Unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle which comprises an engine, the engine is arranged on a fuselage frame plate in a fuselage through an engine mounting frame, a propeller is arranged on an output shaft of the engine, and the engine mounting frame comprises a main supporting plate, a double-layer isolation damping device and an anti-twisting device. The main supporting plate is arranged on a machine body frame plate in the machine body; a plurality of installation lugs are evenly distributed on the edge of the main supporting plate, plane normal lines of the four installation lugs are gathered at the gravity center position after an engine is installed, and the double-layer isolation vibration reduction device is arranged between each installation lug and the corresponding inner wall on the inner wall of the machine body. The vibration attenuation device is used for attenuating and isolating vibration of an engine and a propeller twice to achieve vibration attenuation. The anti-twisting device is arranged between the inner wall of the machine body and the two opposite edges of the main supporting plate and used for limiting twisting of the main supporting plate in the length direction of the machine body. According to the device, the damping effect is remarkably improved, and the safety and stability of power transmission are guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a unmanned aerial vehicle. Background Art

[0002] The engine is the power source of the UAV. A good engine installation design can not only ensure the flight performance of the UAV, but also avoid safety hazards. The role of the engine mounting frame is to reliably install the engine on the UAV with a suitable installation form and structure, so that the engine can work normally in various use environments and flight conditions, and effectively convert the pulling force or thrust generated by the engine driving the propeller to rotate into the power of the UAV flight.

[0003] The engine mounting bracket must not only have sufficient strength and appropriate rigidity, but also be able to isolate or absorb the vibrations generated when the engine / propeller is working to prevent the vibration from interfering with the sensor and flight control system. It is also necessary to prevent the engine from resonating with the fuselage structure and causing damage to the drone structure.

[0004] At present, the engine mounting frame mostly adopts vibration reduction devices, such as installing elastic rubber pads on the joints of the engine mounting frame, or installing them at the intersection of the engine mounting frame and the UAV. No matter which method is adopted, how to maintain the engine mounting structure with a certain rigidity is a difficult point. If the rigidity of the engine mounting structure is large, the vibration reduction effect is poor. If the rigidity of the engine mounting structure is small, the engine mounting structure may be good at isolating or absorbing and reducing the vibration transmitted to the UAV by the engine. However, if the rigidity is too small, on the one hand, it will cause the propeller thrust line to deviate, resulting in a decrease in the performance of the power system and even cause safety accidents; on the other hand, if the rigidity of the engine mounting structure is too small, it will cause the engine and propeller to vibrate widely. This long-term vibration may cause the loosening and failure of the connection parts of the mechanical connectors, fuel system, and engine electrical system, bringing safety hazards, and will also aggravate the wear of the internal bearings and gears of the engine and the wear of the propeller mounting structure.

[0005] Therefore, it is necessary to provide a drone to solve the above problems. Summary of the invention

[0006] In order to reduce the vibration transmitted from the engine to the fuselage and ensure that the wide-range vibration of the engine and the propeller itself is not caused, the present invention provides a drone to solve the existing problem.

[0007] A drone of the present invention adopts the following technical solution, including: An engine, which is mounted on a fuselage frame plate in the fuselage via an engine mounting frame, and a propeller is arranged on an output shaft thereof; The engine mounting bracket includes: A main support plate, which is vertically arranged on the fuselage frame plate inside the fuselage and parallel to the longitudinal section of the fuselage, and is used to install the engine; A plurality of mounting ears are evenly distributed on the edge of the main support plate, wherein the plane normals of all the mounting ears converge at the center of gravity of the engine after installation; Double-layer isolation and vibration reduction devices, arranged between each mounting ear and the corresponding inner wall on the inner wall of the fuselage, are used to attenuate and isolate the vibration of the engine and propeller twice to achieve vibration reduction; And an anti-twist device is arranged between the inner wall of the fuselage and two opposite edges of the main support plate, and is used to limit the torsion of the main support plate around the length direction of the fuselage.

[0008] Preferably, a plurality of mounting seats are arranged on the fuselage frame plate, wherein the double-layer isolation and vibration reduction device is installed between each mounting ear and the corresponding mounting seat.

