Aircraft fuselage module and aircraft

Abstract

The invention relates to the technical field of aircrafts, and discloses an aircraft fuselage module which comprises a frame, a bottom plate module, a cover plate and a battery, the bottom plate module and the cover plate are located on the inner side of the frame, the bottom plate module, the cover 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 is integrated with the aircraft body and serves as an aircraft body bearing structure and a battery bearing structure, the overall weight of the aircraft can be reduced, light weight is achieved, meanwhile, higher aircraft body rigidity and strength can be provided for the aircraft and the battery, and the problem of thermal runaway of the aircraft can be solved. According to the aircraft, the aircraft body is formed by connecting the multiple aircraft body modules and the aircraft body modules, modular assembly is achieved, when the service life of an aircraft battery is over, the aircraft body modules can be rapidly replaced to achieve replacement of a new aircraft body and a new battery, or the battery aircraft body 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 present invention relates to the technical field of aircraft, and in particular to an aircraft fuselage module and an aircraft. Background Art

[0002] Batteries are widely used in energy storage power systems such as hydropower, thermal power, wind power and solar power stations, as well as in automobiles, military equipment, aerospace and other fields. In the field of aircraft, since there are many electrical equipment on the aircraft, it is necessary to carry batteries on the aircraft. At present, most batteries on aircraft are installed in combination with multiple battery packs, and then the batteries are installed on the aircraft. The batteries are heavy. In order to position and fix the batteries, it is necessary to add positioning and fixing mechanisms and load-bearing reinforcement structures. Therefore, the existing batteries not only increase the ineffective weight of the fuselage, but also lead to more structural parts. Not only do they need to ensure that the batteries are sufficiently installed to meet the bearing stiffness strength requirements, but they also require the aircraft to provide fuselage bearing structure installation requirements.

[0003] The prior art discloses an automatically dockable solid-state battery assembly for a vertical take-off and landing aircraft, comprising a battery body, a battery bracket and a battery compartment, the battery compartment comprising a main battery compartment and an auxiliary battery compartment, the main battery compartment and the auxiliary battery compartment are changed in position by a pushing structure, an axle seat is installed in the middle of the battery bracket for lifting and lowering, and a flip baffle is rotatably installed on the axle seat, a main heat absorbing plate and an auxiliary heat absorbing plate with a water cavity are respectively provided on the main battery compartment and the auxiliary battery compartment, and a main joint and an auxiliary joint with a valve are respectively installed on the main heat absorbing plate and the auxiliary heat absorbing plate, a water inlet pipe is provided in the middle of the battery bracket, and water outlet pipes are provided on both sides, an air pipe is connected between the main battery compartment and the auxiliary battery compartment, and vents are provided on the two battery compartments, closing plates are movably installed on both sides of the battery bracket, and flip-type reinforcing plates are installed on the bottom of both sides of the battery bracket. The battery bracket of the patent is installed at the bottom of the aircraft, and the battery compartment is installed in the battery bracket. The battery body adopts a solid-state battery that can be replaced, and a power connection component is provided on it. When the battery body is installed in the battery compartment, it can be docked with the power unit of the aircraft to power the aircraft. Therefore, the battery of the patent not only increases the ineffective weight of the aircraft, but also leads to more structural parts that not only need to ensure that the battery is sufficiently installed to meet the bearing stiffness strength requirements, but also require the aircraft to provide the body bearing structure installation requirements. Summary of the invention

[0004] The object of the present invention is to provide an aircraft fuselage module and an aircraft which are advantageous in reducing the overall weight and improving the rigidity and strength.

[0005] In order to achieve the above-mentioned purpose, the present invention provides an aircraft fuselage module, the aircraft includes an aircraft body and an arm, the arm is connected to the aircraft body, the fuselage module is a part of the aircraft body, the fuselage module includes a frame, a base plate module, a cover plate and a battery, the base plate module and the cover plate are located on the inner side of the frame, and the base plate module, the cover plate and the frame are connected to form a cavity, the cavity is a sealed cavity, the battery is arranged in the cavity, and the battery is used to supply power to the aircraft.

