Vertical fixed-wing unmanned aerial vehicle

Abstract

The utility model discloses a vertical fixed wing unmanned aerial vehicle which comprises a rack and vertical propellers, four sets of vertical propellers are installed on the side wall of the top end of the rack at equal intervals, a rocket booster is installed at the center position of the top end of the rack, forward propellers are installed on the side wall of the rack, and the rocket booster is installed on the side wall of the rack. Cabins are installed on the two sides of the rack correspondingly, side plates are arranged outside the cabins correspondingly, and rotating sleeves are installed at the ends, close to the cabins, of the side plates correspondingly. According to the vertical fixed-wing unmanned aerial vehicle, the unmanned aerial vehicle is conveniently driven to fly forwards after the vertical fixed-wing unmanned aerial vehicle takes off vertically, the initial speed during forward flying is increased, the undercarriage is conveniently and conveniently folded and unfolded, elastic buffering protection during landing is facilitated, the vibration amplitude during landing is reduced, and the safety of the unmanned aerial vehicle is improved. And the service life of the vertical fixed-wing unmanned aerial vehicle is prolonged.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically a vertical take-off and landing fixed-wing UAV. Background Technology

[0002] Vertical take-off and landing (VTOL) fixed-wing drones can take off and land vertically anywhere without a runway, adapting to various complex terrains. They are particularly suitable for use in urban areas, mountainous regions, and other places without runways. Combining the advantages of multi-rotor and fixed-wing drones, VTOL fixed-wing drones have longer endurance and higher flight speeds. VTOL fixed-wing drones have wide applications in many fields, including logistics and delivery, emergency rescue, agricultural plant protection, geographic surveying, urban air traffic, and environmental monitoring.

[0003] A vertical take-off fixed-wing unmanned aerial vehicle (UAV) disclosed in authorization announcement number CN210338285U includes a fuselage, on which wings, an internal slot, and adjusting bolts are provided. The wings are fixedly connected to the upper and lower sides of the fuselage. The internal slot is located inside the fuselage. The adjusting bolts are movably connected to the outer surface of the fuselage. A fixing rod is provided inside the internal slot. An adjusting rod is provided at the left end of the fixing rod. A signal rod is provided at the left end of the adjusting rod. A support rod is provided on the wings. A support frame is provided at the lower end of the support rod. A connecting plate is provided at the lower end of the support frame. A vibration damping spring is provided at the lower end of the connecting plate.

[0004] Although it achieves the goal of locking the adjusting rod inside the fixed rod using adjusting bolts, when the drone is not in use, the signal rod can be retracted into the built-in slot through the adjusting rod, which effectively increases the protection of the drone signal rod and prevents the signal rod from breaking when the drone is not in use, thus improving the service life of the drone. Through the combination of connecting plate, damping spring, fixed plate and base plate, when the drone lands, the drone will exert a compressive force on the damping spring, and at the same time the damping spring will generate a rebound force on the drone, which effectively enhances the buffer force when the drone lands, reduces the probability of damage when the drone lands, and improves the protection effect when the drone is in use;

[0005] However, this does not solve the problem that existing drones of this type are generally not easy to propel forward during use, affecting the initial speed during forward flight, making it difficult to easily fold and unfold the landing gear, and making it difficult to provide elastic cushioning protection during landing, which greatly affects the vibration amplitude during landing and the service life of vertical take-off and landing fixed-wing drones. Utility Model Content

[0006] The purpose of this utility model is to provide a vertical take-off fixed-wing UAV to solve the problems mentioned in the background art, such as the UAV's inconvenience in taking off vertically and then easily propelling itself forward, which affects the initial velocity during forward flight, the inconvenience in folding and unfolding the landing gear, the inconvenience in providing elastic cushioning protection during landing, which affects the vibration amplitude during landing and the service life of the vertical take-off fixed-wing UAV.

[0007] To achieve the above objectives, this utility model provides the following technical solution: a vertical take-off and landing fixed-wing unmanned aerial vehicle (UAV), comprising a frame and vertical take-off propellers. Four sets of vertical take-off propellers are installed at equal intervals on the top side wall of the frame. A rocket booster is installed at the center of the top of the frame. A forward propeller is installed on the side wall of the frame. Cabins are installed on both sides of the frame. Side plates are provided on the exterior of each cabin. A rotating sleeve is installed on the end of each side plate near the cabin. Servo motors are installed on the side walls of each cabin. A rotating column is installed at the output end of each servo motor. The rotating column extends into the interior of the cabin and is movably connected to it. The rotating column is connected to the rotating sleeve. A first connecting shaft is symmetrically and movably installed inside the frame. A second connecting shaft is movably installed on the side of the frame near the first connecting shaft.

