Multi-wing vertical lifting unmanned aerial vehicle

Abstract

The invention discloses a multi-wing vertical lifting unmanned aerial vehicle, relates to the technical field of unmanned aerial vehicles, and aims to solve the problems that various sundries may appear due to the complicated flight environment, and when the sundries are in contact with paddles rotating at a high speed of the unmanned aerial vehicle, the acting force on the paddles cannot be buffered, so that the paddles are broken. According to the multi-wing vertical lifting unmanned aerial vehicle, through the elastic backing ring, the outer cover ring and the inner backing ring are clamped, rotation of the blades is achieved, when the blades are blocked by sundries, resistance is transmitted to the elastic cushion block through the blades and the outer cover ring, the elastic cushion block deforms, the resistance is buffered, the blades are protected, meanwhile, when the resistance is large, the elastic cushion block is damaged by the resistance, and therefore the blades are protected. The clamping connection between the outer cover ring and the inner backing ring is released, so that the blades stop rotating, and the blades are prevented from being broken under the condition of increasing resistance.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, in particular to a multi-wing vertical lift unmanned aerial vehicle. Background Art

[0002] At present, a multi-wing vertical take-off and landing UAV is an unmanned aerial vehicle with multiple wings (usually three or more). Its main feature is that it can take off, land and hover vertically like a helicopter. Compared with traditional fixed-wing UAVs, it does not require a specific take-off and landing site such as a runway, and has higher flexibility. Compared with a single-rotor helicopter, the multi-wing layout makes it better in flight stability and maneuverability. For example, in the logistics distribution scenario in a complex urban environment, it can take off and land conveniently on the top of a building, in a small open space, etc.

[0003] During the flight of a drone, due to the complexity of the flight environment, various debris may appear. When the debris comes into contact with the high-speed rotating blades of the drone, the force acting on the blades cannot be buffered, causing the blades to break. Summary of the invention

[0004] To achieve the above objectives, the present invention is implemented through the following technical solutions: a multi-wing vertical take-off and landing UAV, comprising:

[0005] A fuselage, with wing mechanisms fixedly mounted on both sides of the fuselage, the wing mechanisms being used to block debris encountered during flight;

[0006] A paddle mechanism, which is used to drive air to flow downward quickly, and is installed inside the wing mechanism;

[0007] A support mechanism, which is used to buffer the impact force during vertical takeoff and landing, and is installed at the bottom of the fuselage;

[0008] Wherein, the blade mechanism includes a motor, the motor is fixedly installed inside the wing mechanism, and a coupling is fixedly installed on the output end of the motor, the output end of the motor is fixedly connected to a transmission shaft through a coupling, an inner gasket is fixedly installed on the outer side of the transmission shaft, the outer side of the inner gasket is hexagonal, and an outer cover ring is installed on the outer side of the inner gasket, and an elastic pad is fixedly installed on the inner wall of the outer cover ring, and the elastic pad is evenly installed along the center position of the transmission shaft, and the outer cover ring and the inner gasket are clamped together through the elastic gasket to realize the rotation of the blade, and when the blade is blocked by debris, the resistance The force is transmitted to the elastic pad through the blade and the outer cover ring, causing the elastic pad to deform, thereby buffering the resistance and protecting the blade. At the same time, when the resistance is large, the elastic pad is damaged by the resistance, and the clamping connection between the outer cover ring and the inner pad ring is released to stop the blade from rotating, thereby avoiding the blade from breaking under increased resistance. The outer cover ring is clamped with the outer side of the inner pad ring through the elastic pad, and a nut is threaded on the top of the outer side of the transmission shaft. The bottom of the nut is tightly fitted with the top of the outer cover ring through the pad, and the blade is fixedly installed on the outer side of the outer cover ring, and the blade is evenly installed on the outer side of the outer cover ring along the center position of the transmission shaft.

