Heavy-load-level electric vertical take-off and landing fixed-wing unmanned aerial vehicle

Abstract

The invention discloses a large-load-level electric vertical take-off and landing fixed-wing unmanned aerial vehicle which comprises a rack, wings are arranged on the two sides of the rack, positioning holes are formed in the wings, front-end driving pieces are arranged in the positioning holes, undercarriages are arranged on the two sides of the bottom end of the rack, bearing rods are arranged in the undercarriages, and the bearing rods are connected with the undercarriages. And a bearing bracket is arranged on the peripheral wall of the bearing rod. The invention relates to the technical field of load-carrying unmanned aerial vehicles. According to the large-load-level electric vertical take-off and landing fixed-wing unmanned aerial vehicle, a hydraulic rod controls a front-end driving piece to move downwards, in the process that the front-end driving piece moves downwards, a supporting table is pushed upwards through an extension rod and a transverse table, a heavy object is tilted, the heavy object is tightly attached to the rack, the stability of the heavy object is improved, meanwhile, the front-end driving piece is flush with the heavy object, and the heavy object is prevented from falling off. During vertical takeoff, the front end driving piece is close to the gravity center of the cargo and the gravity center of the unmanned aerial vehicle body, the stability in the flight process can be effectively improved, and the pendulum effect is avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of load-carrying unmanned aerial vehicles, and in particular to a large-load-class electric vertical take-off and landing fixed-wing unmanned aerial vehicle. Background Art

[0002] A drone is an unmanned aircraft controlled by a radio remote control device and its own program control device, or operated completely or intermittently autonomously by an onboard computer.

[0003] In the prior art, when a drone is loaded, the heavy object is mostly hung at the bottom of the frame to fix the cargo and transported by the drone; However, when lifting heavy objects, due to the large inertia of the objects, there will be great pressure at the connection between the cargo and the frame during the take-off and landing of the drone, which can easily cause the objects to fall off or even damage the drone.

[0004] Moreover, this installation method will create a large height difference between the cargo and the drone rotor, which will affect the stability of the drone and easily form a pendulum effect under the influence of ambient wind. In this case, the greater the height difference, the greater the swing amplitude may be, and the more obvious the impact on stability will be.

[0005] Therefore, those skilled in the art provide a large-load-class electric vertical take-off and landing fixed-wing UAV to solve the problems raised in the above-mentioned background technology. Summary of the invention

[0006] The purpose of the present invention is to provide a large-load-class electric vertical take-off and landing fixed-wing UAV to solve the problems raised in the above-mentioned background technology.

[0007] To achieve the above object, the present invention provides the following technical solutions: The above technical objectives of the present invention are achieved through the following technical solutions: A heavy-duty electric vertical take-off and landing fixed-wing UAV comprises a frame, wings are arranged on both sides of the frame, positioning holes are opened inside the wings, front-end driving parts are arranged inside the positioning holes, landing gears are arranged on both sides of the bottom end of the frame, supporting rods are arranged inside the landing gears, and supporting brackets are arranged on the outer peripheral wall of the supporting rods; The supporting bracket includes a transverse platform, which is sleeved on the outer peripheral wall of the supporting rod and rotatably connected to the supporting rod. A support platform is fixedly arranged at the bottom end of the transverse platform, and an extension rod is slidably arranged at the top end of the transverse platform. The top end of the extension rod is rotatably connected to the front end driving member. A mounting rod is arranged on the side of the landing gear, and both ends of the mounting rod are fixedly connected to the landing gear through side plates. A hydraulic rod is fixedly arranged on the upper end of the mounting rod, and the hydraulic rod is vertically arranged to the mounting rod, and the telescopic part of the hydraulic rod is fixedly connected to the front end driving member.

[0008] Furthermore, the front-end driving member includes a positioning ring, a transmission frame is fixedly arranged at the inner bottom end of the positioning ring, a driving motor is arranged at the top end of the transmission frame, a spiral fan blade is arranged at the top end of the driving motor, and a mounting platform is arranged on the side wall of the positioning ring.

[0009] Furthermore, the side wall of the mounting platform is provided with an extension shaft, and the mounting platform is rotatably connected to the extension rod through the extension shaft. A connecting rod is fixedly provided at one end of the side wall of the mounting platform away from the extension shaft, and the connecting rod is fixedly connected to the telescopic end of the hydraulic rod. An electric steering gear is provided inside the mounting platform, and the drive shaft of the electric steering gear is fixedly connected to the positioning ring.

