Aircraft fuselage module and aircraft

Abstract

The utility model relates to the technical field of aircrafts, and discloses an aircraft fuselage module which comprises a frame, a bearing plate module, a top plate and a battery, the bearing plate module and the top plate are located on the inner side of the frame, the bearing plate module, the top plate and the frame are connected to form a cavity, and the battery is arranged in the cavity and used for supplying power to an aircraft. The battery and the fuselage are integrated and serve as a fuselage bearing structure and a battery bearing structure, the overall weight of the aircraft can be reduced, light weight is achieved, meanwhile, higher fuselage rigidity and strength can be provided for the aircraft and the battery, and the heat dissipation problem can be solved. According to the aircraft, the aircraft body is formed by connecting the aircraft body modules and the fuselage modules, modular assembly is achieved, when the service life of an aircraft battery is over, the fuselage modules can be rapidly replaced to achieve replacement of a new aircraft body and a new battery, or the battery fuselage structure can be rapidly replaced in the operation process to achieve efficient operation; and a very efficient design is provided for later maintenance, after-sale and operation.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, in particular to an aircraft fuselage module and aircraft. BACKGROUND

[0002] Batteries are widely used in energy storage power systems such as hydroelectric, thermal, wind and solar power stations, and in many fields such as automobiles, military equipment, aerospace. In the field of aircraft, there are various electrical equipment on the aircraft, so it is necessary to carry batteries on the aircraft. At present, the batteries on the aircraft are mostly installed in combination with multiple battery packs, and then the batteries are installed on the aircraft. The weight of the battery is large, in order to position and fix the battery, a positioning and fixing mechanism and a load-bearing reinforcing structure need to be added, so the existing battery not only increases the ineffective body weight, but also causes more structural parts to not only ensure the sufficient installation and load-bearing stiffness and strength requirements of the battery, but also require the aircraft to provide body load-bearing structure installation requirements.

[0003] The prior art discloses a kind of solid-state battery assembly for vertical take-off and landing aircraft with automatic docking, including battery main body, battery support and battery compartment, battery compartment includes main battery compartment and auxiliary battery compartment, main battery compartment and auxiliary battery compartment are changed position by pushing structure, the middle part of battery support is lifted and installed with shaft seat, and the shaft seat is rotatably installed with turnover baffle, main heat absorbing plate and auxiliary heat absorbing plate with water cavity are respectively arranged on main battery compartment and auxiliary battery compartment, and main heat absorbing plate and auxiliary heat absorbing plate are respectively installed with main connector and auxiliary connector with valve, water inlet pipe is arranged in the middle part of battery support, and water outlet pipe is arranged on both sides, gas pipe is connected between main battery compartment and auxiliary battery compartment, and air hole is arranged on the two battery compartments, and the both sides of battery support are installed with movable and installed closure plate, and the bottom of the both sides of battery support is installed with turnover type reinforcing plate. The battery support of the patent is installed in the bottom position of the aircraft, and the battery compartment is installed in the battery support, and the battery main body adopts solid-state battery that can be replaced, and is provided with power connection assembly, when the battery main body is installed in the battery compartment, can be connected with the power unit of the aircraft, to supply power to the aircraft. Therefore, the battery of the patent not only increases the ineffective body weight, but also causes more structural parts to not only ensure the sufficient installation and load-bearing stiffness and strength requirements of the battery, but also require the aircraft to provide body load-bearing structure installation requirements. UTILITY MODEL CONTENTS

[0004] The utility model aims at providing an aircraft fuselage module and aircraft that are beneficial to reducing overall weight and improving stiffness and strength.

[0005] In order to achieve the above object, the utility model provides a kind of aircraft fuselage module, aircraft includes aircraft main body and machine arm, the machine arm is connected with the aircraft main body, the fuselage module is part of the aircraft main body, the fuselage module includes frame, support plate module, top plate and battery, the support plate module and the top plate are located in the inside of the frame, and the support plate module and the top plate are connected with the frame to form cavity, the battery is located in the cavity, and the battery is used to power supply aircraft.

