A vertical take-off and landing unmanned aerial vehicle with a rotor opening and closing type rectifying mechanism

Abstract

The application provides an opening and closing type rectifying mechanism of a rotor of an unmanned aerial vehicle, which comprises a rudder frame for fixing a rudder motor, a rudder motor, a rudder motor gear, a concentric gear, a connecting rod and a fairing. The rudder motor rotates through the rudder motor gear to drive the concentric gear, and then drives the connecting rod to rotate to drive the fairing to open and close. The application can realize the covering of the rotor of the vertical take-off and landing unmanned aerial vehicle, reduce the aerodynamic resistance of the horizontal flight of the vertical take-off and landing unmanned aerial vehicle, and improve the flight speed.

Description

Technical Field

[0001] This invention relates to a small vertical take-off and landing unmanned aerial vehicle (UAV) with a rotor opening and closing rectification mechanism. Background Technology

[0002] With the development of aviation technology, vertical takeoff and landing (VTOL) aircraft have gradually emerged on the historical stage. The precise definition of a VTOL aircraft is: capable of taking off / landing at zero speed, possessing hovering capability, and able to fly horizontally like a fixed-wing aircraft. Compared to conventional fixed-wing aircraft, it has vertical takeoff and landing capabilities, requiring less space for takeoff and landing; compared to traditional helicopters, it has the greater speed and range of a fixed-wing aircraft.

[0003] While vertical takeoff and landing (VTOL) aircraft offer the advantages mentioned above, they also suffer from drawbacks such as slow flight speed, overly complex structure, and difficulty in controlling transition states. These factors have contributed to the slow development of VTOL aircraft since their inception. The organization that filed this patent application focuses on addressing the problem of slow flight speed in VTOL aircraft. Summary of the Invention

[0004] According to one aspect of the present invention, a vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) is provided, characterized by comprising:

[0005] body,

[0006] The first and second wings, which are connected to the fuselage,

[0007] The first and second rectifier mechanisms are respectively externally mounted on the underside of the first and second wings.

[0008] The first and second vertical tails are respectively connected to the first and second rectifier mechanisms.

[0009] The horizontal tail connecting the first and second vertical tails,

[0010] Turbojet engines are mounted on the fuselage.

[0011] The first rectifier mechanism includes:

[0012] First and second motors,

[0013] The first and second rotors are driven by the first and second motors, respectively.

[0014] The first to fourth hinged panels are arranged with the first and second panels located in front of the first wing, and the third and fourth panels located behind the first wing.

[0015] First carbon nanotubes,

[0016] The first and second base plates are assembled onto the first carbon nanotube. The first and second base plates, along with the first to fourth opening / closing plates, are all arc-shaped plates with an angle of 120 degrees. The first and second opening / closing plates have the same length as the first base plate, and the third and fourth opening / closing plates have the same length as the second base plate. The radius of the arc-shaped plates of the first and second opening / closing plates is slightly larger than the radius of the first base plate, and the radius of the arc-shaped plates of the third and fourth opening / closing plates is slightly larger than the radius of the second base plate.

[0017] The first rectifier head cover is connected to the first carbon tube and the first base plate.

[0018] The lower fairing of the first wing is connected to the first wing.

[0019] The first vertical stabilizer is connected to the fairing, which is connected to the first vertical stabilizer.

[0020] The fairing opening and closing force transmission mechanism includes first to fourth opening and closing plates on both sides of the first base plate, which are fixed to the concentric circles of the arcs of the first and second base plates and can rotate around the center of these concentric circles, thereby realizing the closing and opening of the fairing.

[0021] in:

[0022] When the drone takes off, lands vertically, and / or hovers, the first and second rectifier mechanisms open, and the first to fourth rotors rotate to provide power.

[0023] When the drone is flying at high speed, the first and second rectifier mechanisms close to reduce the drag on the drone, while the turbojet engine starts to provide power, thereby increasing the drone's flight speed. Attached Figure Description

[0024] Figure 1 This is an overall shape drawing of a vertical take-off and landing unmanned aerial vehicle according to an embodiment of the present invention, wherein the openable rectifier mechanism is open.

