Trussed beam type modular fuselage of unmanned helicopter

Abstract

The utility model relates to a truss type modular fuselage of an unmanned helicopter, belongs to the technical field of unmanned helicopters, and solves the problems that a fuselage in the prior art adopts welding connection, the welding quality is unstable, the welding positioning precision is low, the fuselage structure is complicated, the fuselage cannot be detached and the maintenance cost is high. The device comprises a front fuselage truss module and a rear fuselage truss module which are connected through a fixing piece, and the front fuselage truss module and the rear fuselage truss module adopt I-shaped steel structures. The modularized part structures are assembled into the fuselage assembly through the fixing pieces, the connecting and positioning precision is high during assembly, the stability of the whole fuselage is high after assembly, disassembly is convenient during maintenance, parts are convenient to maintain and replace, and rapid mounting, mounting and disassembly of the fuselage are achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned helicopters, and particularly to a girder-type modular fuselage for an unmanned helicopter. Background Art

[0002] The fuselages of existing unmanned helicopters mainly use pipes and welding technology to construct the fuselages of unmanned aerial vehicles.

[0003] Modern welding technology is affected by various factors such as welding parameters, material status, and environmental conditions. It is difficult to ensure the consistency of welding quality, and it is difficult to ensure the process stability of the welded fuselage. During the flight of an unmanned helicopter, the vibrations generated by the engine and the rotor are likely to cause cracks in the fuselage welds, threatening the flight safety of the unmanned helicopter; after the pipes are welded together, the fuselage structure is complex, the connection and positioning accuracy is low, and it is not detachable. Once a component on the unmanned helicopter needs to be repaired or replaced, the disassembly difficulty is great, increasing the difficulty and cost of maintenance. Summary of the Utility Model

[0004] In view of the above analysis, the embodiments of the utility model aim to provide a girder-type modular fuselage for an unmanned helicopter, which uses fixing parts to fixedly connect the modularized structures, and solves the problems of unstable welding technology, unstable fuselage structure, and high maintenance and replacement costs due to the non-detachability of the overall welded fuselage in the prior art.

[0005] The purpose of the utility model is mainly achieved through the following technical solutions:

[0006] A girder-type modular fuselage for an unmanned helicopter, which includes a front fuselage truss module and a rear fuselage truss module connected by fixing parts; the front fuselage truss module and the rear fuselage truss module adopt I-beam structures;

[0007] The front fuselage truss module includes a first front fuselage cross beam, a left front fuselage cross beam and a right front fuselage cross beam with their front ends fixed to the left and right ends of the first front fuselage cross beam, and a second front fuselage cross beam arranged between the left front fuselage cross beam and the right front fuselage cross beam;

[0008] The rear fuselage truss module includes a left rear fuselage longitudinal beam with its front end fixed to the left front fuselage cross beam, a right rear fuselage longitudinal beam with its front end fixed to the right front fuselage cross beam, a first rear fuselage cross beam, a second rear fuselage cross beam, a third rear fuselage cross beam, a fourth rear fuselage cross beam and a fifth rear fuselage cross beam arranged between the left rear fuselage longitudinal beam and the right rear fuselage longitudinal beam from front to back; the fifth rear fuselage cross beam is arranged at the rear ends of the left rear fuselage longitudinal beam and the right rear fuselage longitudinal beam.

[0009] Furthermore, the front fuselage first cross beam, the front fuselage second cross beam, the rear fuselage first cross beam, the rear fuselage second cross beam, the rear fuselage third cross beam, and the rear fuselage fifth cross beam are all rectangular frames surrounded by I-beams.

[0010] Furthermore, the rear fuselage truss module further includes a first V-shaped reinforcement structure, a second V-shaped reinforcement structure, a third V-shaped reinforcement structure, an inverted V-shaped reinforcement structure, and a beam reinforcement structure;

[0011] The first V-shaped reinforcement structure is disposed within the rectangular frame of the rear fuselage first cross beam; the second V-shaped reinforcement structure is disposed within the rectangular frame of the rear fuselage second cross beam; the third V-shaped reinforcement structure is disposed within the rectangular frame of the rear fuselage fifth cross beam; the inverted V-shaped reinforcement structure is disposed within the rectangular frame of the rear fuselage third cross beam; the beam reinforcement structure is symmetrically disposed on the left longitudinal beam of the rear fuselage and the right longitudinal beam of the rear fuselage.