[0009] Preferably, the double-layer isolation and vibration reduction device comprises: The end of the vibration-damping support is correspondingly inserted into the mounting holes provided on the mounting ears and the mounting seat, and two baffles are symmetrically provided on the vibration-damping support about the center thereof; Two isolation vibration reduction components, the isolation vibration reduction components are set on the vibration reduction pillars on the opposite sides of the two baffles, and one of the isolation vibration reduction components is set in the mounting hole of the mounting ear, and the other isolation vibration reduction component is set in the mounting hole opened on the mounting seat; And a flat gasket, which is arranged on the end of the vibration-damping support through screws and is used to form an installation limiting structure with the corresponding baffle.

[0010] Preferably, the isolation and vibration reduction assembly comprises: A vibration-damping bushing, the inner ring of which is sleeved on the vibration-damping support between the baffle and the corresponding vibration-damping flat gasket, the outer ring of which is sleeved in the mounting hole, and a connecting sleeve is coaxially arranged at the axial end thereof; and a vibration-damping pad, which is mounted on the connecting sleeve; Among them, the vibration-damping bushing and the vibration-damping pad are both made of rubber material.

[0011] Preferably, the anti-twist device comprises: The bracket assembly is provided with two coaxially arranged torsion bars for rotation along its length direction, and the opposite ends of the two torsion bars are connected by a coupling; The torque arm is arranged at the ends of the two torque bars which are away from each other; and a spherical bearing, one end of which is connected to the torque arm, and the other end of which is connected to the corresponding side surface of the main support plate through the connecting lug.

[0012] Preferably, the bracket assembly comprises: The bracket support plate is provided with torsion bar support lugs along its length direction, and bearing mounting holes are formed in the torsion bar support lugs. A nylon flange bearing is installed in the bearing mounting holes, and a torsion bar is sleeved and fixed on the inner ring of the nylon flange bearing; And a bracket mounting hole is formed in the bracket support plate.

[0013] Preferably, the torsion arm includes: The torsion arm body is provided with a square hole and a pressing groove hole on its side surface, and the square hole and the pressing groove hole communicate with each other. The square hole is used for inserting the torsion bar; A screw hole is formed in the torsion arm body and penetrates through the pressing groove hole; A connection hole is formed at the end of the torsion arm body and penetrates through the pressing groove hole for connecting with the end of the spherical plain bearing.

[0014] Preferably, the spherical plain bearing includes: An external thread spherical plain bearing and an internal thread spherical plain bearing, and the external thread spherical plain bearing and the internal thread spherical plain bearing are threadedly connected; Wherein, the ends of the external thread spherical plain bearing and the internal thread spherical plain bearing are both universal balls; the universal ball at the end of the external thread spherical plain bearing is threadedly connected with the connection hole by a screw, and the universal ball of the internal thread spherical plain bearing is threadedly connected with the connection ear piece by a screw.

[0015] Preferably, the mounting seat includes: a U-shaped part, a first mounting hole for connecting the U-shaped groove of the U-shaped part is formed at the bottom thereof, and a connecting angle piece is arranged on each of the opposite sides of the two ends thereof, and the two connecting angle pieces are inclined for connecting with the fuselage frame.

[0016] Preferably, a plurality of weight reduction holes are evenly arranged on the main support plate.

[0017] The beneficial effects of the present invention are: By arranging the engine mounting bracket on the fuselage frame plate inside the fuselage; and the double-layer isolation and vibration damping device of the engine mounting bracket significantly improves the vibration damping effect compared with the traditional single-layer isolation and vibration damping device, and can also compensate for the thermal deformation and mechanical deformation of the engine in various states. Secondly, through the anti-torsion device of the engine mounting bracket, the torsional vibration of the engine and the propeller mounted on the engine mounting bracket caused by aerodynamic fluctuations, imbalance or installation errors along the length direction of the fuselage can be restricted, ensuring the safety and stability of power transmission. Description of the Drawings

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the accompanying drawings required for the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other accompanying drawings can be obtained based on these drawings.

[0019] Figure 1 Structural schematic diagram of a drone of the present invention; Figure 2 is Figure 1 Structural schematic diagram of the engine mounting bracket in Figure 3 is Figure 2 Left view of Figure 4 Installation detail diagram of the engine mounting bracket and the engine of the drone of the present invention; Figure 5 Structural schematic diagram of the main support plate of the present invention; Figure 6 Structural schematic diagram of the double-layer isolation and vibration damping device of the present invention; Figure 7 Structural schematic diagram of the vibration damping strut of the present invention; Figure 8 Structural schematic diagram of the mounting seat of the present invention; Figure 9 Structural schematic diagram of the anti-twist device of the present invention; Figure 10 Structural schematic diagram of the bracket assembly of the present invention; Figure 11 Structural schematic diagram of the torsion bar of the present invention; Figure 12 Structural schematic diagram of the torsion arm of the present invention; Figure 13 Structural schematic diagram of the spherical plain bearing of the present invention; Figure 14 Structural schematic diagram of the mounting strut of the present invention; Figure 15 Structural schematic diagram of the vibration damping bushing of the present invention; Figure 16 Structural schematic diagram of the vibration damping pad of the present invention.