[0009] Preferably, the wing mechanism includes a connecting arm, one end of the connecting arm is fixedly connected to the outer side of the fuselage, and the other end of the connecting arm is fixedly connected to a fixing ring, the inner wall of the fixing ring is fixedly connected to a fixing groove ring, the center position of the bottom of the fixing groove ring is fixedly connected to the outer side of the motor, the output end of the motor passes through the fixing groove ring and extends to its top, the bottom of the fixing ring is fixedly connected to a bottom cylinder, the bottom end of the bottom cylinder is an inwardly inclined conical cylinder, through the cooperation of the bottom cylinder and the inner guide cylinder, in the process of conducting air downward, the characteristic that the gap between the inner guide cylinder and the bottom cylinder gradually decreases from top to bottom is utilized to accelerate the speed of air flowing downward, assist the blade mechanism, obtain greater lift, and reduce energy loss, and at the same time, the empty groove opened on the outer side of the inner guide cylinder allows a part of the air to flow quickly along the surface of the motor, drive the heat of the motor when working, and improve the heat dissipation effect, and the outer side of the bottom cylinder is evenly provided with through grooves, and the bottom of the fixing groove ring is fixedly installed with an inner guide cylinder.

[0010] Preferably, the inner guide cylinder is located at the outside of the motor, and the bottom end of the inner guide cylinder is a conical cylinder recessed inward, and empty grooves are evenly opened on the outside of the inner guide cylinder. An inner retaining ring is fixedly installed on the inner wall of the bottom cylinder, and the gap between the inner guide cylinder and the bottom cylinder gradually decreases from top to bottom. A top cylinder is fixedly installed on the top of the fixed ring, and the top cylinder is a conical cylinder with an outer diameter gradually decreasing from top to bottom, and the top cylinder is located at the outside of the blade. A top cover is fixedly installed on the top of the top cylinder, and the cooperation between the top cylinder and the top cover can protect the inner high-speed rotating blades during flight. At the same time, the top cover uses the grille slots to provide an air introduction gap, and at the same time blocks large debris, thereby reducing the obstruction of floating debris to the drone during flight, and grille slots are evenly opened on the top of the top cover.

[0011] Preferably, the supporting mechanism includes a fixing frame, which is fixedly mounted on the bottom of the fuselage, and a slide groove frame is fixedly mounted on the bottom of the fixing frame, a slide groove is opened on the outer side of the slide groove frame, and a slider is slidably mounted at the slide groove of the slide groove frame, and an elastic gasket is fixedly mounted on the top of the slider, and the elastic deformation of the elastic gasket can buffer the impact pressure when the landing speed is too fast, so as to avoid damage caused by a large impact between the drone and the ground during high-speed landing, the top of the elastic gasket is tightly fitted with the inner wall of the slide groove frame, connecting rods are fixedly mounted on both sides of the slider, and a rotating rod is rotatably mounted on the bottom of the slide groove frame through a fastener, and the rotating rod is symmetrically mounted along the center position of the axis of the slide groove frame.

[0012] Preferably, a rotating plate is rotatably installed at one end of the connecting rod away from the slider, and one end of the rotating rod away from the slide groove frame is rotatably connected to the opposite surface of the rotating plate through a fastener, and an outer support rod is fixedly installed at the bottom end of the rotating plate, and an inner support rod is fixed at the bottom of the opposite surface of the rotating plate. Through the cooperation of the inner support rod and the outer support rod, when the landing impact pressure is large, the rotating plate and the connecting rod rotate, so that the inner support rod contacts the ground, and cooperates with the contact between the outer support rod and the ground to increase friction, thereby avoiding large sliding between the drone and the ground during landing, which affects the accuracy of the landing position. The position of the inner support rod is higher than the outer support rod.

[0013] The present invention provides a multi-wing vertical lift UAV, which has the following beneficial effects:

[0014] 1. The multi-wing vertical lift UAV uses an elastic gasket to clamp the outer cover ring and the inner gasket ring to realize the rotation of the blade. When the blade is blocked by debris, the resistance is transmitted to the elastic pad through the blade and the outer cover ring, so that the elastic pad is deformed to buffer the resistance and protect the blade. At the same time, when the resistance is large, the elastic pad is damaged by the resistance, the clamping between the outer cover ring and the inner gasket ring is released, the blade stops rotating, and the blade is prevented from breaking under increased resistance.