[0012] Furthermore, the fuselage further includes a drive system connection module, a landing gear connection module, a support connection module, a tail support module, and a payload mounting module.

[0013] Furthermore, the drive system connection module includes two oppositely disposed reducer housing connectors and belt supports;

[0014] The reducer housing connector is a V-shaped I-beam, and its two ends are respectively fixed to the rear fuselage second cross beam and the rear fuselage third cross beam, and the bent end of the reducer housing connector is fixed to the left longitudinal beam of the rear fuselage or the right longitudinal beam of the rear fuselage;

[0015] The belt support is fixed to the first V-shaped reinforcement structure.

[0016] Furthermore, the landing gear connection module includes a plurality of landing gear connectors symmetrically fixed to the lower end of the rear fuselage truss module; the landing gear connector includes:

[0017] A landing gear connection upper sleeve, which is a semi-circular ring structure; the landing gear connection upper sleeve is fixed to the lower end surface of the left longitudinal beam of the rear fuselage or the right longitudinal beam of the rear fuselage;

[0018] A landing gear connection lower sleeve, which is a semi-circular ring structure, the landing gear connection lower sleeve is fixed to the landing gear connection upper sleeve, and the semi-circular ring structure of the landing gear connection upper sleeve and the semi-circular ring structure of the landing gear connection lower sleeve enclose a connection hole.

[0019] Furthermore, the landing gear connection module further includes a landing gear connection damping rubber, which is disposed in the connection hole.

[0020] Further, the support connection module includes a plurality of fuel tank supports, buffer landing gear connectors, and side mounting connectors symmetrically arranged on the left longitudinal beam of the rear fuselage and the right longitudinal beam of the rear fuselage.

[0021] Further, the tail support module includes a tail intermediate support fixed to the fifth cross beam of the rear fuselage and two tail side supports; the two tail side supports are symmetrically arranged on the left and right sides of the tail intermediate support;

[0022] The tail intermediate support is a Y-shaped round tube; the tail intermediate support includes a lower connection end and two fixed ends arranged on the connection end; a first bushing is welded on the connection end and then fixed to the middle of the fifth cross beam of the rear fuselage; a flat plate for fixing the GPS is arranged on one fixed end, and a second bushing is welded on the other fixed end;

[0023] The lower end of the tail side support is welded with a third bushing and fixed to the fifth cross beam of the rear fuselage through a fixing member, and the upper end of the tail side support is welded with a fourth bushing.

[0024] Further, the load mounting module includes a load support cross beam and a load support member;

[0025] Both ends of the load support cross beam are respectively fixed on the left longitudinal beam of the rear fuselage and the right longitudinal beam of the rear fuselage;

[0026] The load support member is fixed on the second cross beam of the rear fuselage.

[0027] Compared with the prior art, the present utility model can at least achieve one of the following beneficial effects:

[0028] (1) The girder-type modular fuselage of the unmanned helicopter of the present utility model includes a front fuselage truss module and a rear fuselage truss module fixedly connected by fixing members. Each module is fixedly connected by fixing members. During assembly, the connection and positioning accuracy is high, avoiding the crash accidents of unmanned helicopters caused by unstable welding quality of conventional welded fuselages, and increasing the reliability of the unmanned helicopter fuselage; after assembly, the overall fuselage has high stability, is convenient to disassemble during maintenance, is convenient for maintenance and replacement of components, and realizes the rapid mounting and disassembly of the fuselage.

[0029] (2) The girder-type modular fuselage of the unmanned helicopter of the present utility model divides the unmanned helicopter fuselage into multiple modules, which can be replaced as a whole module, effectively reducing the complexity of the unmanned helicopter fuselage maintenance.

[0030] (3) The girder-type modular fuselage of the unmanned helicopter of the present utility model mainly uses I-beams as the fuselage material, the overall weight of the fuselage is strong, and the strength and stiffness of the unmanned helicopter fuselage are enhanced.

