Petrol-electric hybrid vertical-lifting level-flying unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an oil-electric hybrid vertical-lifting level-flying unmanned aerial vehicle. Comprising a fuselage and wings, the wings are symmetrically arranged on the two sides of the fuselage, and the wings are provided with vertical take-off and landing power units through rotating mechanisms; the vertical take-off and landing power unit comprises a front vertical flat-flying rotor device and a rear vertical flat-flying rotor device, the front vertical flat-flying rotor device is arranged upwards perpendicular to the wings, and the rear vertical flat-flying rotor device is arranged downwards perpendicular to the wings; the rotating mechanism comprises a driving wheel, a driven wheel, a transmission device and a driver, an output shaft of the driver is connected with a center shaft of the driving wheel, the driving wheel is connected with the driven wheel through the transmission device, and a vertical lifting power unit is arranged on the driven wheel. The vertical take-off and landing power unit can take off and land vertically or hover in the air and can fly parallel to the ground, the utilization rate of the vertical take-off and landing power unit is improved, and the vertical take-off and landing power unit has the positive effects of increasing the endurance and reducing the waste weight of the unmanned aerial vehicle.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a hybrid electric vertical takeoff and horizontal flight UAV. Background Technology

[0002] Vertical takeoff and landing (VTOL) drones are widely used in emergency rescue, security patrols, and remote sensing aerial surveys. During takeoff and landing, the wings of a VTOL drone are perpendicular to the ground, and the thrust provided by its engine enables it to take off and land vertically or hover in the air. While in flight, the ailerons rotate the fuselage so that the wings are parallel to the ground. Currently, invention patent application number 2021108732046 discloses a VTOL drone and its control method, which includes: a fuselage, a VTOL power unit, a level flight power unit, and a tilting mechanism; the VTOL power unit is fixed to the fuselage; the level flight power unit is connected to the fuselage through the tilting mechanism, which drives the level flight power unit to tilt horizontally. By adding a level flight power unit at the tail of the aircraft, the tilting rudder drives the tilting motor support to tilt, changing the horizontal direction of the thrust (pull) provided by the level flight power system to generate a yaw moment and improve yaw control capability. However, its vertical takeoff and landing power unit can only provide thrust to enable it to take off and land vertically or hover in the air, but cannot fly parallel to the ground, thus not increasing its range. Utility Model Content

[0003] The purpose of this invention is to provide a hybrid electric vertical takeoff and landing (VTOL) drone, which enables the VTOL power unit to take off and land vertically or hover in the air, and also to fly parallel to the ground, thereby increasing its range.

[0004] The hybrid electric vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) provided by this utility model includes a fuselage and wings. Wings are symmetrically arranged on both sides of the fuselage. A VTOL power unit is mounted on each wing via a rotating mechanism. The VTOL power unit includes a front VTOL rotor and a rear VTOL rotor. The front VTOL rotor is positioned vertically upwards relative to the wing, and the rear VTOL rotor is positioned vertically downwards relative to the wing. The rotating mechanism includes a drive wheel, a driven wheel, a transmission device, and a drive motor. The output shaft of the drive motor is connected to the central shaft of the drive wheel. The drive wheel is connected to the driven wheel via the transmission device, and the VTOL power unit is mounted on the driven wheel.

[0005] Furthermore, both the front VTOL level flight rotor device and the rear VTOL level flight rotor device include a hybrid electric drone engine, a propeller, and a mounting base. The front end of the hybrid electric drone engine is equipped with a propeller via a central screw shaft and a propeller mount, and the rear end of the hybrid electric drone engine is mounted on the tilting rotor beam of the wing via a mounting base.

[0006] Furthermore, a fairing is provided on the outer side of the tilting rotor beam, and the fairing is arranged parallel to the fuselage.

[0007] Furthermore, the number of vertical take-off and landing power units is 2, 4, 6, 8, 10 or 12, and the vertical take-off and landing power units are symmetrically arranged on the tilt rotor pylon at the lower end of the wing.

[0008] Furthermore, mounting frames are provided at both the front and rear ends of the tilting rotor beam; the base of the mounting frame is provided with a drive wheel and a driven wheel, a vertical limit plate is provided above the mounting frame, and a horizontal flight limit plate is provided below the mounting frame.

[0009] Furthermore, bearings are provided at both ends of the driven wheel, and the central shaft of the driven wheel passes through the bearings and is fixed on the mounting bracket.

