Vertical take-off and landing fixed-wing unmanned aerial vehicle

Abstract

The utility model provides a vertical take-off and landing fixed-wing unmanned aerial vehicle, and belongs to the technical field of fixed-wing unmanned aerial vehicles. The linkage type power mechanism comprises a fixed pipe, a first rocker arm, a driving motor and a propeller; the tilting steering engine, the second rocker arm, the servo connecting rod, the third rocker arm, the first undercarriage connecting rod, the second undercarriage connecting rod and the landing foot stand are arranged; by controlling the tilting steering engine to change the rotation direction of the propeller and controlling the switch of the driving motor, the fixed-wing unmanned aerial vehicle changes the flight mode, so that the unmanned aerial vehicle can perform operations such as lifting, hovering, in-situ turning around and high-speed level flight; the problems that the requirement of a fixed-wing unmanned aerial vehicle for a flight site is high, and a multi-rotor unmanned aerial vehicle is low in flight speed and short in endurance time are solved, and the environment applicability and the cruising speed of the vertical take-off and landing fixed-wing unmanned aerial vehicle on the market are further improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of fixed-wing unmanned aerial vehicles, and in particular relates to a vertical take-off and landing fixed-wing unmanned aerial vehicle. Background Art

[0002] Today's drone models are mainly fixed-wing and quad-rotor, and some drones are vertical take-off and landing fixed-wing drones; fixed-wing drones have strong endurance and long flight distance, but their take-off and landing methods are mainly through runway taxiing or catapult take-off, and the turning radius during flight is large, which has high requirements for flight sites and flight technology; multi-rotor drones use vertical take-off and landing, and have relatively low requirements for flight sites, but their endurance is weak and the flight speed is slow, which is not suitable for large-scale and long-term operation scenarios;

[0003] Existing vertical take-off and landing fixed-wing UAV technology: CN210391552U: It mainly consists of a fixed-wing fuselage and wings through a fixed tube extending forward arranged on the wing, and a tilt-rotor servo is fixedly installed on it. There is a rotating shaft at the front end, and a motor seat and a swing arm are fixedly connected to the rotating shaft. The swing arm is hinged to one end of the connecting rod, and the connecting rod is hinged to the output rotating arm of the tilt-rotor servo. The tilt-rotor is fixedly installed on the motor seat, and a fixed rotor is installed at the tail of the aircraft; the multi-rotor system of the aircraft consists of three rotors, with poor stability. A take-off bracket is required during take-off, otherwise the rear fixed rotor will touch the ground and wear out, and when switching to fixed mode flight, the rear fixed rotor does not participate in the flight power provision as a power system, which increases the resistance and weight of the aircraft. Utility Model Content

[0004] The utility model aims at solving the problems in the prior art and provides a vertical take-off and landing fixed-wing unmanned aerial vehicle.

[0005] In order to achieve the above purpose, the technical solution adopted in this application is:

[0006] A vertical take-off and landing fixed-wing UAV comprises a fuselage, wherein two wings are fixedly and symmetrically connected to the middle of the fuselage, a tail is arranged at the rear end of the fuselage, the tail comprises a vertical tail and a horizontal tail, the vertical tail is fixedly connected to the rear end of the fuselage, and two horizontal tails are arranged, which are respectively fixedly mounted at the left and right ends of the vertical tail; and a linkage power mechanism is also included, which is fixedly connected to the wings.

[0007] Preferably, the linkage power mechanism includes a fixed tube, a first rocker arm, a drive motor and a propeller, the fixed tube is in the shape of a quadrangular prism; the fixed tube is fixedly connected to the bottom surface of the wing, and the fixed tube is arranged vertically to the wing; the front and rear ends of the top surface of the fixed tube are respectively rotatably connected to the first rocker arm, the top surface of the first rocker arm is fixedly installed with the drive motor, and the propeller is detachably installed on the drive motor.