[0031] In the present utility model, the above-mentioned technical solutions can also be combined with each other to achieve more preferred combined solutions. Other features and advantages of the present utility model will be described in the following content. Moreover, some advantages can be made obvious from the description or understood by implementing the present utility model. The objectives and other advantages of the present utility model can be achieved and obtained from the content specifically pointed out in the text and the drawings. Description of the Drawings

[0032] The drawings are only for the purpose of showing specific embodiments and are not considered as limitations to the present utility model. Throughout the drawings, the same reference signs represent the same components.

[0033] Figure 1 Structural schematic diagram of the truss modular fuselage of an unmanned helicopter for a specific embodiment;

[0034] Figure 2 Structural schematic diagram of the front fuselage truss module for a specific embodiment;

[0035] Figure 3 Structural schematic diagram of the rear fuselage truss module for a specific embodiment;

[0036] Figure 4 Structural schematic diagram of the reducer housing connecting part in the transmission system connection module for a specific embodiment;

[0037] Figure 5 Structural schematic diagram of the belt support part in the transmission system connection module for a specific embodiment;

[0038] Figure 6 Structural schematic diagram of the landing gear connection module for a specific embodiment;

[0039] Figure 7 Structural schematic diagram of the support connection module for a specific embodiment;

[0040] Figure 8 Structural schematic diagram of the tail support module for a specific embodiment;

[0041] Figure 9 Structural schematic diagram of the load support cross beam in the load installation module for a specific embodiment;

[0042] Figure 10 Structural schematic diagram of the load support part in the load installation module for a specific embodiment.

[0043] Reference Signs:

[0044] 1 - Front fuselage truss module; 2 - Rear fuselage truss module; 3 - Transmission system connection module; 4 - Landing gear connection module; 5 - Support connection module; 6 - Tail support module; 7 - Payload installation module; 11 - First cross beam of the front fuselage; 12 - Second cross beam of the front fuselage; 13 - Left cross beam of the front fuselage; 14 - Right cross beam of the front fuselage; 21 - First cross beam of the rear fuselage; 22 - Second cross beam of the rear fuselage; 23 - Third cross beam of the rear fuselage; 24 - Fourth cross beam of the rear fuselage; 25 - Fifth cross beam of the rear fuselage; 26 - Left longitudinal beam of the rear fuselage; 27 - Right longitudinal beam of the rear fuselage; 28 - First V-shaped strengthening structure; 29 - Second V-shaped strengthening structure; 210 - Third V-shaped strengthening structure; 211 - Inverted V-shaped strengthening structure; 212 - Beam strengthening structure; 31 - Reducer housing connection; 32 - Belt support; 41 - Upper sleeve for landing gear connection; 42 - Lower sleeve for landing gear connection; 43 - Shock-absorbing rubber for landing gear connection; 51 - First support for fuel tank; 52 - Second support for fuel tank; 53 - Third support for fuel tank; 54 - Fourth support for fuel tank; 55 - First connecting piece for side mounting; 56 - Second connecting piece for side mounting; 57 - First connecting piece for buffer landing gear; 58 - Second connecting piece for buffer landing gear; 61 - Side support for tail; 611 - Third bushing; 612 - Fourth bushing; 62 - Intermediate support for tail; 621 - First bushing; 622 - Flat plate; 623 - Second bushing; 71 - Payload support cross beam; 72 - Payload support. Detailed implementation mode

[0045] The following combines the drawings to specifically describe the preferred embodiments of the present invention. Among them, the drawings form a part of the present invention and are used together with the embodiments of the present invention to explain the principle of the present invention, and are not used to limit the scope of the present invention.

[0046] A specific embodiment of the present invention, as Figures 1 to 3 shown, discloses a girder-type modular fuselage for an unmanned helicopter, including a front fuselage truss module 1 and a rear fuselage truss module 2,

[0047] The rear end of the front fuselage truss module 1 is fixedly connected to the front end of the rear fuselage truss module 2 by bolts; both the front fuselage truss module 1 and the rear fuselage truss module 2 are made of I-beam materials.

[0048] The front fuselage truss module 1 and the rear fuselage truss module 2 are matched through a groove structure and fixedly connected by bolts to construct the fuselage skeleton of the unmanned helicopter, which is light in overall weight and high in strength and stiffness. Reinforcing ribs are provided at the bolt fixing points of the front fuselage truss module 1 and the rear fuselage truss module 2 to ensure and strengthen the overall stiffness.