[0015] Second, the multi-wing vertical lift UAV, through the cooperation between the bottom tube and the inner guide tube, in the process of conducting air downward, utilizes the characteristic that the gap between the inner guide tube and the bottom tube gradually decreases from top to bottom, accelerates the speed of air flowing downward, assists the blade mechanism, obtains greater lift, and reduces energy loss. At the same time, the empty slots opened on the outside of the inner guide tube allow part of the air to flow quickly along the surface of the motor, driving the heat of the motor when it is working and improving the heat dissipation effect.

[0016] 3. The multi-wing vertical take-off and landing UAV protects the high-speed rotating blades on the inside during flight through the cooperation of the top tube and the top cover. At the same time, the top cover uses the opened grille slots to provide air inlet gaps and block large debris, thereby reducing the obstruction of floating debris to the UAV during flight.

[0017] Fourth, the multi-wing vertical lift UAV can buffer the impact pressure when the landing speed is too fast through the elastic deformation of the elastic pad ring, so as to avoid damage caused by a large impact between the UAV and the ground during high-speed landing.

[0018] 5. The multi-wing vertical lift UAV cooperates with the inner support rod and the outer support rod. When the landing impact pressure is large, the rotating plate and the connecting rod rotate, so that the inner support rod contacts the ground, and cooperates with the contact between the outer support rod and the ground to increase the friction, thereby avoiding large sliding between the UAV and the ground during landing, which affects the accuracy of the landing position. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the external structure of a multi-wing vertical lift UAV of the present invention;

[0020] Figure 2 This is a side view of the structure of a multi-wing vertical lift UAV of the present invention;

[0021] Figure 3 It is a schematic diagram of the wing mechanism structure of the present invention;

[0022] Figure 4 It is a partial structural dissection diagram of the wing mechanism of the present invention;

[0023] Figure 5 It is a partial structural dissected side view of the wing mechanism of the present invention;

[0024] Figure 6 It is a schematic diagram of the structure of the blade mechanism of the present invention;

[0025] Figure 7 It is a partial structural schematic diagram of the blade mechanism of the present invention;

[0026] Figure 8 It is a schematic diagram of the supporting mechanism structure of the present invention;

[0027] Fig. 9 It is a partial structural schematic diagram of the support mechanism of the present invention.

[0028] In the figure: 1, fuselage; 2, wing mechanism; 3, blade mechanism; 4, supporting mechanism; 21, connecting arm; 22, fixing ring; 23, top tube; 24, top cover; 25, bottom tube; 26, inner guide tube; 27, fixing groove ring; 28, inner retaining ring; 31, motor; 32, coupling; 33, transmission shaft; 34, outer cover ring; 35, nut; 36, blade; 37, inner gasket; 38, elastic pad; 41, fixing frame; 42, slide frame; 43, connecting rod; 44, rotating plate; 45, outer support rod; 46, rotating rod; 47, inner support rod; 48, elastic gasket; 49, slider. DETAILED DESCRIPTION

[0029] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments of the present invention are provided for the purpose of illustration and description, and are not intended to be exhaustive or to limit the present invention to the disclosed forms. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments are selected and described in order to better illustrate the principles and practical applications of the present invention, and to enable those of ordinary skill in the art to understand the present invention and thereby design various embodiments with various modifications suitable for specific uses.