[0025] Figures 2(A) and (B) are overall external views of a vertical take-off and landing unmanned aerial vehicle according to an embodiment of the present invention, wherein the open-close rectifier mechanism is closed.

[0026] Figure 3 This is an overall external view of the openable rectifier mechanism when it is closed, according to an embodiment of the present invention.

[0027] Figure 4 This is an overall external view of the open / closed rectifier mechanism in the open state according to an embodiment of the present invention.

[0028] Figure 5 This is a side view of the fairing closed according to the present invention.

[0029] Figure 6 This is a side view of the fairing opening process according to the present invention.

[0030] Figure 7 This is a side view of the fairing when it is open according to the present invention.

[0031] Figure 8 This is an overall external view of the open / closed rectifier mechanism according to the present invention in its open state.

[0032] Figures 9(A) and (B) are schematic diagrams of the fairing opening and closing force transmission mechanism according to the present invention.

[0033] Figure 10 A partial external view of the open / closed rectifier mechanism according to the present invention in its open state. Detailed Implementation

[0034] To address the issue of slow horizontal flight speed in existing vertical takeoff and landing (VTOL) drones, aerodynamic drag should be reduced. For VTOL drones, the rotors used for vertical takeoff and landing generate a large number of aerodynamic vortices during high-speed horizontal flight, resulting in significant flight drag and severely restricting the improvement of drone flight speed.

[0035] Therefore, a rectification mechanism should be designed for the rotor. This mechanism should enable the following: during vertical takeoff and landing and hovering, the rectification mechanism opens, allowing the four rotors to rotate at high speed, ensuring efficient and stable vertical takeoff and landing for the UAV; during high-speed horizontal flight, the rotors and motors stop rotating, and the rectification mechanism closes, reducing aerodynamic drag during high-speed flight. Simultaneously, this mechanism should also be simple in structure, lightweight, and highly stable.

[0036] The following describes specific embodiments of the present invention in conjunction with the accompanying drawings.

[0037] fairing shape design

[0038] An external view of a vertical take-off and landing unmanned aerial vehicle according to an embodiment of the present invention is shown below. Figure 1 As shown in Figure 2, the vertical takeoff and landing UAV includes a fuselage (26), wings (24,25), vertical tail (21,22), horizontal tail (23), landing gear (27), turbojet engine (36), first to fourth motors (32,33,34,35), first to fourth rotors (28,29,30,31), fairing (1,2), hinged plate (7,8,9,10,11,12,13,14), base plate (3,4,5,6), underwing fairing (15,16), and vertical tail connecting fairing (17,18).

[0039] The rectifier mechanism (see description below) is externally mounted on the lower part of the wings (24,25) to enable its opening and closing function. During vertical takeoff and landing or hovering of the UAV, the rectifier mechanism opens, and the first to fourth rotors (28,29,30,31) rotate to provide power. Figure 1When the UAV is flying at high speed, the rectifier mechanism closes (Figure 2(A) and (B)) to reduce the drag on the UAV, while the turbojet engine (36) starts to provide power and increase the flight speed of the UAV.

[0040] The fairing mainly includes the first and second fairing heads (1,2), the first to fourth pairs of hinged panels (7,8,9,10,11,12,13,14), the first to fourth bottom plates (3,4,5,6), the first and second underwing fairings (15,16), and the first and second vertical tail connecting fairings (17,18) (Figure 2). Figure 3 Each of the two wings (24, 25) has a pair of hinged plates at the front and rear. Each hinged plate (7, 8, 9, 10, 11, 12, 13, 14) has the same length as the corresponding base plate (3, 4, 5, 6), and both the hinged plate and the corresponding base plate are arc plates with an angle of 120 degrees. The radius of the arc plate of each hinged plate is slightly larger than the radius of the corresponding base plate. Figure 5 As shown in Figure 6.