[0020] In the figure: 1, main support plate; 2, shock absorption device; 3, mounting seat; 4, anti-torsion device; 5, mounting pillar; 6, fuselage frame plate; 7, engine; 8, propeller; 11, weight reduction hole; 12, weight reduction groove; 13, mounting lug; 14, shock absorption device mounting hole; 15, mounting pillar mounting hole; 16, connecting lug mounting hole; 21, flat gasket; 22, shock absorption pillar; 23, shock absorption pad; 24, shock absorption bushing; 25, screw; 31, central mounting hole; 32, mounting angle piece; 33, mounting angle piece mounting hole; 41, bracket assembly; 42, torsion bar; 43, coupling; 44, nylon flange bearing; 45, torsion arm; 46, spherical plain bearing; 47, connecting lug; 411, torsion bar support lug; 412, nylon flange bearing mounting hole; 413, bracket mounting hole; 451, square hole; 452, pressing groove hole; 453, pressing threaded hole; 454, connecting threaded hole; 461, external thread spherical plain bearing; 462, internal thread spherical plain bearing. Detailed implementation manner

[0021] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0022] An embodiment of a drone of the present invention. For the convenience of description of this embodiment, as Figure 1 shown, the engine 7 is arranged on the fuselage frame plate 6 inside the fuselage through an engine mounting frame, and a propeller 8 is installed on the engine output shaft; wherein, the orientation description of the engine mounting frame refers to the following right-handed rectangular coordinate system: X-axis - along the longitudinal axis of the drone fuselage (i.e., the fuselage length direction), forward is positive; Y-axis - along the vertical axis of the drone fuselage, downward is positive; Z-axis - along the transverse axis of the drone fuselage, leftward is positive. Specifically, as Figure 2 shown, the engine mounting frame of the drone includes: a main support plate 1, a double-layer isolation shock absorption device 2 and an anti-torsion device 4. The main support plate 1 is vertically arranged on the fuselage frame plate 6 inside the fuselage and is parallel to the longitudinal section of the fuselage. The main support plate 1 is used for installing the engine; as Figure 5As shown, four mounting lugs 13 are evenly distributed on the edge of the main support plate 1. That is, in this embodiment, the main support plate 1 extends four mounting ear pieces 13 backward (negative X-axis direction) of the unmanned aerial vehicle. Among them, the plane normal lines of the four mounting ear pieces 13 have the same angle with the X-axis, and the plane normal lines of the four mounting ear pieces 13 converge at a point, which is the center of gravity position after the engine is installed. This design can absorb and reduce the vibration transmitted by the engine to the fuselage in the three directions of the X-axis, Y-axis, and Z-axis; the double-layer isolation vibration damping device 2 is arranged between each mounting lug 13 and the corresponding inner wall of the fuselage inner wall, and is used for attenuating and isolating the vibration of the engine and the propeller twice to achieve vibration damping; the anti-torsion device 4 is arranged between the two opposite edges of the fuselage inner wall and the main support plate 1, and is used to limit the torsion of the main support plate 1 around the length direction of the fuselage.

[0023] Exemplarily, in a specific embodiment, as Figure 2 and Figure 4 shown, four mounting seats 3 are fixedly installed on the fuselage frame plate 6. Among them, the double-layer isolation vibration damping device 2 is installed between each mounting lug 13 and the corresponding mounting seat 3. Among them, as Figure 7 shown, in a specific embodiment, the mounting seat 3 includes: a U-shaped part, a first mounting hole 31 for connecting the U-shaped groove of the U-shaped part is opened at the bottom thereof, and a connecting angle piece 32 is arranged on each of the opposite sides of the two ends thereof, and the two connecting angle pieces 32 are inclined. The connecting angle piece 32 is used to connect with the fuselage frame 6. In this embodiment, the two ends of the mounting seat 3 extend two mounting angle pieces 32 forward (positive X-axis direction of the fuselage), and the mounting angle pieces 32 of the four mounting seats 3 are all in a plane. One mounting angle piece mounting hole 33 is designed on each mounting angle piece 32. In this way, each mounting seat 3 can be connected to the fuselage frame plate 6 by two screws passing through the corresponding mounting angle piece mounting holes 33.