[0030] The first embodiment, as Figure 1 to Figure 2 and Figure 6 to Figure 7 As shown, the present invention provides a technical solution: a multi-wing vertical lift UAV, comprising:

[0031] A fuselage 1, with wing mechanisms 2 fixedly mounted on both sides of the fuselage 1, the wing mechanisms 2 are used to block debris encountered during flight;

[0032] The paddle mechanism 3 is used to drive the air to flow downward quickly, and the paddle mechanism 3 is installed inside the wing mechanism 2;

[0033] A support mechanism 4, which is used to buffer the impact force during vertical takeoff and landing, and is installed at the bottom of the fuselage 1;

[0034] Among them, the blade mechanism 3 includes a motor 31, which is fixedly installed inside the wing mechanism 2, and a coupling 32 is fixedly installed on the output end of the motor 31, and a transmission shaft 33 is fixedly connected to the output end of the motor 31 through the coupling 32. An inner gasket 37 is fixedly installed on the outer side of the transmission shaft 33, and the outer side of the inner gasket 37 is hexagonal, and an outer cover ring 34 is installed on the outer side of the inner gasket 37. An elastic pad 38 is fixedly installed on the inner wall of the outer cover ring 34, and the elastic pad 38 is evenly installed along the center position of the transmission shaft 33. During the rotation process, when the blade 36 contacts a foreign object and a relative force occurs between the blade 36 and the foreign object, the force is transmitted to the outer cover ring 34 through the blade 36, so that the rotation of the outer cover ring 34 is blocked. At this time, the inner gasket 37 driven by the transmission shaft 33 and the outer cover ring 34 rotate relative to each other, causing the elastic pad 38 to deform, buffer the resistance, and protect the blade 36. At the same time, when the resistance is relatively large, When the torque is too large, the elastic pad 38 is torn and damaged, and the clamping connection between the elastic pad 38 and the inner gasket ring 37 is released, so that the blade 36 and the outer cover ring 34 cannot rotate with the transmission shaft 33 and the inner gasket ring 37, thereby avoiding direct damage to the blade 36. The outer cover ring 34 is clamped with the outer side of the inner gasket ring 37 through the elastic pad 38, and the top of the outer side of the transmission shaft 33 is threadedly connected with a nut 35, and the bottom of the nut 35 is tightly fitted with the top of the outer cover ring 34 through the gasket, and the blade 36 is fixedly installed on the outer side of the outer cover ring 34. Through the output end of the motor 31, the transmission shaft 33 is driven to rotate by the coupling 32, so that during the rotation of the transmission shaft 33, the outer cover ring 34 is driven to rotate through the clamping connection between the inner gasket ring 37 and the elastic pad 38, so that the outer cover ring 34 drives the blade 36 fixedly connected on the outside to rotate, so that the blade 36 drives the air above to flow downward quickly, generating a lifting force, and the blade 36 is evenly installed on the outer side of the outer cover ring 34 along the center position of the transmission shaft 33.

[0035] The second embodiment is based on the first embodiment. Figures 3 to 5As shown, the wing mechanism 2 includes a connecting arm 21, one end of the connecting arm 21 is fixedly connected to the outer side of the fuselage 1, the other end of the connecting arm 21 is fixedly connected to a fixing ring 22, the inner wall of the fixing ring 22 is fixedly connected to a fixing groove ring 27, the center position of the bottom of the fixing groove ring 27 is fixedly connected to the outer side of the motor 31, the output end of the motor 31 passes through the fixing groove ring 27 and extends to the top thereof, when the blade 36 rotates downward to quickly conduct air, the air first passes through the fixing groove ring 27 in the process of spiraling downward, and then enters the gap between the bottom tube 25 and the inner guide tube 26, and at the same time, in the process of spiraling, the air The larger dust particles are concentrated on the outside. In the process of downward conduction, the dust particles and a small part of the air are discharged from the through groove of the bottom cylinder 25 through the cooperation of the bottom cylinder 25 and the inner baffle ring 28. Most of the air is conducted downward from the gap between the inner guide cylinder 26 and the bottom cylinder 25. At the same time, the gap between the inner guide cylinder 26 and the bottom cylinder 25 gradually decreases from top to bottom, which speeds up the air discharge. The bottom of the fixed ring 22 is fixedly connected with the bottom of the bottom cylinder 25. The bottom end of the bottom cylinder 25 is an inwardly inclined conical cylinder, and the outer side of the bottom cylinder 25 is evenly provided with through grooves. The inner guide cylinder 26 is fixedly installed at the bottom of the fixed groove ring 27.