[0006] As a preferred scheme, further include a plurality of intermediate cross beams, the support plate module and the top plate are provided with a plurality of, the intermediate cross beam is located in the inside of the frame, the two ends of the intermediate cross beam are connected with the opposite sides of the frame respectively, the two sides of one support plate module are connected with two intermediate cross beams respectively, the two sides of one top plate are connected with two intermediate cross beams respectively, form a plurality of the cavity, and the battery is arranged in each cavity respectively.

[0007] As a preferred scheme, the frame includes first main longitudinal beam, second main longitudinal beam, first cross beam and second cross beam, the first main longitudinal beam, the first cross beam, the second main longitudinal beam and the second cross beam are connected in series to form a ring, the first main longitudinal beam is opposite to the second main longitudinal beam, the first cross beam is opposite to the second cross beam, and the two ends of the intermediate cross beam are connected with the first main longitudinal beam and the second main longitudinal beam respectively.

[0008] As a preferred scheme, the frame includes first main longitudinal beam, second main longitudinal beam, first cross beam and second cross beam, the first main longitudinal beam, the first cross beam, the second main longitudinal beam and the second cross beam are connected in series to form a ring, the first main longitudinal beam is opposite to the second main longitudinal beam, the first main longitudinal beam and the first cross beam, the first cross beam and the second main longitudinal beam, the second main longitudinal beam and the second cross beam, and the second cross beam and the first main longitudinal beam are connected through connecting joint, the connecting joint includes joint body, first plug-in part, second plug-in part and a plurality of connecting parts, the first plug-in part and the second plug-in part are connected with the joint body and are provided with insertion hole, and the first plug-in part and the second plug-in part are used for connecting the frame, the connecting part includes connecting plate, and one end of the connecting plate is connected with the joint body.

[0009] As a preferred scheme, the support plate module is provided with heat dissipation structure.

[0010] As a preferred scheme, cooling liquid passage is arranged on the support plate module, at least two cooling liquid inlet and outlet nozzles are connected with the support plate module, the cooling liquid passage and the cooling liquid inlet and outlet nozzles are communicated to form the heat dissipation structure.

[0011] As a preferred scheme, explosion-proof valve is arranged in the cavity.

[0012] As a preferred solution, the frame comprises a first main longitudinal beam, a second main longitudinal beam, a first cross beam and a second cross beam, the first main longitudinal beam, the first cross beam, the second main longitudinal beam and the second cross beam are connected end to end to form a ring, and the first main longitudinal beam, the second main longitudinal beam, the first cross beam and the second cross beam are all hollow tubes.

[0013] As a preferred solution, the intermediate cross beam is a hollow tube, and the inner wall of the intermediate cross beam is provided with a reinforcing rib.

[0014] The utility model also provides a kind of aircraft, including aircraft main body and arm, the aircraft main body includes one or more above-mentioned fuselage module, the arm is connected with the fuselage module.

[0015] As a preferred solution, it further comprises one or more body modules, and the body modules are connected with the fuselage modules to form the aircraft main body.

[0016] Compared with the prior art, the utility model has the beneficial effects that:

[0017] The utility model discloses a kind of aircraft, including aircraft main body and arm, the aircraft main body includes one or more above-mentioned fuselage module, the arm is connected with the fuselage module. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 It is the structural schematic diagram of the aircraft fuselage module of the utility model embodiment.

[0019] Figure 2 It is the cross-sectional structural schematic diagram of the aircraft fuselage module of the utility model embodiment.

[0020] Figure 3 It is the first visual angle structural schematic diagram of the aircraft fuselage module of the utility model embodiment when not installing top plate.

[0021] Figure 4It is the second visual angle structure schematic view of the aircraft fuselage module without installing the top plate of the embodiment of the utility model.

[0022] Figure 5 It is the longitudinal cutting schematic view of the aircraft fuselage module without installing the battery of the embodiment of the utility model.

[0023] Figure 6 It is the longitudinal cutting schematic view of the aircraft fuselage module without installing the top plate of the embodiment of the utility model.

[0024] Figure 7 It is the first visual angle schematic view of the frame and the bearing plate module connection of the embodiment of the utility model.

[0025] Figure 8 It is the second visual angle schematic view of the frame and the bearing plate module connection of the embodiment of the utility model.