[0041] like Figure 4 As shown, the first wing fairing (15) is connected to the first wing (24), and the first vertical tail fairing (17) is connected to the first vertical tail (21). The first and second base plates (3,5) are mounted on the first carbon fiber tube (19). The first fairing head (1) is connected to the first carbon fiber tube (19) and the first base plate (3) (as shown). Figure 4 As shown). The first and second pairs of opening and closing plates (7,8,9,10) on both sides of the first base plate (3) are fixed on the concentric circle of the arc of the first and second base plates (3,5) through the fairing opening and closing force transmission mechanism (see the description below), and can rotate around the center of the concentric circle, thereby realizing the closing and opening of the fairing. Its isometric view is shown below. Figure 3 and Figure 4 As shown; among them, by Figure 3 Looking at the arrow shown, the first fairing (1) is hidden, and the fairing closing and opening process can be seen; the fully opened side view is as follows. Figure 5 , Figure 6 , Figure 7 As shown in the diagram, the arrows indicate the opening and closing directions.

[0042] Force transmission mechanism for fairing opening and closing

[0043] The force transmission mechanism is installed on both sides of the base plate, with a total of 4 sets of force transmission mechanisms installed on one wing, and a total of 8 sets for the entire aircraft (e.g. Figure 8 (As shown).

[0044] The force transmission mechanism includes a servo frame (37), a servo (43), a servo gear (44), concentric gears (40, 41), a steel shaft (42), a connecting rod (38, 39), and a hinge plate (7, 8). The servo (43) is connected to the servo frame (37), the servo (43) is connected to the servo gear (44), the concentric gear (40) is connected to the connecting rod (39), the concentric gear (41) is connected to the connecting rod (38), the first hinge plate (7) is connected to the left connecting rod (38), and the second hinge plate (8) is connected to the right connecting rod (39). The steel shaft (42) passes through the small holes on the servo frame (37) and the two concentric gears (40, 41) in sequence, and then transmits the force from the small holes on the other side of the servo frame (37), connecting the concentric gear and the connecting rod to the servo frame (37) (as shown in (A) and (B) of Figure 9). The servo mount (37) passes through the first carbon tube (19) and is fixed to both sides of the first base plate (3). The connecting rods (38, 39) are respectively connected to the first and second opening and closing plates (7, 8) on both sides of the first base plate (3) (e.g. Figure 10 (As shown). When the servo motor rotates, the servo gear drives two concentric gears to rotate to both sides. The connecting rod plate, which is fixed to the servo gear, also rotates accordingly, thus realizing the opening and closing movement of the first and second opening plates. (Opening and closing side view as shown) Figure 5 (As shown in 6 and 7)

[0045] An operational example of a vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) according to an embodiment of the present invention will now be described.

[0046] Example: Conventional flight process of a vertical takeoff and landing (VTOL) drone

[0047] 1. Vertical Takeoff: The openable rectifier mechanism opens, and the rotor rotation provides power, enabling the drone to take off vertically.

[0048] Fly to a certain altitude.

[0049] 2. Mode switching: The turbojet engine starts, and when the UAV reaches a certain level flight speed, the rotor stops and the open-close rectifier mechanism closes.

[0050] 3. Fixed-wing climb, cruise, and dive: Perform missions in the manner of a fixed-wing aircraft. At this time, the rectifier mechanism is in a closed state, which reduces the aerodynamic drag of the UAV and increases the flight speed.

[0051] 4. Mode switching: The open-closed rectifier mechanism opens, the rotor starts, and the turbojet engine shuts down.

[0052] 5. Vertical landing: The rotor rotation provides power, enabling the drone to land vertically at the target location.

[0053] The advantages and beneficial effects of this invention include:

[0054] During vertical takeoff and landing and hovering, the rectifier mechanism opens, and the four sets of rotors rotate at high speed to ensure the efficient and stable vertical takeoff and landing of the drone.

[0055] During horizontal high-speed flight, the rotor and motor stop rotating, the rectifier mechanism closes, and the aerodynamic drag during high-speed flight is reduced.

[0056] The solution according to the present invention has the advantages of simple structure, light weight, and high stability.