[0036] The inner guide cylinder 26 is located on the outside of the motor 31, and the bottom end of the inner guide cylinder 26 is a conical cylinder recessed inwardly, and the outer side of the inner guide cylinder 26 is evenly provided with empty grooves, and the inner wall of the bottom cylinder 25 is fixedly installed with an inner retaining ring 28. The gap between the inner guide cylinder 26 and the bottom cylinder 25 gradually decreases from top to bottom, and a top cylinder 23 is fixedly installed on the top of the fixing ring 22. The top cylinder 23 is a conical cylinder with an outer diameter gradually decreasing from top to bottom. The top cylinder 23 cooperates with the top cover 24 so that the top cylinder 23 wraps the blade 36 inside to provide protection for the rotation of the blade 36. At the same time, the top cover 24 blocks external debris through the grille slots provided to provide a gap for air to enter, so as to prevent larger debris from entering the rotation area of ​​the blade 36 during flight and affecting the rotation of the blade 36. The top cylinder 23 is located on the outside of the blade 36, and a top cover 24 is fixedly installed on the top of the top cylinder 23. The top of the top cover 24 is evenly provided with grille slots.

[0037] The third embodiment is based on the first and second embodiments. Figures 8 to 9As shown, the support mechanism 4 includes a fixing frame 41, which is fixedly mounted on the bottom of the fuselage 1, and a slide groove frame 42 is fixedly mounted on the bottom of the fixing frame 41, a slide groove is opened on the outer side of the slide groove frame 42, and a slider 49 is slidably mounted at the slide groove of the slide groove frame 42, and an elastic gasket 48 is fixedly mounted on the top of the slider 49, and the top of the elastic gasket 48 is tightly fitted with the inner wall of the slide groove frame 42. When landing, the outer support rods 45 on both sides first contact the ground. When the landing speed is fast and the impact force on the ground is large, the impact pressure is transmitted to the connecting rod 43 and the slider 49 through the outer support rod 45 and the rotating plate 44, so that the slider 49 compresses the elastic gasket 48 to deform. Through the deformation of the elastic gasket 48, the impact pressure is buffered to protect the drone, and connecting rods 43 are fixedly mounted on both sides of the slider 49, and a rotating rod 46 is rotatably mounted on the bottom of the slide groove frame 42 through a fastener, and the rotating rod 46 is symmetrically installed along the center position of the axis of the slide groove frame 42.

[0038] A rotating plate 44 is rotatably installed at one end of the connecting rod 43 away from the slider 49, and the end of the rotating rod 46 away from the slide groove frame 42 is rotatably connected to the opposite surface of the rotating plate 44 through a fastener. An outer support rod 45 is fixedly installed at the bottom end of the rotating plate 44, and an inner support rod 47 is fixed at the bottom of the opposite surface of the rotating plate 44. During the deformation of the elastic gasket 48, the slider 49, the connecting rod 43, the rotating plate 44 and the outer support rod 45 move together. At the same time, the rotating plate 44 rotates during the movement, so that the inner support rod 47 contacts the ground to assist the outer support rod 45 in supporting and improve the support stability. The position of the inner support rod 47 is higher than the outer support rod 45.

[0039] When in use, the blade mechanism 3 rotates, driving air to enter from the top of the wing mechanism 2 and be discharged from the bottom, so that the UAV generates lift to achieve vertical take-off. At the same time, the wing mechanism 2 protects the internal blade mechanism 3 during take-off and flight, and the support mechanism 4 provides support for the UAV through contact with the ground during take-off and landing.