[0024] Exemplarily, as Figure 6 shown, in a specific embodiment, the double-layer isolation vibration damping device 2 includes: a vibration damping strut 22, and the end of the vibration damping strut 22 is correspondingly inserted into the second mounting hole 14 opened on the mounting lug 13 and the first mounting hole 31 of the mounting seat 3. As Figure 6 shown, two baffles are symmetrically arranged on the vibration damping strut 22 about its center; an isolation vibration damping component is sleeved on each of the vibration damping strut 22 on the opposite sides of the two baffles; the flat gasket 21 is arranged at the end of the vibration damping strut 22 through a screw 25, and the flat gasket 21 is used to form an installation limit structure with the corresponding baffle. It should be noted that the double-layer isolation vibration damping device attenuates and isolates the vibration of the engine and the propeller twice, significantly improving the vibration damping effect.

[0025] Among them, as Figure 6 shown, in a specific embodiment, the isolation vibration damping component includes: a vibration damping bushing 24 and a vibration damping pad 23. Among them, asFigure 15 and Figure 16 As shown in Figure 16 , both the vibration damping bushing 24 and the vibration damping pad 23 are made of rubber material. The inner ring of the vibration damping bushing 24 is sleeved on the vibration damping strut 22 between the baffle and the corresponding vibration damping flat gasket 21, and the outer ring of the vibration damping bushing 24 is sleeved in the mounting hole. And a connecting sleeve is concentrically arranged at the axial end of the vibration damping bushing 24; the vibration damping pad 23 is sleeved on the connecting sleeve. It should be noted that both the vibration damping bushing 24 and the vibration damping pad 23 are structures of the prior art and will not be elaborated in this embodiment.

[0026] It should be noted that, as Figure 2 shown in Figure 2 , the first isolation and vibration damping component in the double-layer isolation and vibration damping device 2 is located on the P plane, and the second isolation and vibration damping component is located on the Q plane. Compared with the single-layer isolation and vibration damping device, the double-layer isolation and vibration damping device significantly improves the vibration damping effect. Each layer of the isolation and vibration damping component is composed of the vibration damping pad 23 and the vibration damping bushing 24 to complete the vibration damping function.

[0027] Exemplarily, as Figure 9 shown in Figure 9 , in a specific embodiment of the double-layer isolation and vibration damping device 2, the anti-torsion device 4 includes: a bracket assembly 41, a torsion arm 45 and a spherical plain bearing 46. Two coaxially arranged torsion bars 42 are rotatably arranged on the bracket assembly 41 along its length direction, and the relative ends of the two torsion bars 42 are connected by a coupling 43; the torsion arm 45 is arranged at one end of the two torsion bars 42 facing away from each other; one end of the spherical plain bearing 46 is connected to the torsion arm 45, and the other end of the spherical plain bearing 46 is connected to the corresponding side end face of the main support plate 1 through a connecting lug 47.

[0028] Among them, as Figure 10 shown in Figure 10 , in a specific embodiment, the bracket assembly 41 includes: a bracket support plate, on which a torsion bar support lug 411 is arranged along its length direction, and a bearing mounting hole 412 is opened in the torsion bar support lug 411. A nylon flange bearing 44 is installed in the bearing mounting hole 412. Among them, the torsion bar 42 is sleeved and fixed on the inner ring of the nylon flange bearing 44; a bracket mounting hole 413 is opened on the bracket support plate, and the bracket support plate is fixed to the fuselage frame 6 by screws passing through the bracket mounting hole 413.

[0029] Among them, as Figure 12 shown in Figure 12 , in a specific embodiment, the torsion arm 45 includes: a torsion arm body, a screw hole 453 and a connection hole 454. A square hole 451 and a pressing groove hole 45 are opened on the side surface of the torsion arm body, and the square hole 451 and the pressing groove hole 45 communicate with each other. Among them, the square hole 451 is used for inserting into the torsion bar 42; the screw hole 453 is arranged on the torsion arm body and penetrates through the pressing groove hole 452; the connection hole 454 is opened at the end of the torsion arm body and penetrates through the pressing groove hole 452 for connecting with the end of the spherical plain bearing 46.