[0006] As a preferred embodiment, it also includes multiple frame beams, the base plate module and the cover plate are set in multiple numbers, the frame beams are located on the inner side of the frame, the two ends of the frame beams are respectively connected to the opposite sides of the frame, the two sides of a base plate module are respectively connected to the two frame beams, and the two sides of a cover plate are respectively connected to the two frame beams, so as to form a plurality of cavities, and the battery is respectively arranged in each cavity.

[0007] As a preferred embodiment, the frame includes a left main longitudinal beam, a right main longitudinal beam, a front cross beam and a rear cross beam. The left main longitudinal beam, the front cross beam, the right main longitudinal beam and the rear cross beam are connected end to end to form a ring. The left main longitudinal beam is opposite to the right main longitudinal beam, the front cross beam is opposite to the rear cross beam, and the two ends of the frame cross beam are respectively connected to the left main longitudinal beam and the right main longitudinal beam.

[0008] As a preferred solution, the frame cross beam, the left main longitudinal beam, the right main longitudinal beam, the front cross beam and the rear cross beam are all formed by extrusion of high-strength alloy materials.

[0009] As a preferred embodiment, the frame includes a left main longitudinal beam, a right main longitudinal beam, a front cross beam and a rear cross beam. The left main longitudinal beam, the front cross beam, the right main longitudinal beam and the rear cross beam are connected end to end to form a ring. The left main longitudinal beam is opposite to the right main longitudinal beam, and the front cross beam is opposite to the rear cross beam. The left main longitudinal beam and the front cross beam, the front cross beam and the right main longitudinal beam, the right main longitudinal beam and the rear cross beam, and the rear cross beam and the left longitudinal beam are connected by connecting joints. The connecting joint includes a joint body, a first plug-in part, a second plug-in part and a plurality of connecting parts. The first plug-in part and the second plug-in part are connected to the joint body and are both provided with jacks. The first plug-in part and the second plug-in part are used for connecting the frame. The connecting part includes a connecting plate, one end of which is connected to the joint body.

[0010] As a preferred solution, the connection joint is formed by casting or machining using a high-strength alloy material.

[0011] As a preferred solution, the base plate module is provided with a heat dissipation structure.

[0012] As a preferred solution, a cooling liquid channel is provided on the bottom plate module, at least two cooling liquid inlet and outlet nozzles are connected to the bottom plate module, and the cooling liquid channel is connected to the cooling liquid inlet and outlet nozzles to form the heat dissipation structure.

[0013] As a preferred solution, an explosion-proof valve is provided in the cavity.

[0014] As a preferred embodiment, the frame includes a left main longitudinal beam, a right main longitudinal beam, a front cross beam and a rear cross beam. The left main longitudinal beam, the front cross beam, the right main longitudinal beam and the rear cross beam are connected end to end to form a ring. The left main longitudinal beam, the right main longitudinal beam, the front cross beam and the rear cross beam are all hollow tubes.

[0015] As a preferred solution, the frame cross beam is a hollow tube, and the inner wall of the frame cross beam is provided with reinforcing ribs.

[0016] The present invention also provides an aircraft, comprising an aircraft body and an arm, wherein the aircraft body comprises one or more of the above-mentioned fuselage modules, and the arm is connected to the fuselage module.

[0017] As a preferred solution, it further comprises one or more fuselage modules, wherein the fuselage modules are connected with the fuselage modules to form the aircraft body.