[0008] Preferably, the surface of the first connecting shaft is fitted with an electric push rod, and the surface of the second connecting shaft is fitted with a curved arm. The electric push rod and the curved arm extend into the interior of the cabin, and the output end of the electric push rod is movably mounted with a rotating shaft.

[0009] Preferably, all the electric push rods are movably connected to the curved arm via a rotating shaft, and each curved arm is equipped with a stepper motor on its side wall, with a worm gear installed at the output end of each stepper motor.

[0010] Preferably, an L-shaped arm is movably fitted at the end of the curved arm away from the second connecting shaft, a rotating shaft is installed on the side wall of the L-shaped arm, a worm gear is fitted on the side of the rotating shaft away from the L-shaped arm, the worm meshes with the worm gear, a support column is provided on the outside of the L-shaped arm, and a damping shock absorber is provided on the outside of the support column.

[0011] Preferably, the damping shock absorber is equipped with wheels on its exterior, and the end of the L-shaped arm away from the rotation axis is movably fitted with a first shaft.

[0012] Preferably, the L-shaped arm is movably connected to the support column via a first shaft, and a second shaft is movably installed on the end of the support column away from the first shaft.

[0013] Preferably, the support column is movably connected to the wheel via a second axle, and a fourth axle is movably fitted on the side wall of the L-shaped arm.

[0014] Preferably, a third shaft is movably fitted on the side wall of each support column, and each damping shock absorber is movably connected to the L-shaped arm via a fourth shaft, and each damping shock absorber is movably connected to the support column via the third shaft.

[0015] Compared with the prior art, the beneficial effects of this utility model are: the UAV not only realizes the convenient forward flight of the UAV after vertical take-off, increasing the initial speed during forward flight, but also facilitates the convenient folding and unfolding of the landing gear, facilitates elastic buffer protection during landing, reduces the vibration amplitude during landing, and extends the service life of the UAV. Attached Figure Description

[0016] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0017] Figure 2 This is a front view structural diagram of the present utility model;

[0018] Figure 3 This is a three-dimensional structural diagram of the cabin of this utility model;

[0019] Figure 4 This is a three-dimensional structural diagram of the electric push rod of this utility model;

[0020] Figure 5 This is a three-dimensional structural diagram of the curved arm of this utility model;

[0021] Figure 6 This is a three-dimensional structural diagram of the damping shock absorber of this utility model;

[0022] Figure 7 This is a three-dimensional structural diagram of the worm gear of this utility model.

[0023] In the diagram: 1. Frame; 2. Vertical propeller; 3. Rocket booster; 4. Cabin; 5. Side plate; 6. Rotating column; 7. Rotating sleeve; 8. Servo motor; 9. First connecting shaft; 10. Electric push rod; 11. Second connecting shaft; 12. Bending arm; 13. Rotating shaft; 14. Stepper motor; 15. Worm gear; 16. Rotating shaft; 17. Worm wheel; 18. L-shaped arm; 19. First shaft; 20. Support column; 21. Second shaft; 22. Wheel; 23. Damping shock absorber; 24. Third shaft; 25. Fourth shaft; 26. Forward propeller. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0025] Please see Figure 1-7 The present invention provides an embodiment of a vertical take-off and landing fixed-wing unmanned aerial vehicle (UAV), comprising a frame 1 and vertical take-off propellers 2. Four sets of vertical take-off propellers 2 are installed at equal intervals on the top side wall of the frame 1. A rocket booster 3 is installed at the center of the top of the frame 1. A forward propeller 26 is installed on the side wall of the frame 1. A cabin 4 is installed on both sides of the frame 1. A side plate 5 is provided on the outside of the cabin 4. A rotating sleeve 7 is installed on the end of the side plate 5 near the cabin 4. A servo motor 8 is installed on the side wall of the cabin 4. A rotating column 6 is installed at the output end of the servo motor 8. The rotating column 6 extends into the interior of the cabin 4 and is movably connected thereto. The rotating column 6 is connected to the rotating sleeve 7. A first connecting shaft 9 is symmetrically and movably installed inside the frame 1. A second connecting shaft 11 is movably installed on the side of the frame 1 near the first connecting shaft 9.