[0008] Preferably, it also includes a landing gear mechanism, which includes a tilting servo, a second rocker arm, a servo connecting rod, a third rocker arm, a first landing gear connecting rod, a second landing gear connecting rod and a landing foot; a mounting hole is opened on the outer side surface of the fixed tube at a quarter of the distance from the back to the front, a tilting servo is arranged in the mounting hole, the output end of the tilting servo is arranged outward along the mounting hole, the output end of the tilting servo is fixedly connected to the second rocker arm, the second rocker arm is rotatably connected to the servo connecting rod through a rotating shaft, and the servo connecting rod is away from itself and the first One end of the two rocker arms is connected to a third rocker arm rotatably connected to the outer side surface of the fixed tube at three quarters from the rear to the front, and the third rocker arm is rotatably connected to the first rocker arm through a rotating shaft; the front end of the servo connecting rod is rotatably connected to the top end of the first landing gear connecting rod through a rotating shaft, and the second landing gear connecting rod is fixedly connected to the bottom surface of the fixed tube at one quarter from the rear to the front through a rotating shaft; the first landing gear connecting rod is hinged in the middle of the second landing gear connecting rod, and the bottom ends of the first landing gear connecting rod and the second landing gear connecting rod are rotatably installed with landing legs.

[0009] Preferably, the fuselage has a built-in battery compartment, a payload compartment and a flight controller, and the flight controller is electrically connected to the drive motor and the tilting servo respectively.

[0010] Preferably, the flight controller is connected to a radio station on the ground via wireless communication of a remote controller receiver.

[0011] Compared with the prior art, the advantages and positive effects of the utility model are:

[0012] The utility model discloses a vertical take-off and landing fixed-wing unmanned aerial vehicle, which is provided with a linkage power mechanism including a fixed tube, a first rocker arm, a driving motor and a propeller, and a tilting servo, a second rocker arm, a servo connecting rod, a third rocker arm, a first landing gear connecting rod, a second landing gear connecting rod and a landing footrest. By controlling the tilting servo to change the rotation direction of the propeller and controlling the switch of the driving motor, the fixed-wing unmanned aerial vehicle changes its flight mode, so that the unmanned aerial vehicle can perform operations such as lifting, hovering, turning around on the spot and high-speed level flight. The utility model solves the problems that the fixed-wing unmanned aerial vehicle has high requirements for the flight site and the multi-rotor unmanned aerial vehicle has slow flight speed and short endurance time, and further improves the environmental applicability and cruising speed of the vertical take-off and landing fixed-wing unmanned aerial vehicles on the market. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0014] Figure 1It is a schematic diagram of the structure of the utility model;

[0015] Figure 2 It is a schematic diagram of the structure of the linkage power mechanism and the landing gear mechanism of the utility model;

[0016] Figure 3 It is a front view of the structure schematic diagram of the vertical take-off and landing mode fixed-wing mode of the linkage power mechanism and the landing gear mechanism of the utility model;

[0017] Figure 4 It is a front view of the schematic diagram of the fixed-wing mode structure of the linkage power mechanism and landing gear mechanism of the utility model;

[0018] In the above figures, 1. fuselage; 2. wing; 3. vertical tail; 4. horizontal tail; 5. linkage power mechanism; 6. fixed tube; 7. first rocker arm; 8. drive motor; 9. propeller; 10. tilting servo; 11. second rocker arm; 12. servo connecting rod; 13. third rocker arm; 14. first landing gear connecting rod; 15. second landing gear connecting rod; 16. landing gear. DETAILED DESCRIPTION

[0019] In order to more clearly understand the above-mentioned purpose, features and advantages of the utility model, the utility model is further described below in conjunction with the accompanying drawings and embodiments. It should be noted that the embodiments of the present application and the features in the embodiments can be combined with each other without conflict.

[0020] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways than those described herein. Therefore, the present invention is not limited to the specific embodiments of the following disclosure.

[0021] Embodiment 1, as Figures 1 to 3 As shown, a vertical take-off and landing fixed-wing UAV of the present application comprises a fuselage 1, wherein two wings 2 are fixedly and symmetrically connected to the middle of the fuselage 1, a tail wing is arranged at the rear end of the fuselage 1, and the tail wing comprises a vertical tail wing 3 and a horizontal tail wing 4, the vertical tail wing 3 is fixedly connected to the rear end of the fuselage 1, and two horizontal tail wing 4 are arranged, which are respectively fixedly mounted on the left and right ends of the vertical tail wing 3; further comprising a linkage power mechanism 5, wherein the linkage power mechanism 5 is fixedly connected to the wings 2; the fuselage 1, the wings 2 and the tail wing comprising the vertical tail wing 3 and the horizontal tail wing 4 are all standard fixed-wing UAV structures; the UAV built-in power machine adopts a four-rotor UAV structure;