[0010] Furthermore, the drive motor is either a servo motor or a steering motor.

[0011] Furthermore, the transmission device can be any one of a synchronous belt, chain, gear, or ball joint.

[0012] Furthermore, the drive wheel can be any one of a sprocket, a gear, or a rocker arm.

[0013] The hybrid electric vertical takeoff and horizontal flight UAV provided by this utility model has the following beneficial effects:

[0014] 1. When the UAV needs to perform vertical take-off and landing or hover in the air, the rotating mechanism of this utility model ensures that the vertical take-off and landing power unit is perpendicular to the wing. The front vertical take-off and level flight rotor is positioned vertically upwards and perpendicular to the wing, while the rear vertical take-off and level flight rotor is positioned vertically downwards. The front vertical take-off and level flight rotor provides upward thrust, and the rear vertical take-off and level flight rotor enables the UAV to perform vertical take-off and landing or hover in the air.

[0015] 2. When the UAV needs to fly horizontally, the rotating mechanism of this invention positions the vertical take-off and landing (VTOL) power unit parallel to the wing. The front VTOL horizontal flight rotor is positioned parallel to the wing and forward, while the rear VTOL horizontal flight rotor is positioned parallel to the wing and backward. The front VTOL horizontal flight rotor provides forward thrust, and the rear VTOL horizontal flight rotor provides forward thrust, enabling the UAV to fly parallel to the ground.

[0016] Therefore, the vertical take-off and landing power unit of this utility model can not only take off and land vertically or hover in the air, but also fly parallel to the ground, which improves the utilization rate of the vertical take-off and landing power unit and has the positive effect of increasing endurance and reducing the weight of the UAV. Attached Figure Description

[0017] The accompanying drawings disclose specific embodiments of this utility model, wherein,

[0018] Figure 1 This is a schematic diagram of the structure of this utility model when hovering;

[0019] Figure 2 This is a schematic diagram of the structure of this utility model during level flight;

[0020] Figure 3 This is a schematic diagram of the vertical take-off and landing power unit of this utility model during hovering;

[0021] Figure 4 This is a schematic diagram of the vertical takeoff and landing power unit of this utility model during level flight;

[0022] Figure 5 This is a schematic diagram of the rotating mechanism during hovering of this utility model;

[0023] Figure 6 This is a schematic diagram of the rotating mechanism during level flight of this utility model;

[0024] Figure 7 This is a structural cross-sectional view of the rotating mechanism during hovering of this utility model;

[0025] Figure 8 This is a structural cross-sectional view of the rotating mechanism during level flight of this utility model;

[0026] Figure label:

[0027] 1. Fuselage;

[0028] 2. Wing; 21. Tiltrotor beam; 22. Fairing; 23. Mounting bracket; 24. Vertical take-off limit plate; 25. Level flight limit plate;

[0029] 3. Vertical take-off and landing power unit;

[0030] 4. Forward vertical takeoff and landing rotor assembly; 41. Hybrid electric unmanned aerial vehicle engine; 42. Propeller; 43. Mounted base;

[0031] 5. Rear-mounted horizontal flight rotor system;

[0032] 6. Rotating mechanism; 61. Driving wheel; 62. Driven wheel; 63. Transmission device; 64. Drive motor; 65. Bearing. Detailed Implementation

[0033] like Figure 1-8As shown, the hybrid electric vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) provided by this utility model includes a fuselage 1 and wings 2. Wings 2 are symmetrically arranged on both sides of the fuselage 1. Vertical takeoff and landing (VTOL) power units 3 are arranged on the wings 2 through a rotating mechanism 6. The VTOL power unit 3 includes a front VTOL rotor 4 and a rear VTOL rotor 5. The front VTOL rotor 4 is arranged vertically upward to the wings 2, and the rear VTOL rotor 5 is arranged vertically downward to the wings 2. The rotating mechanism 6 includes a drive wheel 61, a driven wheel 62, a transmission device 63, and a drive motor 64. The output shaft of the drive motor 64 is connected to the central shaft of the drive wheel 61. The drive wheel 61 is connected to the driven wheel 62 through the transmission device 63. The VTOL power unit 3 is arranged on the driven wheel 62.