[0026] Figure 9 It is the section view of the bearing plate module of the embodiment of the application.

[0027] Figure 10 It is the structure schematic view of the aircraft of the embodiment of the utility model.

[0028] In the figure, 1-bearing plate module;101-cooling liquid channel;102-explosion-proof port;103-first bearing plate;104-second bearing plate;2-top plate;3-battery;4-cavity;5-intermediate cross beam;501-stiffener;6-first main longitudinal beam;7-second main longitudinal beam;8-first cross beam;9-second cross beam;10-connection joint;1001-joint main body;1002-first plug-in part;1003-second plug-in part;1004-connection part;10041-connection plate;11-cooling liquid inlet and outlet nozzle;12-explosion-proof valve;13-body module;14-arm. DETAILED DESCRIPTION

[0029] The specific embodiments of the utility model are described in further detail below in combination with the drawings and examples. The following examples are used to illustrate the utility model, but are not used to limit the scope of the utility model.

[0030] In the description of the utility model, it needs to explain, the term "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and so on indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawing, only for the convenience of describing the utility model and simplifying the description, and therefore cannot be understood as limiting the utility model. In addition, the terms "first", "second" and "third" are only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0031] In the description of the utility model, it needs to explain, unless otherwise specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integrally connected, it can be mechanical connection, or electrical connection, it can be directly connected, or indirectly connected through intermediate medium, it can be the communication inside two elements. For ordinary skilled in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0032] In addition, in the description of the utility model, unless otherwise stated, the meaning of "a plurality of" is two or more than two.

[0033] Example one

[0034] As Figures 1 to 8 The utility model preferred embodiment's aircraft fuselage module, aircraft includes aircraft main body and machine arm 14, machine arm 14 is connected with aircraft main body, and the fuselage module is the part of aircraft main body, and the fuselage module includes frame, bearing plate module 1, top plate 2 and battery 3, and bearing plate module 1 and top plate 2 are located in the inside of frame, and bearing plate module 1 and top plate 2 are connected with frame to form cavity 4, and battery 3 is arranged in cavity 4, and battery 3 is used to supply power to aircraft. The embodiment is by arranging battery 3 in the cavity 4 formed by the connection of frame, bearing plate module 1 and top plate 2, makes the fuselage and battery 3 integration, and frame, top plate 2 and bearing plate module 1 are not only fuselage bearing structure but also battery 3 bearing structure, which is conducive to reducing the overall weight of aircraft, realizing lightweight, at the same time, not only can provide higher fuselage stiffness and strength for aircraft, but also provide high strength and high stiffness protection for aircraft battery 3, and battery 3 and fuselage integration, more conducive to battery 3 heat dissipation, solve the important safety problem of aircraft heat dissipation.

[0035] The battery 3 of the embodiment is not limited to solid or non-solid or soft package or hard package battery 3.

[0036] Example two

[0037] The difference between the embodiment and the embodiment one is that the aircraft fuselage module is further illustrated based on the embodiment one.

[0038] The aircraft fuselage module of the embodiment further comprises a plurality of intermediate cross beams 5, the support plate module 1 and the top plate 2 are arranged in plurality, the intermediate cross beams 5 are located at the inner side of the frame, the two ends of the intermediate cross beams 5 are connected with the opposite sides of the frame respectively, the two sides of one support plate module 1 are connected with two intermediate cross beams 5 respectively, the two sides of one top plate 2 are connected with two intermediate cross beams 5 respectively, a plurality of cavities 4 are formed, and the battery 3 is arranged in each cavity 4 respectively. The intermediate cross beams 5 are arranged, the batteries 3 are arranged in plurality of independent cavities 4, the batteries 3 are arranged separately, which is beneficial to heat dissipation and safety of the batteries 3. And the intermediate cross beams 5 can improve the strength of the frame. The two adjacent cavities 4 of the embodiment do not share the intermediate cross beams 5.