Claims

1. A vertical take-off and landing drone, characterized in that The unmanned aerial vehicle comprises: a fuselage (26), first and second wings (24, 25) connected to the fuselage, first and second fairing mechanisms respectively externally mounted at lower portions of the first and second wings (24, 25), first and second vertical tails (21, 22) respectively connected to the first and second fairing mechanisms, a horizontal tail (23) connecting the first and second vertical tails, a turbojet engine (36) mounted on the fuselage, wherein the first fairing mechanism comprises: first and second motors (32, 33), first and second rotors (28, 29) respectively driven by the first and second motors, first to fourth flaps (7, 8, 9, 10), wherein the first and second flaps (7, 8) are arranged in front of the first wing (24), and the third and fourth flaps (9, 10) are arranged behind the first wing (24), a first carbon tube (19), first and second bottom plates (3, 5) assembled on the first carbon tube (19), the first and second bottom plates (3, 5) are circular arc plates with an angle of 120 degrees, the first and second flaps (7, 8) have the same length as the first bottom plate (3), the third and fourth flaps (9, 10) have the same length as the second bottom plate (5), the radius of the circular arc plate of the first and second flaps (7, 8) is slightly larger than the radius of the first bottom plate (3), and the radius of the circular arc plate of the third and fourth flaps (9, 10) is slightly larger than the radius of the second bottom plate (5), a first fairing head cover (1) connected to the first carbon tube (19) and the first bottom plate (3), a first wing lower fairing cover (15) connected to the first wing (24), a first vertical tail connecting fairing cover (17) connected to the first vertical tail (21), a fairing cover opening and closing transmission mechanism, wherein the first to fourth flaps (7, 8, 9, 10) on both sides of the first bottom plate (3) are fixed on a concentric circle of the circle where the circular arcs of the first and second bottom plates (3, 5) are located by the fairing cover opening and closing transmission mechanism, and can rotate around the center of the concentric circle, thereby realizing the closing and opening of the fairing cover, wherein: when the unmanned aerial vehicle is vertically taking off and / or hovering, the first and second fairing mechanisms are opened, the first to fourth rotors (28, 29, 30, 31) are rotated to provide power, and when the unmanned aerial vehicle is flying at a high speed, the first and second fairing mechanisms are closed to reduce the resistance received by the unmanned aerial vehicle, and at the same time the turbojet engine (36) is started to provide power, so as to increase the flight speed of the unmanned aerial vehicle, the fairing cover opening and closing transmission mechanism comprises a rudder frame (37), a rudder (43), a rudder gear (44), concentric gears (40, 41), a steel shaft (42), connecting rods (38, 39), first and second flaps (7, 8), wherein: the rudder (43) is connected to the rudder frame (37), the rudder (43) is connected to the rudder gear (44), the concentric gear (40) is connected to the connecting rod (39), the concentric gear (41) is connected to the connecting rod (38), the first flap (7) is connected to the left connecting rod (38), The second opening and closing plate (8) is connected with the right connecting rod (39), the steel shaft (42) passes through the small holes on the rudder frame (37) and the two concentric gears (40, 41) in sequence, and then is transmitted out from the small hole on the other side of the rudder frame (37), thereby connecting the concentric gears and the connecting rod on the rudder frame (37), The rudder frame (37) passes through the first carbon tube (19) and is fixed on both sides of the first bottom plate (3), The connecting rods (38, 39) are respectively connected with the first and second opening and closing plates (7, 8) on both sides of the first bottom plate (3), When the rudder rotates, the rudder gear drives the two concentric gears to rotate to both sides, and the connecting rod opening and closing plate fixed with the rudder gear also rotates, thereby realizing the opening and closing movement of the first and second opening and closing plates.

2. The vertical take-off and landing unmanned aerial vehicle according to claim 1, characterized in that: The second flow regulation mechanism has a symmetrical structure with the first flow regulation mechanism.

3. The VTOL drone of claim 1, wherein Further comprising: Landing gear (27).

4. The vertical take-off and landing unmanned aerial vehicle according to claim 1, characterized in that: The fairing opening and closing force transmission mechanism is installed on both sides of each bottom plate, and 4 sets of force transmission mechanisms are installed on one side of the wing, and the whole machine has 8 sets in total.

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