[0049] The front fuselage truss module 1 includes a front fuselage first cross beam 11, a front fuselage second cross beam 12, a left front fuselage cross beam 13, and a right front fuselage cross beam 14; both the front fuselage first cross beam 11 and the front fuselage second cross beam 12 are rectangular frames formed by I-beams; both ends of the front fuselage first cross beam 11 are fixed to the front end of the left front fuselage cross beam 13 and the end face of the right front fuselage cross beam 14 by bolts; the left and right ends of the front fuselage second cross beam 12 are fixed to the middle of the left front fuselage cross beam 13 and the middle of the right front fuselage cross beam 14. The function of the front fuselage second cross beam 12 is to support the middle of the left front fuselage cross beam 13 and the right front fuselage cross beam 14, so that the front fuselage truss has sufficient lateral stiffness.

[0050] The rear fuselage truss module 2 includes:

[0051] A left rear fuselage longitudinal beam 26, the front end of which is fixed to the rear end of the left front fuselage cross beam 13 by bolts;

[0052] A right rear fuselage longitudinal beam 27, the front end of which is fixed to the rear end of the right front fuselage cross beam 14 by bolts; the left rear fuselage longitudinal beam 26 and the right rear fuselage longitudinal beam 27 are symmetrical parts, both of which are multiple rectangular frames formed by channel beams, and beam strengthening structures 212 are arranged inside the rectangular frames to strengthen the longitudinal stiffness of the rear fuselage; a plurality of fixing holes are arranged on the left rear fuselage longitudinal beam 26 and the right rear fuselage longitudinal beam 27, which are the installation positions of the drive system connection module 3, the landing gear connection structure, the support connection module 5, the tail wing support module 6, and the load installation module 7, and stiffeners are arranged at the positions of the fixing holes;

[0053] And a rear fuselage first cross beam 21, a rear fuselage second cross beam 22, a rear fuselage third cross beam 23, a rear fuselage fourth cross beam 24, and a rear fuselage fifth cross beam 25 are sequentially arranged between the left rear fuselage longitudinal beam 26 and the right rear fuselage longitudinal beam 27 from front to back.

[0054] Among them, the rear fuselage first cross beam 21, the rear fuselage second cross beam 22, the rear fuselage third cross beam 23, and the rear fuselage fifth cross beam 25 are all rectangular frames formed by I-beams, and reinforcing rib plates are arranged inside the I-beams; a first V-shaped strengthening structure 28 is arranged inside the rectangular frame of the rear fuselage first cross beam 21, and the function of the rear fuselage first cross beam 21 is to improve the front lateral stiffness of the rear fuselage truss module 2; a second V-shaped strengthening structure 29 is arranged inside the rectangular frame of the rear fuselage second cross beam 22, and an inverted V-shaped strengthening structure 211 is arranged inside the rectangular frame of the rear fuselage third cross beam 23; the cross sections of the rear fuselage second cross beam 22 and the rear fuselage third cross beam 23 are used to improve the middle lateral stiffness of the fuselage truss module; a third V-shaped strengthening structure 210 is arranged inside the rectangular frame of the rear fuselage fifth cross beam 25, and the rear fuselage fifth cross beam 25 is used to improve the rear lateral stiffness of the rear fuselage truss module 2.

[0055] The No. 4 cross beam 24 of the rear fuselage is an I-beam, with its left end fixed to the left longitudinal beam 26 of the rear fuselage through a fixing part, and its right end fixed to the right longitudinal beam 27 of the rear fuselage through a fixing part. The function of the No. 4 cross beam 24 of the rear fuselage is to support the lateral stiffness of the lower part of the fuselage.

[0056] As Figure 4 and Figure 5 shown, the girder-type modular fuselage of the unmanned helicopter further includes a drive system connection module 3. The drive system connection module 3 is fitted with the rear fuselage truss module 2 through a slot structure and is fixed to the rear fuselage truss module 2 by bolts.