[0010] Furthermore, a battery pack is arranged at the rear end of the frame, tail wings are fixedly arranged on both sides of the battery pack, a tail hole is opened inside the tail wing, and a tail drive member is arranged inside the tail hole.

[0011] Furthermore, the tail end drive component includes a tail end ring, a tail end frame is arranged at the bottom end of the tail end ring, a control motor is arranged at the top end of the tail end frame, a tail end fan blade is arranged at the top end of the control motor, two synchronous servos are arranged on the inner wall of the tail end hole, and the shafts of the two synchronous servos are coaxially arranged and are both fixedly connected to the tail end ring.

[0012] Furthermore, the support platform includes a connecting plate, which is fixedly connected to the bottom end of the horizontal platform, and the four corners of the side wall of the connecting plate are threaded with adjusting rods, the ends of the adjusting rods are commonly connected to an L-shaped support plate, and a universal shaft is provided at the connection between the adjusting rod and the L-shaped support plate.

[0013] Furthermore, a connecting platform is arranged on the inner side of the L-shaped supporting plate, and a plurality of buffer members are arranged between the connecting platform and the L-shaped supporting plate.

[0014] Furthermore, an expansion plate is arranged in the middle of the bottom end of the frame, support springs are arranged at the four corners of the bottom end of the expansion plate, a pressure plate is arranged at the bottom end of the support springs, and a damping rod is arranged inside the support springs.

[0015] In summary, the present invention includes at least one of the following beneficial technical effects: 1. This is a heavy-load electric vertical take-off and landing fixed-wing UAV. The hydraulic rod controls the front-end driving part to move downward. During the downward movement of the front-end driving part, the support platform is pushed upward by the extension rod and the horizontal platform to lift the heavy object, so that the heavy object is close to the frame, thereby improving the stability of the heavy object. At the same time, the front-end driving part and the heavy object are flush with each other. During vertical take-off, the center of gravity of the front-end driving part, the cargo and the UAV body are close to each other, which can effectively improve the stability during flight and avoid the occurrence of the pendulum effect. 2. This heavy-load electric vertical take-off and landing fixed-wing UAV, on the other hand, when the UAV flush with the heavy object pushes the air downward to generate lift, avoids the downward moving air from contacting the heavy object, thereby avoiding turbulence at the bottom of the front driving member, which can further improve the stability of vertical take-off; 3. This kind of heavy-load electric vertical take-off and landing fixed-wing UAV has a support spring setting. After the weight is installed, the pressure plate is pressed against the upper surface of the weight, which improves the stability of the weight and cushions the weight when the UAV takes off and lands, reducing the damage to the equipment caused by the inertia of the weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 It is a structural schematic diagram of a large-load-class electric vertical take-off and landing fixed-wing UAV of the present invention; Figure 2 It is a structural schematic diagram of a heavy-load electric vertical take-off and landing fixed-wing UAV of the present invention after the front-end driving part of the UAV turns; Figure 3 It is a schematic diagram of the bottom structure of a frame of a heavy-load electric vertical take-off and landing fixed-wing UAV of the present invention; Figure 4 It is a structural schematic diagram of a front-end driving part of a heavy-load electric vertical take-off and landing fixed-wing UAV of the present invention after turning; Figure 5 It is a structural schematic diagram of a front-end driving component of a heavy-load electric vertical take-off and landing fixed-wing UAV of the present invention; Figure 6 It is a structural schematic diagram of a tail end drive component of a heavy-load electric vertical take-off and landing fixed-wing UAV of the present invention; Figure 7 It is a schematic diagram of the planar structure of a large-load-class electric vertical take-off and landing fixed-wing UAV of the present invention after the front-end driving part is turned; Figure 8 It is a planar structural schematic diagram of a front-end driving component of a large-load-class electric vertical take-off and landing fixed-wing UAV of the present invention.