[0040] In the paddle mechanism 3, the output end of the motor 31 is used to drive the transmission shaft 33 to rotate by using the coupling 32, so that during the rotation of the transmission shaft 33, the outer cover ring 34 is driven to rotate through the clamping connection between the inner gasket ring 37 and the elastic pad 38, so that the outer cover ring 34 drives the paddle 36 fixedly connected to the outside to rotate, so that the paddle 36 drives the air above to flow downward quickly, generating a lifting force. At the same time, during the rotation process, when the paddle 36 contacts a foreign object and a relative force occurs between the paddle 36 and the foreign object, the paddle 36 acts as a The force is transmitted to the outer cover ring 34 through the blades 36, so that the rotation of the outer cover ring 34 is blocked. At this time, the inner gasket ring 37 driven by the transmission shaft 33 and the outer cover ring 34 rotate relative to each other, causing the elastic pad 38 to deform, thereby buffering the resistance and protecting the blades 36. At the same time, when the resistance is large, the elastic pad 38 is torn and damaged to release the clamping connection with the inner gasket ring 37, so that the blades 36 and the outer cover ring 34 cannot rotate with the transmission shaft 33 and the inner gasket ring 37, thereby avoiding direct damage to the blades 36.

[0041] In the wing mechanism 2, the top tube 23 cooperates with the top cover 24 so that the top tube 23 wraps the blade 36 inside, and provides protection for the rotation of the blade 36. At the same time, the top cover 24 blocks external debris through the grille slots provided to provide a gap for air to enter, so as to prevent larger debris from entering the rotation area of ​​the blade 36 during flight and affecting the rotation of the blade 36. At the same time, when the blade 36 rotates downward to quickly conduct air, the air first passes through the fixed groove ring 27 during the spiral downward process, and then enters the gap between the bottom tube 25 and the inner guide tube 26. At the same time, during the spiral process, larger dust particles in the air are concentrated on the outside. During the downward conduction process, the dust particles and a small part of the air are discharged from the through groove of the bottom tube 25 through the cooperation of the bottom tube 25 and the inner stop ring 28, and most of the air is conducted downward from the gap between the inner guide tube 26 and the bottom tube 25. At the same time, the gap between the inner guide tube 26 and the bottom tube 25 gradually decreases from top to bottom, which accelerates the air discharge speed.

[0042] In the support mechanism 4, when landing, the outer support rods 45 on both sides first contact the ground. When the landing speed is fast and has a large impact force on the ground, the impact pressure is transmitted to the connecting rod 43 and the slider 49 through the outer support rod 45 and the rotating plate 44, so that the slider 49 compresses the elastic gasket 48 to deform. Through the deformation of the elastic gasket 48, the impact pressure is buffered to protect the UAV. At the same time, during the deformation of the elastic gasket 48, the slider 49, the connecting rod 43, the rotating plate 44 and the outer support rod 45 move together. At the same time, during the movement, the rotating plate 44 rotates, so that the inner support rod 47 contacts the ground to assist the outer support rod 45 in supporting and improve the support stability.

[0043] Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field and related fields without creative work should fall within the scope of protection of the present invention. The structures, devices and operating methods not specifically described and explained in the present invention are implemented according to the conventional means in the field unless otherwise specified and limited.

Claims

1. A multi-wing vertical take-off and landing UAV, characterized in that: include: A fuselage (1), with wing mechanisms (2) fixedly mounted on both sides of the fuselage (1), the wing mechanisms (2) being used to block debris encountered during flight; A paddle mechanism (3), the paddle mechanism (3) being used to drive air to flow downward rapidly, the paddle mechanism (3) being installed inside the wing mechanism (2); A support mechanism (4), the support mechanism (4) is used to buffer the impact force during vertical take-off and landing, and the support mechanism (4) is installed at the bottom of the fuselage (1); The blade mechanism (3) comprises a motor (31), the motor (31) is fixedly mounted inside the wing mechanism (2), and a coupling (32) is fixedly mounted on the output end of the motor (31), the output end of the motor (31) is fixedly connected to a transmission shaft (33) through the coupling (32), an inner gasket (37) is fixedly mounted on the outer side of the transmission shaft (33), the outer side of the inner gasket (37) is hexagonal, and an outer cover ring (34) is mounted on the outer side of the inner gasket (37), an elastic pad (38) is fixedly mounted on the inner wall of the outer cover ring (34), the elastic pad (38) is evenly mounted along the center position of the transmission shaft (33), and the outer cover ring (34) is clamped with the outer side of the inner gasket (37) through the elastic pad (38).