[0057] The drive system connection module 3 includes a reducer housing connecting part 31 and a belt support part 32, which are used to provide a structure for installing the drive system and fixing the reducer pulley. The reducer housing connecting part 31 is of I-beam structure and in a V shape. The two ends and the bent part of the reducer housing connecting part 31 are successively fixed to the No. 2 cross beam 22 of the rear fuselage, the No. 3 cross beam 23 of the rear fuselage and the left longitudinal beam 26 of the rear fuselage or the right longitudinal beam 27 of the rear fuselage. The reducer housing connecting part 31 is used to install the drive system of the unmanned helicopter; the belt support part 32 is of a circular ring structure and is used to fix the reducer pulley.

[0058] As Figure 6 shown, the girder-type modular fuselage of the unmanned helicopter further includes a landing gear connection module 4. The landing gear connection module 4 includes a plurality of landing gear connecting parts symmetrically fixed to the lower end of the rear fuselage truss module 2; the landing gear connecting part includes a landing gear connecting upper sleeve 41, a landing gear connecting lower sleeve 42 and a landing gear connecting damping rubber 43. The semi-circular ring structure landing gear connecting upper sleeve 41 and the landing gear connecting lower sleeve 42 enclose a connection hole, and the landing gear connecting damping rubber 43 is fixed in the connection hole. The landing gear is arranged in the connection hole, and the landing gear connecting damping rubber 43 plays a role in damping and buffering.

[0059] The number of the landing gear connecting parts can be set to multiple numbers such as 4, 6 or 8 according to actual use needs. The multiple landing gear connecting parts are symmetrically arranged on the lower end surfaces of the left longitudinal beam 26 of the rear fuselage and the right longitudinal beam 27 of the rear fuselage.

[0060] As Figure 1 and Figure 7 shown, the girder-type modular fuselage of the unmanned helicopter further includes the support connection module 5, which includes: a plurality of fuel tank support parts, a plurality of buffer-type landing gear connecting parts and a plurality of side mounting connecting parts;

[0061] The plurality of fuel tank support parts are symmetrically arranged on the left longitudinal beam 26 of the rear fuselage and the right longitudinal beam 27 of the rear fuselage; the fuel tank support parts are used to fix the fuel tank of the unmanned helicopter. As Figure 7As shown in the figure, taking the left longitudinal beam 26 of the rear fuselage as an example, there are a first fuel tank support member 51, a second fuel tank support member 52, a third fuel tank support member 53 and a fourth fuel tank support member 54 provided on the left longitudinal beam 26 of the rear fuselage; the first fuel tank support member 51 and the fourth fuel tank support member 54 are of strip structures, with reinforcing ribs provided below, and they are fixed in the groove under the rear fuselage longitudinal beam by bolts, and their function is to fix the fuel tank of the unmanned helicopter; the second fuel tank support member 52 and the third fuel tank support member 53 include a strip support structure and triangular reinforcing ribs provided under the strip support member, and relief holes are opened on the reinforcing ribs, and the second fuel tank support member 52 and the third fuel tank support member 53 are fixed in the groove of the rear fuselage longitudinal beam by bolts.

[0062] A plurality of the buffer type landing gear connectors are fixed on the left longitudinal beam 26 of the rear fuselage and the right longitudinal beam 27 of the rear fuselage according to the corresponding relationship with the landing gear connectors; as Figure 1 shown in the figure, taking the left longitudinal beam 26 of the rear fuselage as an example, 2 landing gear connectors are arranged at the front and rear of the left longitudinal beam 26 of the rear fuselage, and according to the corresponding relationship, a first buffer type landing gear connector 57 and a second buffer type landing gear connector 58 are arranged on the left longitudinal beam 26 of the rear fuselage.

[0063] A plurality of side mounting connectors are symmetrically arranged on the left longitudinal beam 26 of the rear fuselage and the right longitudinal beam 27 of the rear fuselage. The side mounting connectors are of long strip cantilever beam structures, and the cross section is a ring. The side mounting connectors are fixed in the groove above the rear fuselage longitudinal beam by bolts, and their function is to connect the upper ends of the side mounts; as Figure 7 shown in the figure, taking the right longitudinal beam 27 of the rear fuselage as an example, a first side mounting connector 55 and a second side mounting connector 56 are arranged on the right longitudinal beam 27 of the rear fuselage, and at the corresponding positions, side mounting connectors are also arranged on the left longitudinal beam 26 of the rear fuselage. The positions of the first side mounting connector 55 and the second side mounting connector 56 are respectively arranged corresponding to the second cross beam 22 of the rear fuselage and the third cross beam 23 of the rear fuselage.