[0018] In the figure, 1, frame; 2, wing; 3, positioning hole; 4, front end drive member; 41, positioning ring; 42, transmission frame; 43, drive motor; 44, propeller blade; 45, mounting platform; 46, extension shaft; 47, connecting rod; 48, electric steering gear; 5, landing gear; 6, supporting rod; 7, supporting bracket; 71, horizontal platform; 72, supporting platform; 721, connecting plate; 722, adjusting rod; 723, L shaped support plate; 724, connecting platform; 725, buffer; 73, extension rod; 8, mounting rod; 9, hydraulic rod; 10, battery pack; 11, tail wing; 12, tail end hole; 13, tail end drive member; 131, tail end ring; 132, tail end frame; 133, control motor; 134, tail end fan blade; 135, synchronous servo; 14, expansion board; 15, support spring; 16, pressure plate; 17, damping rod. DETAILED DESCRIPTION

[0019] Below, the invention is further described in conjunction with the accompanying drawings and specific embodiments: Reference Figure 1 - Figure 8 The present invention discloses a large-load-class electric vertical take-off and landing fixed-wing UAV, comprising a frame 1, wings 2 are arranged on both sides of the frame 1, positioning holes 3 are opened inside the wings 2, front-end driving members 4 are arranged inside the positioning holes 3, landing gears 5 are arranged on both sides of the bottom end of the frame 1, supporting rods 6 are arranged inside the landing gears 5, and supporting brackets 7 are arranged on the outer peripheral wall of the supporting rods 6; The supporting bracket 7 includes a transverse platform 71, which is sleeved on the outer peripheral wall of the supporting rod 6 and is rotatably connected to the supporting rod 6. A support platform 72 is fixedly provided at the bottom end of the transverse platform 71, and an extension rod 73 is slidably provided at the top end of the transverse platform 71. The top end of the extension rod 73 is rotatably connected to the front end driving member 4. A mounting rod 8 is arranged on the side of the landing gear 5, and both ends of the mounting rod 8 are fixedly connected to the landing gear 5 through side plates. A hydraulic rod 9 is fixedly arranged on the upper end of the mounting rod 8, and the hydraulic rod 9 is arranged vertically to the mounting rod 8, and the telescopic part of the hydraulic rod 9 is fixedly connected to the front end driving member 4.

[0020] In this embodiment, when loading heavy objects, the heavy objects are overlapped on the top of the support platforms 72 on both sides. After the placement is completed, the hydraulic rod 9 is controlled by the oil pump arranged inside the frame 1 to retract. At this time, the hydraulic rod 9 stretches the front end driving member 4 downward to separate the front end driving member 4 from the wing 2. In the process of the front end driving member 4 moving downward, the support platform 72 is pushed upward by the setting of the extension rod 73 and the horizontal platform 71, so that the heavy objects are tilted up and contacted with the bottom end of the frame 1, so as to achieve the purpose of fixing the heavy objects. At this time, the front end driving member 4 is flush with the heavy objects or lower than the heavy objects. During vertical takeoff, the pendulum effect can be effectively avoided, thereby improving the stability during flight. At the same time, during takeoff, since the heavy object and the front-end driving component 4 are flush with each other, when the front-end driving component 4 pushes the air downward, the problem of turbulence caused by contact between the air and the heavy object can be avoided, thereby further improving the stability of vertical takeoff.

[0021] In a further preferred embodiment of the present invention, Figure 4 , Figure 5 and Figure 7 As shown, the front end driving member 4 includes a positioning ring 41, a transmission frame 42 is fixedly arranged at the inner bottom end of the positioning ring 41, a driving motor 43 is arranged at the top end of the transmission frame 42, a spiral fan blade 44 is arranged at the top end of the driving motor 43, and a mounting platform 45 is arranged on the side wall of the positioning ring 41.

[0022] In this embodiment, Figure 1 and Figure 4 As shown, through the positioning ring 41, when the equipment is not in use, the positioning ring 41 is inserted into the positioning hole 3 to achieve the purpose of protecting the front-end driving component 4. Through the transmission frame 42, the driving motor 43 is fixedly set inside the positioning ring 41, and the lift is generated by driving the spiral fan blades 44. The mounting platform 45 is used to connect the positioning ring 41 with the supporting bracket 7 and the hydraulic rod 9 to achieve the purpose of installing the front-end driving component 4.

[0023] In a further preferred embodiment of the present invention, Figure 4 As shown, the side wall of the mounting platform 45 is provided with an extension shaft 46, and the mounting platform 45 is rotatably connected to the extension rod 73 through the extension shaft 46. A connecting rod 47 is fixedly provided at one end of the side wall of the mounting platform 45 away from the extension shaft 46, and the connecting rod 47 is fixedly connected to the telescopic end of the hydraulic rod 9. An electric steering gear 48 is provided inside the mounting platform 45, and the driving shaft of the electric steering gear 48 is fixedly connected to the positioning ring 41.