[0018] Compared with the prior art, the present invention has the following beneficial effects: The present invention integrates the fuselage and the battery by placing the battery in a cavity formed by connecting the frame, the bottom plate module and the cover plate. The frame, the cover plate and the bottom plate module are both the fuselage load-bearing structure and the battery load-bearing structure, which is conducive to reducing the overall weight of the aircraft and achieving lightweight. At the same time, it can not only provide the aircraft with higher fuselage rigidity and strength, but also provide high-strength and high-rigidity protection for the aircraft battery. In addition, the battery and the fuselage are integrated, which is more conducive to the heat dissipation of the battery. The cavity of the present invention is a sealed cavity, which solves the important safety problem of thermal runaway of the aircraft. The aircraft of the present invention forms the aircraft body by connecting a number of fuselage modules with the fuselage module to achieve modular assembly. When the aircraft battery life ends, the fuselage module can be quickly replaced to achieve the replacement of the new aircraft body and battery, or the battery fuselage structure can be quickly replaced during operation to achieve efficient operation, providing a very efficient design for later maintenance, after-sales, and operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic structural diagram of an aircraft fuselage module according to an embodiment of the present invention.

[0020] Figure 2 It is a schematic cross-sectional structure diagram of an aircraft fuselage module according to an embodiment of the present invention.

[0021] Figure 3It is a first-view structural schematic diagram of an aircraft fuselage module according to an embodiment of the present invention when a cover plate is not installed.

[0022] Figure 4 It is a schematic structural diagram from a second viewing angle when the aircraft fuselage module according to an embodiment of the present invention is not installed with a cover plate.

[0023] Figure 5 It is a longitudinal section schematic diagram of an aircraft fuselage module according to an embodiment of the present invention when no battery is installed.

[0024] Figure 6 It is a longitudinal section schematic diagram of an aircraft fuselage module according to an embodiment of the present invention when a cover plate is not installed.

[0025] Figure 7 It is a schematic diagram from a first perspective of the connection between the frame and the base plate module of an embodiment of the present invention.

[0026] Figure 8 2 is a schematic diagram of the connection between the frame and the base plate module according to an embodiment of the present invention from a second viewing angle.

[0027] Fig. 9 is a cross-sectional view of a base plate module according to an embodiment of the present invention.

[0028] Fig.10 Schematic diagram of the structure of an aircraft according to an embodiment of the present invention.

[0029] In the figure, 1-bottom plate module; 101-cooling liquid channel; 102-explosion-proof port; 103-first bottom plate; 104-second bottom plate; 2-cover plate; 3-battery; 4-cavity; 5-frame beam; 501-reinforcement rib; 6-left main longitudinal beam; 7-right main longitudinal beam; 8-front beam; 9-rear beam; 10-connecting joint; 1001-joint body; 1002-first plug-in part; 1003-second plug-in part; 1004-connecting part; 10041-connecting plate; 11-cooling liquid inlet and outlet nozzle; 12-explosion-proof valve; 13-machine body module; 14-machine arm. DETAILED DESCRIPTION

[0030] The specific implementation of the present invention is further described in detail below in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0031] In the description of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0032] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0033] Furthermore, in the description of the present invention, unless otherwise specified, “plurality” means two or more.

[0034] Embodiment 1 like Figures 1 to 8 As shown, an aircraft fuselage module of a preferred embodiment of the present invention, the aircraft includes an aircraft body and an arm 14, the arm 14 is connected to the aircraft body, the fuselage module is a part of the aircraft body, the fuselage module includes a frame, a bottom plate module 1, a cover plate 2 and a battery 3, the bottom plate module 1 and the cover plate 2 are located on the inner side of the frame, and the bottom plate module 1 and the cover plate 2 are connected to the frame to form a cavity 4, the cavity 4 is a sealed cavity, the battery 3 is arranged in the cavity 4, and the battery 3 is used to supply power to the aircraft. In this embodiment, the battery 3 is arranged in a cavity 4 formed by connecting the frame, the bottom plate module 1 and the cover plate 2, so that the fuselage and the battery 3 are integrated. The frame, the cover plate 2 and the bottom plate module 1 are both the fuselage bearing structure and the battery 3 bearing structure, which is beneficial to reducing the overall weight of the aircraft and achieving lightweight. At the same time, it can not only provide the aircraft with higher fuselage stiffness and strength, but also provide high-strength and high-rigidity protection for the aircraft battery 3. In addition, the battery 3 is integrated with the fuselage, which is more conducive to the heat dissipation of the battery 3. The cavity 4 of this embodiment is a sealed cavity, which solves the important safety problem of thermal runaway of the aircraft.