2. A multi-wing vertical take-off and landing UAV according to claim 1, characterized in that: A nut (35) is threadedly connected to the top of the outer side of the transmission shaft (33); the bottom of the nut (35) is tightly fitted with the top of the outer cover ring (34) via a gasket; blades (36) are fixedly mounted on the outer side of the outer cover ring (34); and the blades (36) are evenly mounted on the outer side of the outer cover ring (34) along the center position of the transmission shaft (33).

3. The multi-wing vertical take-off and landing UAV according to claim 1, characterized in that: The wing mechanism (2) comprises a connecting arm (21), one end of the connecting arm (21) is fixedly connected to the outer side of the fuselage (1), the other end of the connecting arm (21) is fixedly connected to a fixing ring (22), the inner wall of the fixing ring (22) is fixedly connected to a fixing groove ring (27), the center position of the bottom of the fixing groove ring (27) is fixedly connected to the outer side of the motor (31), and the output end of the motor (31) passes through the fixing groove ring (27) and extends to the top thereof.

4. A multi-wing vertical take-off and landing UAV according to claim 3, characterized in that: The bottom of the fixing ring (22) is fixedly connected to a bottom cylinder (25), the bottom end of the bottom cylinder (25) is an inwardly inclined conical cylinder, and the outer side of the bottom cylinder (25) is evenly provided with through grooves, and the bottom of the fixing groove ring (27) is fixedly installed with an inner guide cylinder (26).

5. The multi-wing vertical take-off and landing UAV according to claim 4, characterized in that: The inner guide cylinder (26) is located outside the motor (31), and the bottom end of the inner guide cylinder (26) is an inwardly concave conical cylinder. The outer side of the inner guide cylinder (26) is evenly provided with hollow grooves. An inner retaining ring (28) is fixedly mounted on the inner wall of the bottom cylinder (25), and the gap between the inner guide cylinder (26) and the bottom cylinder (25) gradually decreases from top to bottom.

6. The multi-wing vertical take-off and landing UAV according to claim 4, characterized in that: A top tube (23) is fixedly mounted on the top of the fixing ring (22). The top tube (23) is a conical tube whose outer diameter gradually decreases from top to bottom, and the top tube (23) is located outside the blade (36). A top cover (24) is fixedly mounted on the top of the top tube (23), and grille grooves are evenly arranged on the top of the top cover (24).

7. The multi-wing vertical take-off and landing UAV according to claim 1, characterized in that: The support mechanism (4) comprises a fixing frame (41), the fixing frame (41) is fixedly mounted on the bottom of the fuselage (1), and a slide groove frame (42) is fixedly mounted on the bottom of the fixing frame (41), a slide groove is provided on the outer side of the slide groove frame (42), and a slider (49) is slidably mounted on the slide groove of the slide groove frame (42).

8. The multi-wing vertical take-off and landing UAV according to claim 7, characterized in that: An elastic gasket (48) is fixedly installed on the top of the slider (49), and the top of the elastic gasket (48) is tightly fitted with the inner wall of the slide groove frame (42). Connecting rods (43) are fixedly installed on both sides of the slider (49). A rotating rod (46) is rotatably installed on the bottom of the slide groove frame (42) through a fastener. The rotating rod (46) is symmetrically installed along the center position of the axis of the slide groove frame (42).

9. The multi-wing vertical take-off and landing UAV according to claim 8, characterized in that: The end of the connecting rod (43) away from the slider (49) is rotatably mounted with a rotating plate (44), and the end of the rotating rod (46) away from the slide slot frame (42) is rotatably connected to the opposite surface of the rotating plate (44) through a fastener.

10. The multi-wing vertical take-off and landing UAV according to claim 9, characterized in that: An outer support rod (45) is fixedly mounted on the bottom end of the rotating plate (44), and an inner support rod (47) is fixedly mounted on the bottom of the opposite surface of the rotating plate (44), wherein the position of the inner support rod (47) is higher than the outer support rod (45).

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