[0034] When this invention is in use, if the UAV needs to take off and land vertically or hover in the air, the drive motor 64 is first started. The drive motor 64 drives the drive wheel 61 to rotate. The drive wheel 61 drives the driven wheel 62 to rotate under the action of the bearing 65 through the transmission device 63. The rotation mechanism 6 keeps the vertical take-off and landing power unit 3 in a state perpendicular to the wing 2, with the front vertical take-off and level flight rotor device 4 set vertically upward to the wing 2 and the rear vertical take-off and level flight rotor device 5 set vertically downward to the wing 2. Then, the vertical take-off and landing power unit 3 is started. The front vertical take-off and level flight rotor device 4 provides upward pull, and the rear vertical take-off and level flight rotor device 5 provides upward thrust. The front vertical take-off and level flight rotor device 4 and the rear vertical take-off and level flight rotor device 5 enable the UAV to take off and land vertically or hover in the air.

[0035] When the UAV needs to fly at level, the drive motor 64 is first activated. The drive motor 64 drives the drive wheel 61 to rotate, and the drive wheel 61 drives the driven wheel 62 to rotate under the action of the bearing 65 through the transmission device 63. The rotation mechanism 6 then positions the vertical take-off and landing power unit 3 parallel to the wing 2, with the front vertical take-off and level flight rotor 4 positioned forward parallel to the wing 2, and the rear vertical take-off and level flight rotor 5 positioned rearward parallel to the wing 2. Then, the vertical take-off and landing power unit 3 is activated. The front vertical take-off and level flight rotor 4 provides forward thrust, and the rear vertical take-off and level flight rotor 5 provides forward thrust, enabling the UAV to fly parallel to the ground.

[0036] The vertical take-off and landing power unit of this invention can take off and land vertically or hover in the air, and can also fly parallel to the ground, which improves the utilization rate of the vertical take-off and landing power unit, increases the endurance, and reduces the weight of the drone.

[0037] like Figure 1-8As shown, both the front VTOL rotor assembly 4 and the rear VTOL rotor assembly 5 include a hybrid electric unmanned aerial vehicle (UAV) engine 41, a propeller 42, and a mounting base 43. The propeller 42 is mounted on the front end of the hybrid electric UAV engine 41 via a central screw shaft and a propeller mount. The rear end of the hybrid electric UAV engine 41 is mounted on the tilting rotor beam 21 of the wing 2 via the mounting base 43. The front VTOL rotor assembly 4 and the rear VTOL rotor assembly 5 can take off and land vertically or hover in the air, and can also fly parallel to the ground, thus increasing endurance.

[0038] like Figure 1-8 As shown, a fairing 22 is provided on the outer side of the tilting rotor beam 21, and the fairing 22 is arranged parallel to the fuselage 1. The fairing 22 can prevent the UAV from being impacted and interfered with by airflow during flight, thereby increasing its endurance.

[0039] like Figure 1-8 As shown, the number of vertical takeoff and landing (VTOL) power units 3 is 2, 4, 6, 8, 10, or 12, meaning the number of forward VTOL rotor devices 4 is 2, 4, 6, 8, 10, or 12, and correspondingly, the number of rear VTOL rotor devices 5 is 2, 4, 6, 8, 10, or 12. The VTOL power units 3 are symmetrically arranged on the tilting rotor beam 21 at the lower end of the wing 2. The VTOL power units 3 are rationally configured according to the UAV model and structure, enabling the UAV to take off and land vertically or hover in the air, and also to fly parallel to the ground, thus increasing its endurance.

[0040] like Figure 1-8 As shown, mounting brackets 23 are provided at both the front and rear ends of the tilting rotor beam 21. A drive wheel 61 and a driven wheel 62 are mounted on the base of the mounting bracket 23. A vertical take-off limiting plate 24 is provided above the mounting bracket 23, and a level flight limiting plate 25 is provided below the mounting bracket 23. When the rotating mechanism 6 positions the vertical take-off and landing power unit 3 perpendicular to the wing 2, the vertical take-off limiting plate 24 effectively prevents the vertical take-off and landing power unit 3 from tilting. When the rotating mechanism 6 positions the vertical take-off and landing power unit 3 parallel to the wing 2, the level flight limiting plate 25 effectively prevents the vertical take-off and landing power unit 3 from drooping.

[0041] like Figure 5-6 As shown, bearings 65 are provided at both ends of the driven wheel 62. The central shaft of the driven wheel 62 passes through the bearings 65 and is fixed on the mounting bracket 23. The driven wheel 62 rotates under the action of the bearings 65, which can make the vertical take-off and landing power unit 3 perpendicular to the wing 2, enabling the UAV to take off and land vertically or hover in the air; or it can make the vertical take-off and landing power unit 3 parallel to the wing 2, enabling the UAV to fly parallel to the ground.