[0039] Specifically, the frame comprises a first main longitudinal beam 6, a second main longitudinal beam 7, a first cross beam 8 and a second cross beam 9, the first main longitudinal beam 6, the first cross beam 8, the second main longitudinal beam 7 and the second cross beam 9 are connected in series to form a ring shape, the first main longitudinal beam 6 is opposite to the second main longitudinal beam 7, the first cross beam 8 is opposite to the second cross beam 9, and the two ends of the intermediate cross beam 5 are connected with the first main longitudinal beam 6 and the second main longitudinal beam 7 respectively. The frame of the embodiment is a rectangular closed frame, the length of the left main longitudinal beam 6 and the right main longitudinal beam 7 is greater than the length of the front cross beam 8 and the rear cross beam 9. Since the left main longitudinal beam 6 and the right main longitudinal beam 7 are longer, the independent box body is verified by test to meet the requirement that when the battery is in thermal runaway, all batteries are not powered off to cause power loss of the aircraft, and the power backup function is played. And the large energy battery is divided into small module batteries (small energy body), which can prevent the large energy body from releasing instantaneously when the aircraft is in thermal runaway. When the battery in a certain box body is in thermal runaway, the box body structure is made of high-strength metal material and sealed structure, and the explosion-proof valve can only release smoke through a specified path, thereby preventing the fire from spreading to other box bodies. Even if the battery in a certain box body is in thermal runaway, the surrounding is metal material with high heat conduction, so that the frame structure will not lose the body bearing function due to the sudden decrease of the strength caused by the high temperature in thermal runaway.

[0040] The connection between the intermediate cross beam 5 and the first main longitudinal beam 6 and the second main longitudinal beam 7 is not limited to the connection mode, which can be adhesive, welding or mechanical connection. After connection, sealing can be realized.

[0041] The intermediate cross beam 5, the first main longitudinal beam 6, the second main longitudinal beam 7, the first cross beam 8 and the second cross beam 9 are all extruded from high-strength alloy material. Specifically, the intermediate cross beam 5, the first main longitudinal beam 6, the second main longitudinal beam 7, the first cross beam 8 and the second cross beam 9 are all made of alloy material with tensile strength not less than 350 MPa, specified non-proportional elongation strength Rp0.2 not less than 310 MPa, elongation after fracture not less than 8%, material density not greater than 2.9 g / cm3, and thermal conductivity not less than 150 W / mK.

[0042] Further, the first main longitudinal beam 6 and the first cross beam 8, the first cross beam 8 and the second main longitudinal beam 7, the second main longitudinal beam 7 and the second cross beam 9, and the second cross beam 9 and the first main longitudinal beam 6 are connected by the connecting joint 10, which includes a joint body 1001, a first plug-in part 1002, a second plug-in part 1003 and a plurality of connecting parts 1004. The first plug-in part 1002 and the second plug-in part 1003 are connected with the joint body 1001 and are both provided with a plug hole. The first plug-in part 1002 and the second plug-in part 1003 are used for frame connection. The connecting part 1004 includes a connecting plate 10041, one end of which is connected with the joint body 1001. The frame of the embodiment is connected by four connecting joints 10, which are the first connecting joint 10, the second connecting joint 10, the third connecting joint 10 and the fourth connecting joint 10. The first end of the first main longitudinal beam 6 is plugged into the plug hole of the first plug-in part 1002 of the first connecting joint 10. The first end of the first cross beam 8 is plugged into the plug hole of the second plug-in part 1003 of the first connecting joint 10. The second end of the first cross beam 8 is plugged into the plug hole of the first plug-in part 1002 of the second connecting joint 10. The first end of the second main longitudinal beam 7 is plugged into the plug hole of the second plug-in part 1003 of the second connecting joint 10. The second end of the second main longitudinal beam 7 is plugged into the plug hole of the first plug-in part 1002 of the third connecting joint 10. The first end of the second cross beam 9 is plugged into the plug hole of the second plug-in part 1003 of the third connecting joint 10. The second end of the second cross beam 9 is plugged into the plug hole of the first plug-in part 1002 of the fourth connecting joint 10. The second end of the first main longitudinal beam 6 is plugged into the plug hole of the second plug-in part 1003 of the fourth connecting joint 10. In addition, the connecting part 1004 of the embodiment has two parallel and spaced connecting plates 10041, which can be connected with other parts of the aircraft body or the arm 14 by riveting, welding or the like.