[0035] The battery 3 of this embodiment is not limited to solid or non-solid or soft-pack or hard-pack battery 3. In addition, the sealing form of the cavity 4 is not limited. In addition, the inner wall of the cavity 4 is also provided with a heat insulation structure.

[0036] Embodiment 2 The difference between this embodiment and the first embodiment is that, based on the first embodiment, this embodiment further illustrates the aircraft fuselage module.

[0037] The aircraft fuselage module of this embodiment also includes a plurality of frame beams 5. The bottom plate module 1 and the cover plate 2 are provided in a plurality of frame beams 5. The frame beams 5 are located on the inner side of the frame. The two ends of the frame beams 5 are respectively connected to the two opposite sides of the frame. The two sides of a bottom plate module 1 are respectively connected to two frame beams 5, and the two sides of a cover plate 2 are respectively connected to two frame beams 5, forming a plurality of cavities 4, each of which is provided with a battery 3. The frame beams 5 are provided to be divided into a plurality of independent cavities 4, and the batteries 3 are placed separately, which is beneficial to the heat dissipation and safety of the batteries 3. In addition, the frame beams 5 can improve the strength of the frame. The frame beams 5 are not shared between two adjacent cavities 4 of this embodiment.

[0038] Specifically, the frame includes a left main longitudinal beam 6, a right main longitudinal beam 7, a front cross beam 8 and a rear cross beam 9. The left main longitudinal beam 6, the front cross beam 8, the right main longitudinal beam 7 and the rear cross beam 9 are connected end to end to form a ring. The left main longitudinal beam 6 is opposite to the right main longitudinal beam 7, and the front cross beam 8 is opposite to the rear cross beam 9. The two ends of the frame cross beam 5 are respectively connected to the left main longitudinal beam 6 and the right main longitudinal beam 7. There is a certain gap between the frame cross beam 5 closest to the front cross beam 8 and the front cross beam 8, and there is a certain gap between the frame cross beam 5 closest to the rear cross beam 9 and the rear cross beam 9. It should be pointed out that there may be no gap or a gap between the frame cross beam 5 closest to the front cross beam 8 and the front cross beam 8, and between the frame cross beam 5 closest to the rear cross beam 9 and the rear cross beam 9. The frame of the present embodiment is a rectangular closed frame, and the length of the left main longitudinal beam 6 and the right main longitudinal beam 7 is greater than that 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 relatively long, they are split into independent boxes to ensure that when thermal runaway occurs, all batteries will not be powered off, resulting in loss of aircraft power, and thus play a role in power backup; and the large-energy battery is decomposed into small module batteries (small energy bodies) to prevent the instantaneous release of large-energy bodies such as explosion and fire when the aircraft thermal runaway occurs; when a box battery thermally runs away, the box structure is made of high-strength metal materials and a sealed structure, and the explosion-proof valve can only release smoke in a specified path, thereby preventing the module from being burned to other boxes; even if a box battery thermally runs away, the surrounding area is made of metal materials with high thermal conductivity, so that the frame structure will not lose the body bearing function due to the sudden decrease in rigidity due to excessive temperature during thermal runaway.

[0039] The frame cross beam 5 and the left main longitudinal beam 6 and the right main longitudinal beam 7 may be connected in any manner, and may be bonded, welded, or mechanically connected, as long as sealing is achieved after the connection.

