be combined in any one or more embodiments or examples in a suitable manner.

[0103] The above only describes some embodiments of the present application, and it should be pointed out that, for those skilled in the art, other similar implementation manners based on the technical idea of the present application without departing from the technical concept of the present application also belong to the protection scope of the embodiments of the present application.

Claims

1. A composite paper structure, characterized by, The application relates to a composite paper structure applied to at least one structural system of an aircraft, comprising: a main structure comprising at least two layers of honeycomb structures and at least one support plate; each of the honeycomb structure layers is arranged in a stack; the support plate is connected between the honeycomb structures of adjacent layers; a face paper, at least one layer, attached to at least one side of the main structure.

2. The composite paper structure according to claim 1, wherein, The honeycomb structure comprises a plurality of cell units connected in sequence. The composite paper structure is in a flattened state, and the edge of the cell unit is in a closed figure on the face paper. In the same honeycomb structure, the closed figures of each cell unit are the same.

3. The composite paper structure according to claim 1, wherein, In the same honeycomb structure, at least two kinds of cell units are included. The closed figures of each kind of cell unit are different.

4. The composite paper structure according to claim 1, wherein, Further comprising at least one of the following: The closed figure of the cell unit of the honeycomb structure comprises a regular geometric figure. The closed figure comprises an irregular polygon. At least one side of the closed figure is curved. Opposite sides of the closed figure are hyperbolic.

5. The composite paper structure according to claim 4, wherein, The closed figure comprises a regular hexagon. The honeycomb structure further comprises a reinforcing wall arranged in at least one cell unit in a first direction, and the edge is connected with the inner wall of the cell unit. The first direction is perpendicular to the flattened composite paper structure.

6. The composite paper structure according to claim 4, wherein, The at least two layers of the honeycomb structure comprise a first honeycomb plate and a second honeycomb plate; the closed figure of the cell unit of the first honeycomb plate is a hexagon; and the material of the first honeycomb plate comprises carbon fibers. The closed figure of the cell unit of the second honeycomb plate is a rhombus; and the material of the second honeycomb plate comprises aramid fibers.

7. The composite paper structure according to claim 1, wherein, The composite paper structure is in a flattened state, and the cell units of the at least two layers of the honeycomb structure are partially overlapped on the face paper.

8. The composite paper structure according to claim 1, wherein Further comprising: an adhesive layer; The adhesive layer is arranged between the main structure and the face paper, and / or between the honeycomb structure and the support plate.

9. The composite paper structure according to claim 1, wherein, The support plate comprises a base paper and a coating layer coated on the surface of the base paper.

10. A structural system for an aircraft, characterized in that Comprising: The composite paper structure according to any one of claims 1-9.

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