[0042] The drive motor 64 of this invention can be any one of a servo motor or a steering wheel. The transmission device 63 can be any one of a synchronous belt, chain, gear, or ball joint. The drive wheel 61 can be any one of a sprocket, gear, or rocker arm.

[0043] All the above components are installed, connected, or set up using common mechanical methods, such as welding, threaded connections, and screw connections. Furthermore, the specific structure, model, and coefficient indicators of all components are based on their own technologies, and any method that achieves the desired beneficial effect can be implemented. The hybrid electric drone engine 41 mentioned above is a common component on the market; upon purchase and use, it only needs to be connected according to the instruction manual purchased with it, so it will not be described in detail here.

[0044] The technical solution of this utility model is not limited to the scope of this utility model. All technical contents not described in detail in this utility model are known technologies.

Claims

1. A hybrid electric vertical takeoff and horizontal flight unmanned aerial vehicle (UAV), comprising a fuselage (1) and wings (2), wherein the wings (2) are symmetrically arranged on both sides of the fuselage (1), characterized in that, The wing (2) is equipped with a vertical take-off and landing power unit (3) via a rotating mechanism (6); the vertical take-off and landing power unit (3) includes a front vertical take-off and level flight rotor device (4) and a rear vertical take-off and level flight rotor device (5). The front vertical take-off and level flight rotor device (4) is arranged vertically upward to the wing (2), and the rear vertical take-off and level flight rotor device (5) is arranged vertically downward to the wing (2); the rotating mechanism (6) includes a drive wheel (61), a driven wheel (62), a transmission device (63), and a drive motor (64). The output shaft of the drive motor (64) is connected to the central shaft of the drive wheel (61). The drive wheel (61) is connected to the driven wheel (62) via the transmission device (63). The vertical take-off and landing power unit (3) is arranged on the driven wheel (62). The front vertical take-off and horizontal flight rotor device (4) and the rear vertical take-off and horizontal flight rotor device (5) both include a hybrid electric unmanned aerial vehicle engine (41), a propeller (42), and a fixed base (43). The front end of the hybrid electric unmanned aerial vehicle engine (41) is equipped with a propeller (42) through a central screw shaft and a propeller seat. The rear end of the hybrid electric unmanned aerial vehicle engine (41) is mounted on the tilting rotor beam (21) of the wing (2) through the fixed base (43). The tilt rotor beam (21) is provided with a fairing (22) on its outer side, and the fairing (22) is arranged parallel to the fuselage (1); the tilt rotor beam (21) is provided with a mounting bracket (23) at both the front and rear ends; the mounting bracket (23) is provided with a drive wheel (61) and a driven wheel (62) on its base; a vertical lift limit plate (24) is provided above the mounting bracket (23); and a level flight limit plate (25) is provided below the mounting bracket (23). The number of the vertical take-off and landing power units (3) is 2, 4, 6, 8, 10 or 12, and the vertical take-off and landing power units (3) are symmetrically arranged on the tilt rotor beam (21) at the lower end of the wing (2); The driven wheel (62) is provided with bearings (65) at both ends. The central shaft of the driven wheel (62) passes through the bearings (65) and is fixed on the mounting bracket (23). The drive motor (64) drives the drive wheel (61) to rotate. The drive wheel (61) drives the driven wheel (62) to rotate under the action of the bearing (65) through the transmission device (63). The rotating mechanism (6) makes the vertical take-off and landing power unit (3) perpendicular to the wing (2). The front vertical take-off and horizontal flight rotor device (4) is set upward perpendicular to the wing (2), and the rear vertical take-off and horizontal flight rotor device (5) is set downward perpendicular to the wing (2).

2. The hybrid electric vertical takeoff and horizontal flight UAV according to claim 1, characterized in that, The drive unit (64) is either a servo motor or a servo motor.

3. The hybrid electric vertical takeoff and horizontal flight UAV according to claim 1, characterized in that, The transmission device (63) can be any one of synchronous belt, chain, gear, or ball joint.

4. The hybrid electric vertical takeoff and horizontal flight UAV according to claim 1, characterized in that, The drive wheel (61) can be any one of a sprocket, a gear, or a rocker arm.

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