[0040] The frame cross beam 5, the left main longitudinal beam 6, the right main longitudinal beam 7, the front cross beam 8 and the rear cross beam 9 are all extruded by high-strength alloy materials. Specifically, the frame cross beam 5, the left main longitudinal beam 6, the right main longitudinal beam 7, the front cross beam 8 and the rear cross beam 9 are all made of alloy materials with a tensile strength of not less than 350Mpa, a specified non-proportional elongation strength Rp0.2 of not less than 310Mpa, an elongation after fracture of not less than 8%, a material density of not more than 2.9g / cm3, and a thermal conductivity of not less than 150W / mK.

[0041] In this embodiment, the connection between the frame beam 5 and the left main longitudinal beam 6, the right main longitudinal beam 7, the connection between the bottom plate module 1 and the frame beam 5, and the connection between the cover plate 2 and the frame beam 5 are all provided with sealing structures. Optionally, the sealing structure of this embodiment adopts a sealing ring. In addition, the sealing method of the cavity 4 of this embodiment can also adopt the bottom plate module 1 and the frame beams 5 on both sides thereof as an integral part. After the battery 3 is placed in the cavity 4, the connection between the cover plate 2 and the frame beams 5 on both sides is connected in a sealed form. In addition, the heat insulation structure of the cavity 4 of this embodiment adopts a heat insulation pad, and the heat insulation pad is arranged and laid on the cavity wall of the cavity 4.

[0042] Furthermore, the left main longitudinal beam 6 and the front cross beam 8, the front cross beam 8 and the right main longitudinal beam 7, the right main longitudinal beam 7 and the rear cross beam 9, and the rear cross beam 9 and the left longitudinal beam are connected through a connecting joint 10, and the connecting joint 10 includes a joint body 1001, a first plug-in portion 1002, a second plug-in portion 1003 and a plurality of connecting portions 1004, the first plug-in portion 1002 and the second plug-in portion 1003 are connected to the joint body 1001 and are both provided with jacks, the first plug-in portion 1002 and the second plug-in portion 1003 are used for frame connection, and the connecting portion 1004 includes a connecting plate 10041, and one end of the connecting plate 10041 is connected to the joint body 1001. The frame of this embodiment is connected by four connecting joints 10, namely 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 left main longitudinal beam 6 is inserted into the socket of the first plug-in portion 1002 of the first connecting joint 10, the first end of the front cross beam 8 is inserted into the socket of the second plug-in portion 1003 of the first connecting joint 10, the second end of the front cross beam 8 is inserted into the socket of the first plug-in portion 1002 of the second connecting joint 10, and the right main longitudinal beam The first end of the right main longitudinal beam 7 is inserted into the insertion hole of the second insertion part 1003 of the second connection joint 10, the second end of the right main longitudinal beam 7 is inserted into the insertion hole of the first insertion part 1002 of the third connection joint 10, the first end of the rear cross beam 9 is inserted into the insertion hole of the second insertion part 1003 of the third connection joint 10, the second end of the rear cross beam 9 is inserted into the insertion hole of the first insertion part 1002 of the fourth connection joint 10, and the second end of the left longitudinal beam is inserted into the insertion hole of the second insertion part 1003 of the fourth connection joint 10. In addition, the connection part 1004 of this embodiment has two parallel and spaced connection plates 10041, and the connection plates 10041 can be connected to other parts of the aircraft body or the arm 14 by riveting, welding, etc.

[0043] The connection joint 10 is formed by casting or machining a high-strength alloy material, and the connection joint 10 is an alloy material with a tensile strength of not less than 440 MPa, an elongation after fracture of not less than 7%, and a material density of not more than 2.9 g / cm3.