[0022] The linkage power mechanism 5 includes a fixed tube 6, a first rocker arm 7, a drive motor 8 and a propeller 9, and the fixed tube 6 is in the shape of a quadrangular prism. In the present embodiment, two fixed tubes 6 are provided, and the length of the fixed tubes 6 is greater than the width of the wing 2. The middle parts of the top surfaces of the two fixed tubes 6 are respectively fixedly connected to the bottom surface of the wing 2, and the fixed tubes 6 are vertically arranged to the wing 2. The front and rear ends of the top surface of the fixed tube 6 are respectively rotatably connected to the first rocker arm 7, and the top surface of the first rocker arm 7 is fixedly installed with the drive motor 8, and the propeller 9 is detachably installed on the drive motor 8. The drive motor adopts an outer rotor brushless motor, and its model is XDRC 2807.

[0023] The vehicle also includes a landing gear mechanism, which includes a tilting servo 10, a second rocker arm 11, a servo link 12, a third rocker arm 13, a first landing gear link 14, a second landing gear link 15 and a landing footrest 16; a mounting hole is provided on the outer side of the fixed tube 6 at a quarter of the distance from the back to the front, and a tilting servo 10 is provided in the mounting hole, and an output end of the tilting servo 10 is arranged outward along the mounting hole, and a second rocker arm 11 is fixedly connected to the output end of the tilting servo 10, and the second rocker arm 11 is rotatably connected to the servo link 12 through a rotating shaft, and the servo link 12 is connected away from the end thereof connected to the second rocker arm 11 There is a third rocker arm 13 rotatably connected to the outer side surface of the fixed tube 6 at three quarters from the back to the front, and the third rocker arm 13 is rotatably connected to the first rocker arm 7 through a rotating shaft; the front end of the servo connecting rod 12 is connected to the top of the first landing gear connecting rod 14 through a rotating shaft, and the second landing gear connecting rod 15 is fixedly connected to the bottom surface of the fixed tube 6 from the back to the front quarter through a rotating shaft; the first landing gear connecting rod 14 is hinged to the middle of the second landing gear connecting rod 15, and the bottom ends of the first landing gear connecting rod 14 and the second landing gear connecting rod 15 are rotatably installed with a landing tripod 16; when in use, when the UAV needs to take off in a vertical take-off and landing mode, ... bottom of the second landing gear connecting rod 15. The landing gear link 14 is close to the top of the second landing gear link 15, the fixed tube 6 is lifted, and then the wing 2 is lifted. In this process, the drive motor 8 connected to the propeller 9 on the first rocker arm 7 is set perpendicular to the ground. At this time, the propeller 9 rotates to generate a vertical downward lift so that the UAV can take off or land vertically. At the same time, the setting of the vertical take-off and landing mode can achieve hovering and turning on the spot; when the UAV flies to a certain height, the flight mode of the UAV can be switched to the fixed-wing mode. At this time, the tilt-steering servo 10 receives the signal and outputs the signal to rotate the first rocker arm 7, so that the drive motor 8 connected to the propeller 9 is rotated. The aircraft 8 is arranged horizontally with the ground, and the distance between the top ends of the first landing gear link 14 and the second landing gear link 15 is lengthened, so that the landing gear mechanism is retracted, and the propeller 9 generates a backward thrust to make the UAV enter a high-speed level flight state. At the same time, the two rear propellers 9 stop rotating and the landing gear mechanism is retracted, which can reduce the air resistance during the overall flight. At this time, the lift of the UAV is provided by the wing 2. This mode can greatly save the energy consumption required for the flight of the UAV; at this time, if a higher-speed flight is required, the two propellers 9 at the rear end of the fixed tube 6 can be rotated in the opposite direction to provide a backward thrust to further increase the flight speed of the UAV;

[0024] The fuselage 1 has a battery compartment, a payload compartment and a flight controller built in, and the flight controller is electrically connected to the drive motor 8 and the tilting servo 10 respectively; the model of the flight controller is f405WING, and it has a built-in barometer, which can determine the flight altitude of the drone by measuring the air pressure; the flight controller measures the airspeed through an airspeed meter, and the airspeed meter adopts a digital airspeed meter, and the airspeed meter is integrated with a compass, and the model is BZ181. The airspeed meter is arranged at the front end of the fuselage 1 to prevent the airspeed meter from being affected by the propeller airflow;

[0025] The flight controller is connected to a radio station on the ground through wireless communication of a remote controller receiver; the remote controller receiver model is Elrs Nano crsf, and the flight controller acts through the signal transmitted by the remote controller to the remote controller receiver, and the remote controller model is Radiomaster TX12.