[0026] When flying a VTOL fixed-wing UAV, the servo motor 8 is activated. Supported by the cabin 4, the servo motor 8 drives the rotating column 6 to rotate. The rotating column 6 drives the rotating sleeve 7 and the side plate 5 to rotate around the rotating column 6 as the axis. The side plate 5 acts as a seal for the cabin 4. Multiple sets of VTOL propellers 2 are activated, allowing the UAV to rise to the required height. When forward flight is required, the rocket booster 3 is activated. Supported by the frame 1, the rocket booster 3 drives the frame 1 forward, increasing the initial velocity during forward flight. When the rocket booster 3 runs out of fuel, the forward propeller 26 is activated, allowing the forward propeller 26 to drive the frame 1 into flight. This facilitates convenient flight of the UAV, enabling the UAV to be easily propelled forward after vertical takeoff, increasing the initial velocity during forward flight, and improving the convenience of propelling the UAV forward after vertical takeoff.

[0027] Electric push rods 10 are mounted on the surface of the first connecting shaft 9, and curved arms 12 are mounted on the surface of the second connecting shaft 11. The electric push rods 10 and curved arms 12 extend into the interior of the cabin 4, and a rotating shaft 13 is movably installed at the output end of the electric push rods 10.

[0028] All electric push rods 10 are movably connected to the curved arm 12 via a rotating shaft 13. Each curved arm 12 is equipped with a stepper motor 14 on its side wall, and each stepper motor 14 is equipped with a worm gear 15 at its output end.

[0029] L-shaped arms 18 are movably mounted on the end of the curved arm 12 away from the second connecting shaft 11. Rotating shafts 16 are installed on the side walls of the L-shaped arms 18. Worm gears 17 are mounted on the side of the rotating shafts 16 away from the L-shaped arms 18. The worm 15 meshes with the worm gears 17. Support columns 20 are provided on the outside of the L-shaped arms 18. Damping shock absorbers 23 are provided on the outside of the support columns 20.

[0030] All damping shock absorbers 23 are equipped with wheels 22 on their exterior. The end of the L-shaped arm 18 away from the rotating shaft 16 is movably fitted with a first shaft 19. The L-shaped arm 18 is movably connected to the support column 20 through the first shaft 19. The end of the support column 20 away from the first shaft 19 is movably fitted with a second shaft 21. The support column 20 is movably connected to the wheel 22 through the second shaft 21. The side wall of the L-shaped arm 18 is movably fitted with a fourth shaft 25.

[0031] The side walls of the support column 20 are all equipped with a third shaft 24, and the damping shock absorbers 23 are all movably connected to the L-shaped arm 18 through the fourth shaft 25. The damping shock absorbers 23 are all movably connected to the support column 20 through the third shaft 24.

[0032] As the drone descends, servo motor 8 is activated, causing side plate 5 and rotating sleeve 7 to rotate to an angle with cabin 4, allowing wheel 22 to be removed from the cabin. Electric push rod 10 is activated, and supported by first connecting shaft 9, it drives rotating shaft 13 to move. Supported by second connecting shaft 11, rotating shaft 13 drives bent arm 12, L-shaped arm 18, support column 20, damping shock absorber 23, and wheel 22 to rotate around second connecting shaft 11. Stepper motor 14 is activated, and supported by bent arm 12, it drives worm gear 15 to rotate. With worm gear 15 meshing with worm wheel 17, worm gear 15 drives worm wheel 17 to rotate, which in turn drives rotating shaft 16, L-shaped arm 18, support column 20, wheel 22, and damping shock absorber 23 to rotate at a certain angle. The landing gear is positioned so that the wheels 22 make contact with the ground. When the wheels 22 make contact with the ground, the ground exerts a rebound force on the wheels 22 and the UAV. With the support of the support column 20, the wheels 22 transmit the force to the damping shock absorber 23 through the third shaft 24. The damping shock absorber 23 buffers the force and transmits the remaining small force after buffering to the frame 1 through the fourth shaft 25. This facilitates the buffering of the rebound force. When the landing gear needs to be retracted, the stepper motor 14 and the electric push rod 10 are opened in the reverse direction to facilitate the wheels 22 entering the interior of the cabin 4. This prevents the landing gear from being exposed and affecting the flight attitude. This enables the UAV to conveniently fold and unfold the landing gear, facilitates elastic buffering protection during landing, reduces the vibration amplitude during landing, and extends the service life of the UAV.