[0064] As Figure 8 shown in the figure, the tail wing support module 6 includes a middle tail wing support member 62 fixed to the fifth cross beam 25 of the rear fuselage and two side tail wing support members 61; the two side tail wing support members 61 are symmetrically arranged on the left and right sides of the middle tail wing support member 62;

[0065] The middle support member 62 of the tail fin is a Y-shaped hollow circular tube; the middle support member 62 of the tail fin includes a lower connection end and two fixed ends provided on the connection end; a first bushing 621 is welded on the connection end and then fixed to the middle part of the fifth cross beam 25 of the rear fuselage; a flat plate 622 for fixing the GPS is provided on one of the fixed ends, and a second bushing 623 is welded on the other fixed end, and the second bushing 623 is used to connect the tail fin skin;

[0066] The lower end of the side support member 61 of the tail fin is welded with a third bushing 611 and then fixed to the fifth cross beam 25 of the rear fuselage through a fixing member. The upper end of the side support member 61 of the tail fin is welded with a fourth bushing 612, and the upper end of the left side support member of the tail fin is used to connect the tail fin skin.

[0067] As Figure 9 and Figure 10 shown, the load mounting module 7 is used to mount a load. The load mounting module 7 is fixed to the middle part of the rear fuselage truss module 2 through a fixing member. The load mounting module 7 includes a load support cross beam 71 and a load support member 72;

[0068] The load support cross beam 71 is an I-beam, and its two ends are respectively fixed to the left longitudinal beam 26 of the rear fuselage and the right longitudinal beam 27 of the rear fuselage. Fixed holes are provided on the load support cross beam 71, and stiffeners are provided at the positions of the fixed holes;

[0069] The load support member 72 is fixed on the second cross beam 22 of the rear fuselage.

[0070] For the girder-type lightweight modular fuselage of the unmanned helicopter in this embodiment, a steel girder fuselage assembly fixed by bolt fasteners is used. The steel girder fuselage assembly has a lightweight modular design, and it includes a front fuselage truss module 1, a rear fuselage truss module 2, a drive system connection module 3, a landing gear connection module 4, a support connection module 5, a tail fin support module 6, and a load mounting module 7. The fuselage assembly has a simple structure, is convenient to disassemble, has good interchangeability, effectively reduces the complexity of the maintenance of the unmanned helicopter fuselage, avoids the crash accidents of the unmanned helicopter caused by the unstable welding quality of the conventional welded fuselage, and increases the reliability of the unmanned helicopter fuselage.

[0071] The above are only the preferred specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A girder-type modular fuselage for an unmanned helicopter, characterized in that It includes a front fuselage truss module (1) and a rear fuselage truss module (2) connected by a fixing member; the front fuselage truss module (1) and the rear fuselage truss module (2) adopt an I-beam structure; The front fuselage truss module (1) includes a front fuselage first cross beam (11), a front fuselage left cross beam (13) and a front fuselage right cross beam (14) with their front ends fixed to both ends of the front fuselage first cross beam (11), and a front fuselage second cross beam (12) arranged between the front fuselage left cross beam (13) and the front fuselage right cross beam (14); The rear fuselage truss module (2) includes a rear fuselage left longitudinal beam (26) with its front end fixed to the front fuselage left cross beam (13), a rear fuselage right longitudinal beam (27) with its front end fixed to the front fuselage right cross beam (14), a rear fuselage first cross beam (21), a rear fuselage second cross beam (22), a rear fuselage third cross beam (23), a rear fuselage fourth cross beam (24) and a rear fuselage fifth cross beam (25) arranged in sequence from front to back between the rear fuselage left longitudinal beam (26) and the rear fuselage right longitudinal beam (27).

2. The girder-type modular fuselage of the unmanned helicopter according to claim 1, characterized in that The front fuselage first cross beam (11), the front fuselage second cross beam (12), the rear fuselage first cross beam (21), the rear fuselage second cross beam (22), the rear fuselage third cross beam (23) and the rear fuselage fifth cross beam (25) are all rectangular frames surrounded by I-beams.