[0030] Among them, as Figure 13 shown, in a specific embodiment, the spherical plain bearing 46 includes an external thread spherical plain bearing 461 and an internal thread spherical plain bearing 462, and the external thread spherical plain bearing 461 and the internal thread spherical plain bearing 462 are threadedly connected; among them, the ends of both the external thread spherical plain bearing 461 and the internal thread spherical plain bearing 462 are universal balls; the universal ball at the end of the internal thread spherical plain bearing 462 is threadedly connected to the connection hole 454 by a screw, and the universal ball of the external thread spherical plain bearing 461 is installed on the connection lug 47 by a screw. Among them, as Figure 5 shown, there are two mounting holes 16 for the connection lugs 47 on each side of the main support plate 1. The mounting holes 16 are used to mount the connection lugs 47 of the anti-torsion device 4, realizing the connection between the anti-torsion device 4 and the main support plate 1.

[0031] It should be noted that in this embodiment, the nylon flange bearing 44 is made of nylon, with light weight, and plays a role in supporting and lubricating when the torsion bar rotates. As Figure 10 shown, one end of the torsion bar 42 is square and is inserted into the square hole 451 on the torsion arm 45; the other end of the torsion bar 42 is wedge-shaped, and the included angle between the two surfaces of the wedge is 60°. The wedge-shaped end is inserted into the hole of the coupling 43 during installation, and a set screw is used to press against the two flat surfaces of the wedge-shaped end to prevent relative rotation between the torsion bar 42 and the coupling 43. Therefore, the two torsion bars 42 are connected into a whole that will not produce relative rotation through the coupling 43. After the square end of the torsion bar 42 is inserted into the square hole 451 of the torsion arm 45, a screw is screwed into the screw hole 453 on the side of the torsion arm 45, so that the pressing slot hole 452 is deformed to a certain extent. At this time, the square hole 451 can press the torsion bar 42, thereby preventing the torsion bar 42 from moving and falling off the torsion arm 25. The spherical plain bearing has three degrees of rotational freedom. Because the vibration of the engine itself persists, and in addition, due to the fluctuations, imbalance or installation errors of the aerodynamic force of the propeller, if the stiffness of the engine mount in the X-axis direction is insufficient, wide-range vibrations of the engine and the propeller will occur, which is extremely harmful. Using the anti-torsion device 4 of this embodiment to connect the main support plate 1 with the fuselage frame 6 can limit the torsional vibration of the engine mount and the engine around the X-axis.

[0032] Exemplarily, as Figure 1 and Figure 14 , it further includes a mounting pillar 5. The mounting pillar 5 is cylindrical and has a through hole in the middle. The main support plate 1, the mounting pillar 5 and the engine are connected by screws and nuts. The length of the mounting pillar 5 can be determined according to the gap between the engine and the fuselage frame plate or the engine nacelle bulkhead. This reserved gap can ensure the heat dissipation of the engine and the installation space for engine accessories.

[0033] Exemplarily, in a specific embodiment, a plurality of weight-reducing holes are evenly arranged on the main support plate 1.

[0034] Working principle During the operation of the UAV, since both the engine 7 and the propeller 8 generate vibrations, after these vibrations are transmitted to the double-layer isolation and vibration damping device through the main support plate 1, the vibration is attenuated twice through the vibration damping bushings 24 and the vibration damping pads 23 of the two isolation and vibration damping components of the double-layer isolation and vibration damping device, and the vibration amplitude is greatly reduced. Thus, the vibrations of the engine 7 and the propeller 8 are prevented from being transmitted to the fuselage of the UAV, and the harm of the vibrations to the avionics equipment and the fuselage structure of the UAV is avoided. On the other hand, the anti-torsion device of the present invention connects the main support plate to the fuselage, which can limit the torsional vibration of the engine mounting bracket and the engine around the propeller rotation axis, and increases the rigidity of the engine mounting bracket.

[0035] In summary, the engine mounting bracket realized by the present invention has both sufficient strength and appropriate rigidity. Compared with the single-layer isolation and vibration damping device, the double-layer isolation and vibration damping device of the present invention significantly improves the vibration damping effect. At the same time, the present invention also designs an anti-torsion device, which can limit the torsional vibration of the engine and the propeller around the rotation axis, and ensure the safety and stability of power transmission.