[0044] Optionally, the frame includes a left main longitudinal beam 6, a right main longitudinal beam 7, a front cross beam 8 and a rear cross beam 9, which are connected end to end to form a ring, and the left main longitudinal beam 6, the right main longitudinal beam 7, the front cross beam 8 and the rear cross beam 9 are all hollow tubes. The cross sections of the left main longitudinal beam 6, the right main longitudinal beam 7, the front cross beam 8 and the rear cross beam 9 of this embodiment are all rectangular, which facilitates the connection of the bottom plate module 1, the cover plate 2 and the frame cross beam 5.

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

[0046] The left main longitudinal beam 6, the right main longitudinal beam 7, the front cross beam 8, the rear cross beam 9, the connecting joint 10, the frame cross beam 5, the bottom plate module 1, and the cover plate 2 are all made of high-strength aluminum alloy materials, so that after the aircraft battery 3 thermal runaway, there will be no structural thermal deformation causing the fuselage structure to lose its structural bearing capacity.

[0047] Embodiment 3 The difference between this embodiment and the second embodiment is that, based on the third embodiment, this embodiment further illustrates the base plate module 1 .

[0048] In this embodiment, the base plate module 1 is provided with a heat dissipation structure, which helps the aircraft and the battery 3 to dissipate heat, and effectively realizes heat dissipation and heat insulation of the aircraft. Specifically, a coolant channel 101 is provided on the base plate module 1, and at least two coolant inlet and outlet nozzles 11 are connected to the base plate module 1. The coolant channel 101 is connected to the coolant inlet and outlet nozzles 11 to form a heat dissipation structure. The coolant enters the coolant channel 101 through one of the coolant inlet and outlet nozzles 11, and then flows out from the other coolant inlet and outlet nozzles 11 to cool the battery 3 and the cavity 4 placed on the base plate module 1. The base plate module 1 includes a first base plate 103 and a second base plate 104 connected to each other. The first base plate 103 is provided with a protruding structure, and a coolant channel 101 is formed between the protruding structure and the second base plate 104.

[0049] The connection between the first base plate 1 and the second base plate 1 and the coolant inlet and outlet nozzle 11 and the base plate module 1 is not limited to mechanical connection or welding. When the fuselage module forms the main body of the aircraft, the base plate module 1 is placed on the outside, which can increase the heat dissipation rate of the battery 3 during charging and discharging. In this embodiment, the fuselage module serves as the bottom of the aircraft body, so the base plate module 1 is located on the bottom side of the aircraft. The cover plate 2 of this embodiment is provided with a through hole that communicates with the cavity 4, one end of the coolant inlet and outlet nozzle 11 is connected to the base plate module 1, and the other end of the coolant inlet and outlet nozzle 11 extends from the through hole.

[0050] Furthermore, an explosion-proof valve 12 is provided in the cavity 4. The explosion-proof valve 12 is connected to the base plate module 1, and an explosion-proof port 102 is provided on the base plate module 1. The explosion-proof valve 12 is connected to the explosion-proof port 102. The base plate module 1, two frame beams 5, the frame and the cover plate 2 form an independent sealed cavity, which can achieve IP68 grade. The battery 3 is placed in the sealed cavity 4. The explosion-proof valve 12 can control the pressure in the cavity 4, prevent thermal runaway, explosion and combustion, etc., and improve safety.

[0051] The other structures of this embodiment are the same as those of the second embodiment and will not be described again here.

[0052] Embodiment 4 like Fig. 9As shown, an embodiment of the present invention provides an aircraft, an aircraft body and an arm 14, the arm 14 is connected to the aircraft body, the aircraft body includes one or more fuselage modules described in embodiment 1, embodiment 2 or embodiment 3, and the arm 14 is connected to the fuselage module. The arm 14 is used to support the power device, one end of the arm 14 is connected to the rotor, and the other end of the arm 14 is connected to the frame of the fuselage module. The arm 14 of this embodiment is connected to the connecting portion 1004 of the connecting joint 1001.