[0033] Working principle: When the VTOL fixed-wing UAV is in flight, the servo motor 8 drives the rotating column 6 to rotate. The rotating column 6 drives the rotating sleeve 7 and the side plate 5 to rotate around the rotating column 6 as the axis. The side plate 5 acts as a seal for the cabin 4. Multiple sets of VTOL propellers 2 are opened, allowing the UAV to rise to the required height. When forward flight is required, the rocket booster 3 drives the frame 1 forward, increasing the initial velocity. When the rocket booster 3 runs out of fuel, the forward propeller 26 is opened, allowing the forward propeller 26 to drive the frame 1 in flight. When the UAV is falling, the servo motor 8 is activated, causing the side plate 5 and the rotating sleeve 7 to rotate to form a certain angle with the cabin 4, allowing the wheels 22 to be removed from the cabin. The electric push rod 10 drives the rotating shaft 13 to move. Supported by the second connecting shaft 11, the rotating shaft 13 drives the curved arm 12, the L-shaped arm 18, the support column 20, and the damping shock absorber 23. The wheel 22 rotates around the second connecting shaft 11. The stepper motor 14 drives the worm gear 15 to rotate, which in turn drives the worm wheel 17 to rotate. The worm wheel 17 drives the rotating shaft 16, L-shaped arm 18, support column 20, wheel 22, and damping shock absorber 23 to rotate at a certain angle, so that the wheel 22 contacts the ground. When the wheel 22 contacts the ground, the ground exerts a rebound force on the wheel 22 and the drone. With the support of the support column 20, the wheel 22 transmits the force to the damping shock absorber 23 through the third shaft 24. The damping shock absorber 23 buffers the force and transmits the remaining small force after buffering to the frame 1 through the fourth shaft 25, which facilitates the buffering of the rebound force. When the landing gear needs to be retracted, the stepper motor 14 and electric push rod 10 are opened in the opposite direction to facilitate the wheel 22 entering the interior of the cabin 4, so as to prevent the landing gear from being exposed and affecting the flight attitude, thus completing the operation of the drone.

Claims

1. A vertical take-off and landing fixed-wing unmanned aerial vehicle, characterized in that: The system includes a frame (1) and vertical propellers (2). Four sets of vertical propellers (2) are installed at equal intervals on the top side wall of the frame (1). A rocket booster (3) is installed at the center of the top of the frame (1). A forward propeller (26) is installed on the side wall of the frame (1). A cabin (4) is installed on both sides of the frame (1). Side plates (5) are provided on the outside of each cabin (4). A rotor is installed on the side plate (5) near the cabin (4). The rotating sleeve (7) is equipped with servo motors (8) on the side walls of the cabin (4). The output end of each servo motor (8) is equipped with a rotating column (6). The rotating column (6) extends into the interior of the cabin (4) and is movably connected thereto. The rotating column (6) is connected to the rotating sleeve (7). The first connecting shaft (9) is symmetrically and movably installed inside the frame (1). The second connecting shaft (11) is movably installed on the side of the frame (1) near the first connecting shaft (9).

2. The vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 1, characterized in that: The surface of the first connecting shaft (9) is fitted with an electric push rod (10), and the surface of the second connecting shaft (11) is fitted with a bent arm (12). The electric push rod (10) and the bent arm (12) extend into the interior of the cabin (4). The output end of the electric push rod (10) is movably mounted with a rotating shaft (13).

3. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 2, characterized in that: All electric push rods (10) are movably connected to the curved arm (12) via a rotating shaft (13). Each curved arm (12) is equipped with a stepper motor (14) on its side wall, and each stepper motor (14) is equipped with a worm gear (15) at its output end.

4. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 3, characterized in that: The end of each curved arm (12) away from the second connecting shaft (11) is movably fitted with an L-shaped arm (18). A rotating shaft (16) is installed on the side wall of each L-shaped arm (18). A worm gear (17) is fitted on the side of the rotating shaft (16) away from the L-shaped arm (18). The worm (15) meshes with the worm gear (17). A support column (20) is provided on the outside of each L-shaped arm (18). A damping shock absorber (23) is provided on the outside of each support column (20).

5. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 4, characterized in that: The damping shock absorber (23) is equipped with wheels (22) on its exterior, and the L-shaped arm (18) is movably fitted with a first shaft (19) at the end away from the rotating shaft (16).

6. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 5, characterized in that: The L-shaped arm (18) is movably connected to the support column (20) via the first shaft (19), and the end of the support column (20) away from the first shaft (19) is movably equipped with a second shaft (21).

7. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 6, characterized in that: The support column (20) is movably connected to the wheel (22) via the second shaft (21), and the side wall of the L-shaped arm (18) is movably fitted with a fourth shaft (25).

8. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 7, characterized in that: The side walls of the support column (20) are all fitted with a third shaft (24), and the damping shock absorbers (23) are all movably connected to the L-shaped arm (18) through the fourth shaft (25). The damping shock absorbers (23) are all movably connected to the support column (20) through the third shaft (24).

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