[0043] The connecting joint 10 is made of high-strength alloy material by casting or machining. In addition, the connecting joint 10 is made of alloy material with tensile strength not less than 440 MPa, elongation after fracture not less than 7%, and material density not greater than 2.9 g / cm3.

[0044] Optionally, the frame comprises a first main longitudinal beam 6, a second main longitudinal beam 7, a first cross beam 8 and a second cross beam 9, the first main longitudinal beam 6, the first cross beam 8, the second main longitudinal beam 7 and the second cross beam 9 are connected end to end to form a ring, and the first main longitudinal beam 6, the second main longitudinal beam 7, the first cross beam 8 and the second cross beam 9 are all hollow tubes. The first main longitudinal beam 6, the second main longitudinal beam 7, the first cross beam 8 and the second cross beam 9 of the embodiment are all rectangular in cross section, facilitating the connection of the support plate module 1, the top plate 2 and the intermediate cross beam 5.

[0045] In addition, the intermediate cross beam 5 is a hollow tube, and the inner wall of the intermediate cross beam 5 is provided with a reinforcing rib 501. The intermediate cross beam 5 of the embodiment is rectangular in cross section, and the two sides of the reinforcing rib 501 are connected to the two opposite inner walls of the intermediate cross beam 5.

[0046] The first main longitudinal beam 6, the second main longitudinal beam 7, the first cross beam 8, the second cross beam 9, the connecting joint 10, the intermediate cross beam 5, the support plate module 1 and the top plate 2 are all made of high-strength aluminum alloy material, so that the aircraft battery 3 does not appear structural thermal deformation after thermal runaway, resulting in loss of structural load-bearing capacity of the aircraft structure.

[0047] Embodiment three

[0048] The difference between the embodiment and the embodiment two is that the support plate module 1 is further described in the embodiment three based on the embodiment two.

[0049] In the embodiment, the support plate module 1 is provided with a heat dissipation structure, which is helpful for the heat dissipation of the aircraft and the battery 3, and effectively realizes the heat dissipation and heat insulation of the aircraft. Specifically, the support plate module 1 is provided with a cooling liquid channel 101, and at least two cooling liquid inlet and outlet nozzles 11 are connected to the support plate module 1, and the cooling liquid channel 101 and the cooling liquid inlet and outlet nozzles 11 are in communication to form a heat dissipation structure. The cooling liquid enters the cooling liquid channel 101 through one of the cooling liquid inlet and outlet nozzles 11, and then flows out from the other cooling liquid inlet and outlet nozzle 11, thereby cooling the battery 3 placed on the support plate module 1 and the cavity 4. The support plate module 1 comprises a first support plate 1 and a second support plate 1 connected together, the first support plate 1 is provided with a protruding structure, and the protruding structure and the second support plate 1 form the cooling liquid channel 101.

[0050] The connection between the first support plate 1 and the second support plate 1 and the cooling liquid inlet and outlet nozzle 11 and the support plate module 1 is not limited to mechanical connection or welding. When the fuselage module constitutes the main body of the aircraft, the support plate module 1 is placed on the outside, which can improve the heat dissipation rate of the battery 3 during charging and discharging. In the embodiment, the fuselage module serves as the bottom of the main body of the aircraft, and therefore the support plate module 1 is located on the bottom side of the aircraft. The top plate 2 of the embodiment is provided with a via hole communicating with the cavity 4, one end of the cooling liquid inlet and outlet nozzle 11 is connected to the support plate module 1, and the other end of the cooling liquid inlet and outlet nozzle 11 extends out of the via hole.

[0051] Further, the cavity 4 is provided with an explosion-proof valve 12. The explosion-proof valve 12 is connected to the bearing plate module 1, the bearing plate module 1 is provided with an explosion-proof opening 102, and the explosion-proof valve 12 is connected to the explosion-proof opening 102. The bearing plate module 1, the two intermediate cross beams 5, the frame and the top plate 2 form a self-contained sealed cavity, which can achieve IP68 level. The battery 3 is placed in the sealed cavity 4, and the explosion-proof valve 12 can control the pressure in the cavity 4 to prevent heat runaway, string explosion and other phenomena, thereby improving safety. When the bottom plate 1, the cover plate 2, the intermediate cross beam 5 and the first and second main longitudinal beams 6 and 7 are connected, they are all sealed.