[0053] In addition, the aircraft of this embodiment further includes one or more fuselage modules 13, and the fuselage modules 13 are connected with the fuselage modules to form the aircraft body. The fuselage modules 13 of this embodiment include brackets, and the frame of the fuselage module is connected with the frame of the adjacent fuselage module 13. The aircraft body of this embodiment includes a fuselage module and a plurality of fuselage modules 13, and the fuselage module and the fuselage module 13 are connected to form an aircraft body with a cabin, and the fuselage module serves as the bottom of the aircraft body. The bracket of the fuselage module 13 is connected with the frame of the fuselage module by welding, riveting, etc. A skin is provided on the bracket of the fuselage module 13 of this embodiment. In this embodiment, the aircraft body is formed by connecting a fuselage module and a fuselage module 13.

[0054] The aircraft of this embodiment is connected with the fuselage module through the fuselage module 13 to form the aircraft body, realizing modular assembly. When the life of the aircraft battery 3 ends, the fuselage module can be quickly replaced to realize the replacement of the new aircraft body and the battery 3, or the battery 3 can be quickly replaced during operation to realize efficient operation, providing a very efficient design for later maintenance, after-sales and operation.

[0055] In summary, the embodiment of the present invention provides an aviation fuselage module, which integrates the fuselage and the battery 3 by arranging the battery 3 in the cavity 4 formed by the frame, the bottom plate module 1 and the cover plate 2. The frame, the cover plate 2 and the bottom plate module 1 are both the fuselage bearing structure and the battery 3 bearing structure, which is conducive to reducing the overall weight of the aircraft and achieving lightweight. At the same time, it can not only provide higher fuselage rigidity and strength for the aircraft, but also provide high-strength and high-rigidity protection for the aircraft battery 3. The battery 3 is integrated with the fuselage, which is more conducive to the heat dissipation of the battery 3 and solves the important safety problem of thermal runaway of the aircraft. The cavity 4 of the fuselage module is provided with an explosion-proof valve 12 to achieve thermal runaway isolation protection. In addition, the fuselage module adopts an alloy material with a tensile strength of not less than 350Mpa, a non-proportional extension strength Rp0.2 of not less than 310Mpa, an elongation after fracture of not less than 8%, a material density of not more than 2.9g / cm3, and a thermal conductivity of not less than 150W / mK. The sealed combined cavity structure ensures that after the aircraft battery 3 is thermally runaway, there will be no structural thermal deformation, which will cause the fuselage structure to lose its structural bearing capacity. The aircraft of the embodiment of the present invention forms an aircraft body by connecting a number of fuselage modules 13 with the fuselage module to achieve modular assembly. When the life of the aircraft battery 3 ends, the fuselage module can be quickly replaced to achieve a new aircraft body and battery 3 replacement, or the battery 3 can be quickly replaced during operation to achieve efficient operation of the fuselage structure, providing a very efficient design for later maintenance, after-sales, and operation.

[0056] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and substitutions can be made without departing from the technical principles of the present invention. These improvements and substitutions should also be regarded as the scope of protection of the present invention.

Claims

1. An aircraft fuselage module, 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 a part of the main body of the aircraft, and comprises a frame, a base plate module (1), a cover plate (2) and a battery (3); the base plate module (1) and the cover plate (2) are located on the inner side of the frame, and the base plate module (1), the cover plate (2) and the frame are connected to form a cavity (4); the cavity (4) is a sealed cavity; the battery (3) is arranged in the cavity (4); and the battery (3) is used to supply power to the aircraft.

2. The aircraft fuselage module according to claim 1, characterized in that: It also comprises a plurality of frame cross beams (5), the base plate module (1) and the cover plate (2) are arranged in a plurality, the frame cross beam (5) is located on the inner side of the frame, the two ends of the frame cross beam (5) are respectively connected to the two opposite sides of the frame, the two sides of one base plate module (1) are respectively connected to the two frame cross beams (5), and the two sides of one cover plate (2) are respectively connected to the two frame cross beams (5), so as to form a plurality of cavities (4), each of which is provided with a battery (3).