[0036] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A drone, characterized in that: include: An engine, which is mounted on a fuselage frame plate in the fuselage via an engine mounting frame, and a propeller is arranged on an output shaft thereof; The engine mounting bracket includes: A main support plate, which is vertically arranged on the fuselage frame plate inside the fuselage and parallel to the longitudinal section of the fuselage, and is used to install the engine; A plurality of mounting ears are evenly distributed on the edge of the main support plate, wherein the plane normals of all the mounting ears converge at the center of gravity of the engine after installation; Double-layer isolation and vibration reduction devices, arranged between each mounting ear and the corresponding inner wall on the inner wall of the fuselage, are used to attenuate and isolate the vibration of the engine and propeller twice to achieve vibration reduction; And an anti-twist device is arranged between the inner wall of the fuselage and two opposite edges of the main support plate, and is used to limit the torsion of the main support plate around the length direction of the fuselage.

2. The drone according to claim 1, characterized in that: A plurality of mounting seats are arranged on the fuselage frame plate, wherein a double-layer isolation and vibration reduction device is installed between each mounting ear and the corresponding mounting seat.

3. The drone according to claim 2, characterized in that: The double-layer isolation and vibration reduction device includes: The end of the vibration-damping support is correspondingly inserted into the mounting holes provided on the mounting ears and the mounting seat, and two baffles are symmetrically provided on the vibration-damping support about the center thereof; Two isolation vibration reduction components, the isolation vibration reduction components are set on the vibration reduction pillars on the opposite sides of the two baffles, and one of the isolation vibration reduction components is set in the mounting hole of the mounting ear, and the other isolation vibration reduction component is set in the mounting hole opened on the mounting seat; And a flat gasket, which is arranged on the end of the vibration-damping support through screws and is used to form an installation limiting structure with the corresponding baffle.

4. The drone according to claim 3, characterized in that: The isolation and vibration reduction components include: A vibration-damping bushing, whose inner ring is sleeved on the vibration-damping support between the baffle and the corresponding vibration-damping flat gasket, whose outer ring is sleeved in the mounting hole, and whose axial end is concentrically provided with a connecting sleeve; and a vibration-damping pad, which is mounted on the connecting sleeve; Among them, the vibration-damping bushing and the vibration-damping pad are both made of rubber material.

5. The drone according to claim 1, characterized in that: The anti-twist device includes: The bracket assembly is provided with two coaxially arranged torsion bars for rotation along its length direction, and the opposite ends of the two torsion bars are connected by a coupling; The torque arm is arranged at the ends of the two torque bars which are away from each other; and a spherical bearing, one end of which is connected to the torque arm, and the other end of which is connected to the corresponding side surface of the main support plate through the connecting lug.

6. The drone according to claim 5, characterized in that: The bracket assembly includes: The bracket support plate is provided with a torsion bar support ear piece along its length direction, and a bearing mounting hole is opened on the torsion bar support ear piece, and a nylon flange bearing is installed in the bearing mounting hole, wherein the torsion bar is fixed to the inner ring of the nylon flange bearing; And the bracket mounting hole is opened on the bracket support plate.

7. The drone according to claim, characterized in that: Torque arm includes: The torque arm body has a square hole and a clamping slot on its side, and the square hole and the clamping slot are connected, wherein the square hole is used for plugging with the torque rod; A screw hole is provided on the torque arm body and penetrates the clamping slot; The connecting hole is provided at the end of the torque arm body and passes through the clamping slot hole, and is used for connecting with the end of the spherical bearing.

8. The drone according to claim 7, characterized in that: Spherical plain bearings include: An externally threaded spherical bearing and an internally threaded spherical bearing, wherein the externally threaded spherical bearing and the internally threaded spherical bearing are threadedly connected; Among them, the ends of the external threaded spherical bearing and the internal threaded spherical bearing are both universal balls; the universal ball at the end of the external threaded spherical bearing is threadedly connected to the connecting hole through a screw, and the universal ball of the internal threaded spherical bearing is connected to the connecting ear through a screw.

9. The drone according to claim 2, characterized in that: Mount includes: The U-shaped part has a first mounting hole at the bottom thereof for connecting to the U-shaped groove, and a connecting angle piece is arranged on each of the two opposite sides of the two ends thereof, and the two connecting angle pieces are arranged obliquely and are used to connect to the fuselage frame.

10. The drone according to claim 1, characterized in that: A plurality of weight-reducing holes are evenly distributed on the main support plate.

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