3. The girder-type modular fuselage of the unmanned helicopter according to claim 2, characterized in that, The rear fuselage truss module (2) further includes a first V-shaped strengthening structure (28), a second V-shaped strengthening structure (29), a third V-shaped strengthening structure (210), an inverted V-shaped strengthening structure (211) and a beam strengthening structure (212); The first V-shaped strengthening structure (28) is arranged inside the rectangular frame of the rear fuselage first cross beam (21); the second V-shaped strengthening structure (29) is arranged inside the rectangular frame of the rear fuselage second cross beam (22); the third V-shaped strengthening structure (210) is arranged inside the rectangular frame of the rear fuselage fifth cross beam (25); the inverted V-shaped strengthening structure (211) is arranged inside the rectangular frame of the rear fuselage third cross beam (23); the beam strengthening structure (212) is symmetrically arranged on the rear fuselage left longitudinal beam (26) and the rear fuselage right longitudinal beam (27).

4. The girder-type modular fuselage of the unmanned helicopter according to claim 3, wherein It also includes a transmission system connection module (3), a landing gear connection module (4), a support connection module (5), a tail wing support module (6) and a load installation module (7).

5. The girder-type modular fuselage of an unmanned helicopter according to claim 4, characterized in that, The transmission system connection module (3) includes two oppositely arranged reducer box connectors (31) and belt supports (32); The reducer box connector (31) is a V-shaped I-beam, with its two ends respectively fixed to the rear fuselage second cross beam (22) and the rear fuselage third cross beam (23), and the bent end of the reducer box connector (31) is fixed to the rear fuselage left longitudinal beam (26) or the rear fuselage right longitudinal beam (27); The belt support (32) is fixed to the first V-shaped strengthening structure (28).

6. The girder-type modular fuselage of an unmanned helicopter according to claim 4, characterized in that, The landing gear connection module (4) includes a plurality of landing gear connectors symmetrically fixed to the lower end of the rear fuselage truss module (2); the landing gear connectors include: A landing gear connection upper sleeve (41), which is a semi-circular ring structure; the landing gear connection upper sleeve (41) is fixed to the lower end surface of the left longitudinal beam (26) or the right longitudinal beam (27) of the rear fuselage. A landing gear connection lower sleeve (42), which is a semi-circular ring structure. The landing gear connection lower sleeve (42) is fixed to the landing gear connection upper sleeve (41). The semi-circular ring structure of the landing gear connection upper sleeve (41) and the semi-circular ring structure of the landing gear connection lower sleeve (42) enclose a connection hole.

7. The girder-type modular fuselage of an unmanned helicopter according to claim 6, wherein The landing gear connection module (4) further includes a landing gear connection damping rubber (43), which is arranged in the connection hole.

8. The girder-type modular fuselage of the unmanned helicopter according to claim 4, characterized in that The support connection module (5) includes: a plurality of fuel tank support members, buffer type landing gear connectors and side mounting connectors symmetrically arranged on the left longitudinal beam (26) and the right longitudinal beam (27) of the rear fuselage.

9. The modular fuselage of the unmanned helicopter with a girder type according to claim 4, characterized in that, The tail wing support module (6) includes a tail wing middle support member (62) fixed to the fifth cross beam (25) of the rear fuselage and two tail wing side support members (61); the two tail wing side support members (61) are symmetrically arranged on the left and right sides of the tail wing middle support member (62). The tail wing middle support member (62) is a Y-shaped round tube; the tail wing middle support member (62) includes a lower connection end and two fixed ends arranged on the connection end; a first bushing (621) is welded on the connection end and then fixed to the middle part of the fifth cross beam (25) of the rear fuselage; a flat plate (622) for fixing GPS is arranged on one fixed end, and a second bushing (623) is welded on the other fixed end. For the tail wing side support member (61), a third bushing (611) is welded to its lower end, and it is fixed to the fifth cross beam (25) of the rear fuselage through a fixing member. A fourth bushing (612) is welded to the upper end of the tail wing side support member (61).

10. The girder-type modular fuselage of an unmanned helicopter according to claim 4, characterized in that, The load installation module (7) includes a load support cross beam (71) and a load support member (72). Both ends of the load support cross beam (71) are respectively fixed to the left longitudinal beam (26) and the right longitudinal beam (27) of the rear fuselage. The load support member (72) is fixed to the second cross beam (22) of the rear fuselage.

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