3. The aircraft fuselage module according to claim 2, characterized in that: The frame comprises a left main longitudinal beam (6), a right main longitudinal beam (7), a front cross beam (8) and a rear cross beam (9); the left main longitudinal beam (6), the front cross beam (8), the right main longitudinal beam (7) and the rear cross beam (9) are connected end to end to form a ring; the left main longitudinal beam (6) is opposite to the right main longitudinal beam (7), the front cross beam (8) is opposite to the rear cross beam (9), and the two ends of the frame cross beam (5) are respectively connected to the left main longitudinal beam (6) and the right main longitudinal beam (7).

4. The aircraft fuselage module according to claim 3, characterized in that: The frame cross beam (5), the left main longitudinal beam (6), the right main longitudinal beam (7), the front cross beam (8) and the rear cross beam (9) are all formed by extrusion of a high-strength alloy material.

5. The aircraft fuselage module according to claim 1, characterized in that: The frame comprises a left main longitudinal beam (6), a right main longitudinal beam (7), a front cross beam (8) and a rear cross beam (9); the left main longitudinal beam (6), the front cross beam (8), the right main longitudinal beam (7) and the rear cross beam (9) are connected end to end to form a ring; the left main longitudinal beam (6) is opposite to the right main longitudinal beam (7); the front cross beam (8) is opposite to the rear cross beam (9); the left main longitudinal beam (6) and the front cross beam (8), the front cross beam (8) and the right main longitudinal beam (7), the right main longitudinal beam (7) and the rear cross beam (9), and the rear cross beam (9) and the left longitudinal beam are connected by connecting joints. The connecting joint (10) comprises a joint body (1001), a first plug-in portion (1002), a second plug-in portion (1003) and a plurality of connecting portions (1004); the first plug-in portion (1002) and the second plug-in portion (1003) are connected to the joint body (1001) and are both provided with plug holes; the first plug-in portion (1002) and the second plug-in portion (1003) are used for connecting to the frame; the connecting portion (1004) comprises a connecting plate (10041); one end of the connecting plate (10041) is connected to the joint body (1001).

6. The aircraft fuselage module according to claim 5, characterized in that The connection joint (10) is formed by casting or machining using a high-strength alloy material.

7. The aircraft fuselage module according to claim 1, characterized in that: The base plate module (1) is provided with a heat dissipation structure.

8. The aircraft fuselage module according to claim 5, characterized in that: The base plate module (1) is provided with a cooling liquid channel (101), the base plate module (1) is connected to at least two cooling liquid inlet and outlet nozzles (11), and the cooling liquid channel (101) is connected to the cooling liquid inlet and outlet nozzles (11) to form the heat dissipation structure.

9. The aircraft fuselage module according to claim 1, characterized in that: An explosion-proof valve (12) is provided in the cavity (4).

10. The aircraft fuselage module according to claim 1, characterized in that: The frame comprises a left main longitudinal beam (6), a right main longitudinal beam (7), a front cross beam (8) and a rear cross beam (9); the left main longitudinal beam (6), the front cross beam (8), the right main longitudinal beam (7) and the rear cross beam (9) are connected end to end to form a ring; the left main longitudinal beam (6), the right main longitudinal beam (7), the front cross beam (8) and the rear cross beam (9) are all hollow tubes.

11. The aircraft fuselage module according to claim 2, characterized in that: The frame cross beam (5) is a hollow tube, and the inner wall of the frame cross beam (5) is provided with reinforcing ribs (501).

12. An aircraft, characterized in that: The invention comprises an aircraft body and an arm (14), wherein the aircraft body comprises one or more fuselage modules according to any one of claims 1 to 11, and the arm (14) is connected to the fuselage module.

13. The aircraft according to claim 12, characterized in that It also comprises one or more fuselage modules, wherein the fuselage module (13) is connected with the fuselage module to form the aircraft body.

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