[0052] The other structures of the embodiment are the same as those of embodiment two, and will not be described here.

[0053] Embodiment four

[0054] As shown in Figure 9 The utility model discloses an aircraft, including aircraft main body and machine arm 14, machine arm 14 is connected with aircraft main body, and aircraft main body includes one or more machine body module of the embodiment one or embodiment two or embodiment three, and machine arm 14 is connected with machine body module. Machine arm 14 is used for supporting power device, and one end of machine arm 14 is connected with rotor, and the other end of machine arm 14 is connected with the frame of machine body module, and the connecting part 1004 of connecting joint 1001 of the machine arm 14 of the embodiment is connected.

[0055] In addition, the aircraft of the embodiment further includes one or more machine body modules 13, and the machine body module 13 is connected with the machine body module to form the aircraft main body. The machine body module 13 of the embodiment includes a support, and the frame of the machine body module is connected with the frame of the adjacent machine body module 13. The aircraft main body of the embodiment includes one machine body module and multiple machine body modules 13, and the machine body module and the machine body module 13 are connected to form an aircraft main body with a cabin, and the machine body module serves as the bottom of the aircraft main body. The support of the machine body module 13 is connected with the frame of the machine body module by welding, riveting or other forms. The support of the machine body module 13 is provided with a skin. The aircraft main body of the embodiment is connected by one machine body module and one machine body module 13.

[0056] The aircraft of the embodiment is connected by multiple machine body modules 13 and machine body modules to form an aircraft main body, realizes modular assembly, and when the service life of the aircraft battery 3 ends, the machine body module can be quickly replaced to realize replacement of the new aircraft main body and the battery 3, or the battery 3 can be quickly replaced in operation to realize efficient operation of the machine body structure, which provides very efficient design for later maintenance, after-sales service and operation.

[0057] In summary, the utility model embodiment provides a kind of aviation fuselage module, it is by battery 3 is arranged in the cavity 4 formed by the frame, support plate module 1 and top plate 2 connection, make fuselage and battery 3 integration, frame, top plate 2 and support plate module 1 are fuselage bearing structure and battery 3 bearing structure, it is favorable to reduce the overall weight of aircraft, realize light weight, can not only provide higher fuselage stiffness and strength for aircraft, also provide high strength high stiffness protection for aircraft battery 3, and battery 3 is integrated with fuselage, more conducive to battery 3 heat dissipation, solve the important safety problem of aircraft heat dissipation.Fuselage module cavity 4 is provided with explosion-proof valve 12, realizes thermal runaway cut-off protection.And fuselage module uses alloy material, tensile strength is not less than 350Mpa, specified non-proportional extension intensity Rp0.2 is not less than 310Mpa, elongation after break is not less than 8%, material density is not more than 2.9g / cm3, thermal conductivity is not less than 150W / mK, so that aircraft battery 3 thermal runaway does not appear structural thermal deformation and leads to the loss of structural bearing capacity of aircraft structure.The utility model embodiment aircraft is connected by several body modules 13 and fuselage module to form aircraft main body, realize modular assembly, when aircraft battery 3 life ends, can quickly replace fuselage module to realize the replacement of new aircraft main body and battery 3, or in operation, battery 3 fuselage structure can be quickly replaced to realize efficient operation, provide very efficient design for later maintenance, after-sales service, operation.

[0058] The above is only preferred embodiment of the utility model, it should be pointed out, for ordinary skilled person in the art, without departing from the technical principle of the utility model, can make several improvements and substitutions, these improvements and substitutions also should be considered as the protection scope of the utility model.

Claims

1. A module of an aircraft fuselage, the aircraft comprising an aircraft body and an arm (14), the arm (14) being connected to the aircraft body, characterized in that, The fuselage module is part of the aircraft body, the fuselage module comprises a frame, a support plate module (1), a top plate (2) and a battery (3), the support plate module (1) and the top plate (2) are located on the inner side of the frame, and the support plate module (1) and the top plate (2) are connected with the frame to form a cavity (4), and the battery (3) is arranged in the cavity (4), and the battery (3) is used for supplying power to the aircraft.