[0026] The above description is only a preferred embodiment of the present invention and does not limit the present invention in other forms. Any technician familiar with the profession may use the technical content disclosed above to change or modify it into an equivalent embodiment with equivalent changes and apply it to other fields. However, any simple modification, equivalent change and modification made to the above embodiment based on the technical essence of the present invention without departing from the content of the technical solution of the present invention still falls within the protection scope of the technical solution of the present invention.

Claims

1. A vertical take-off and landing fixed-wing unmanned aerial vehicle, comprising a fuselage (1), wherein two wings (2) are fixedly and symmetrically connected to the middle of the fuselage (1), and a tail wing is arranged at the rear end of the fuselage (1), wherein the tail wing comprises a vertical tail wing (3) and a horizontal tail wing (4), wherein the vertical tail wing (3) is fixedly connected to the rear end of the fuselage (1), and two horizontal tail wing (4) are arranged and fixedly mounted on the left and right ends of the vertical tail wing (3), respectively; characterized in that: It also includes a linkage-type power mechanism (5), wherein the linkage-type power mechanism (5) is fixedly connected to the wing (2).

2. A vertical take-off and landing fixed-wing UAV according to claim 1, characterized in that: The linkage power mechanism (5) comprises a fixed tube (6), a first rocker arm (7), a drive motor (8) and a propeller (9); the fixed tube (6) is in the shape of a quadrangular prism; the fixed tube (6) is fixedly connected to the bottom surface of the wing (2), and the fixed tube (6) is arranged perpendicular to the wing (2); the front and rear ends of the top surface of the fixed tube (6) are rotatably connected to the first rocker arm (7), the top surface of the first rocker arm (7) is fixedly mounted with the drive motor (8), and the propeller (9) is detachably mounted on the drive motor (8).

3. A vertical take-off and landing fixed-wing UAV according to claim 2, characterized in that: The invention also comprises a landing gear mechanism, wherein the landing gear mechanism comprises a tilting servo (10), a second rocker arm (11), a servo connecting rod (12), a third rocker arm (13), a first landing gear connecting rod (14), a second landing gear connecting rod (15) and a landing foot frame (16); a mounting hole is provided on the outer side surface of the fixing tube (6) at a quarter of the distance from the rear to the front, a tilting servo (10) is provided in the mounting hole, an output end of the tilting servo (10) is arranged outward along the mounting hole, a second rocker arm (11) is fixedly connected to the output end of the tilting servo (10), the second rocker arm (11) is rotatably connected to the servo connecting rod (12) via a rotating shaft, and the servo connecting rod (12) is away from itself and is connected to the servo connecting rod (12). One end of the second rocker arm (11) is connected to a third rocker arm (13) which is rotatably connected to the outer side surface of the fixed tube (6) at a position three quarters from the rear to the front, and the third rocker arm (13) is rotatably connected to the first rocker arm (7) via a rotating shaft; the front end of the servo connecting rod (12) is rotatably connected to the top end of the first landing gear connecting rod (14) via a rotating shaft, and the second landing gear connecting rod (15) is fixedly connected to the bottom surface of the fixed tube (6) at a position one quarter from the rear to the front via a rotating shaft; the first landing gear connecting rod (14) and the second landing gear connecting rod (15) are hinged at the middle part, and the bottom ends of the first landing gear connecting rod (14) and the second landing gear connecting rod (15) are rotatably mounted with a landing footrest (16).

4. A vertical take-off and landing fixed-wing UAV according to claim 3, characterized in that: The fuselage (1) has a built-in battery compartment, a payload compartment and a flight controller, and the flight controller is electrically connected to the drive motor (8) and the tilting servo (10) respectively.

5. A vertical take-off and landing fixed-wing UAV according to claim 4, characterized in that: The flight controller is connected to a radio station on the ground via wireless communication of a remote controller receiver.

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