2. The aircraft fuselage module of claim 1, wherein, A plurality of intermediate cross beams (5) are further included, the support plate module (1) and the top plate (2) are arranged in plurality, the intermediate cross beams (5) are located on the inner side of the frame, the two ends of the intermediate cross beams (5) are connected with the opposite sides of the frame respectively, the two sides of one support plate module (1) are connected with two intermediate cross beams (5) respectively, the two sides of one top plate (2) are connected with two intermediate cross beams (5) respectively, and a plurality of cavities (4) are formed, and the battery (3) is arranged in each cavity (4).

3. The aircraft fuselage module of claim 2, wherein, The frame comprises a first main longitudinal beam (6), a second main longitudinal beam (7), a first cross beam (8) and a second cross beam (9), the first main longitudinal beam (6), the first cross beam (8), the second main longitudinal beam (7) and the second cross beam (9) are connected in series to form a ring shape, the first main longitudinal beam (6) is opposite to the second main longitudinal beam (7), the first cross beam (8) is opposite to the second cross beam (9), and the two ends of the intermediate cross beam (5) are connected with the first main longitudinal beam (6) and the second main longitudinal beam (7) respectively.

4. The aircraft fuselage module of claim 1, wherein, The frame comprises a first main longitudinal beam (6), a second main longitudinal beam (7), a first cross beam (8) and a second cross beam (9), the first main longitudinal beam (6), the first cross beam (8), the second main longitudinal beam (7) and the second cross beam (9) are connected in series to form a ring shape, the first main longitudinal beam (6) is opposite to the second main longitudinal beam (7), the first main longitudinal beam (6) and the first cross beam (8), the first cross beam (8) and the second main longitudinal beam (7), the second main longitudinal beam (7) and the second cross beam (9), and the second cross beam (9) and the first main longitudinal beam (6) are connected through a connecting joint (10), the connecting joint (10) comprises a joint body (1001), a first plug-in part (1002), a second plug-in part (1003) and a plurality of connecting parts (1004), the first plug-in part (1002) and the second plug-in part (1003) are connected with the joint body (1001) and are each provided with a plug hole, the first plug-in part (1002) and the second plug-in part (1003) are used for connecting the frame, and the connecting part (1004) comprises a connecting plate (10041), one end of the connecting plate (10041) is connected with the joint body (1001).

5. The aircraft fuselage module of Claim 1, wherein, The support plate module (1) is provided with a heat dissipation structure.

6. The aircraft fuselage module of claim 5, wherein, The supporting plate module (1) is provided with a cooling liquid channel (101), and the supporting plate module (1) is connected with at least two cooling liquid inlet and outlet nozzles (11), the cooling liquid channel (101) and the cooling liquid inlet and outlet nozzles (11) are communicated to form the heat dissipation structure.

7. The aircraft fuselage module of claim 1, wherein, The cavity (4) is provided with an explosion-proof valve (12).

8. The aircraft fuselage module of Claim 1, wherein, The frame comprises a first main longitudinal beam (6), a second main longitudinal beam (7), a first cross beam (8) and a second cross beam (9), the first main longitudinal beam (6), the first cross beam (8), the second main longitudinal beam (7) and the second cross beam (9) are connected in series to form a ring shape, and the first main longitudinal beam (6), the second main longitudinal beam (7), the first cross beam (8) and the second cross beam (9) are all hollow tubes.

9. The aircraft fuselage module of Claim 2, wherein, The intermediate cross beam (5) is a hollow tube, and the inner wall of the intermediate cross beam (5) is provided with a reinforcing rib (501).

10. An aircraft, characterized in that The aircraft comprises an aircraft body and an arm (14), the aircraft body comprises one or more body modules according to any one of claims 1-9, and the arm (14) is connected with the body module.

11. The aircraft of claim 10, wherein, The aircraft further comprises one or more body modules, and the body module (13) is connected with the body module to form the aircraft body.

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