[0024] In this embodiment, the extension shaft 46 is used to connect the extension rod 73 to the mounting platform 45, and the mounting platform 45 is fixedly connected to the hydraulic rod 9 through the connecting rod 47, and then the position of the mounting platform 45 is controlled by the extension and retraction of the hydraulic rod 9, that is, it is used to control the position of the front-end drive component 4, and the angle of the positioning ring 41 can be controlled by the setting of the electric servo 48, which is used to change the inclination angle of the propeller blades 44, so that the UAV can cooperate with the fixed wings 2 to fly horizontally quickly when it is lifted.

[0025] In a further preferred embodiment of the present invention, Figure 1 and Figure 2 As shown, a battery pack 10 is provided at the tail end of the frame 1, and the battery pack 10 is used to provide power to each front-end drive component 4, the tail-end drive component 13 and the hydraulic pump inside the frame, and can control the electric servo 48 and the synchronous servo 135 to control the angles of the front-end drive component 4 and the tail-end drive component 13, thereby providing power for the flight of the UAV through the front-end drive component 4 and the tail-end drive component 13, and controlling the lifting and lowering of the hydraulic rod 9 through the hydraulic pump to adjust the height of the front-end drive component 4 and fix the cargo, and tail wings 11 are fixedly provided on both sides of the battery pack 10, and a tail end hole 12 is opened inside the tail wing 11, and a tail end drive component 13 is arranged inside the tail end hole 12.

[0026] In this embodiment, the tail 11 and the tail end driving member 13 are used to improve the stability of the frame 1 .

[0027] In a further preferred embodiment of the present invention, Figure 6 As shown, the tail end driving member 13 includes a tail end ring 131, a tail end frame 132 is arranged at the bottom end of the tail end ring 131, a control motor 133 is arranged at the top end of the tail end frame 132, a tail end fan blade 134 is arranged at the top end of the control motor 133, and two synchronous servos 135 are arranged on the inner wall of the tail end hole 12, and the shafts of the two synchronous servos 135 are coaxially arranged and are both fixedly connected to the tail end ring 131.

[0028] In this embodiment, the tail ring 131 is installed inside the tail hole 12 through a synchronous servo 135. The two synchronous servos 135 are used to control the front and rear tilt angles of the tail ring 131 to provide horizontal power when the drone is flying.

[0029] In a further preferred embodiment of the present invention, Figure 7 As shown, the support platform 72 includes a connecting plate 721, which is fixedly connected to the bottom end of the horizontal platform 71, and the four corners of the side wall of the connecting plate 721 are threadedly connected with an adjusting rod 722, the ends of the adjusting rod 722 are commonly connected to an L-shaped support plate 723, and a universal shaft is provided at the connection between the adjusting rod 722 and the L-shaped support plate 723.

[0030] In this embodiment, the L-shaped support plate 723 is installed by means of the adjusting rod 722 and the universal shaft, and the bottom end of the heavy object is clamped by the L-shaped support plate 723 to achieve the purpose of improving the stability of the heavy object after installation, and the angle of the L-shaped support plate 723 is adjusted by controlling the position of the adjusting rod 722, so that the device can be suitable for heavy objects of different sizes, wherein the long plate portion of the L-shaped support plate 723 is telescopically arranged.

[0031] In a further preferred embodiment of the present invention, Figure 7 As shown, a connecting platform 724 is disposed on the inner side of the L-shaped supporting plate 723 , and a plurality of buffer members 725 are disposed between the connecting platform 724 and the L-shaped supporting plate 723 .

[0032] In this embodiment, the connecting platform 724 is used to isolate the L-shaped support plate 723 and the heavy object, and cooperates with the buffer member 725 to reduce the pressure between the support plate and the heavy object, thereby reducing the damage to the equipment caused by the heavy object when the drone takes off and lands.

[0033] In a further preferred embodiment of the present invention, Figure 3 As shown, an expansion plate 14 is provided in the middle of the bottom end of the frame 1, support springs 15 are provided at the four corners of the bottom end of the expansion plate 14, a pressure plate 16 is provided at the bottom end of the support spring 15, and a damping rod 17 is provided inside the support spring 15.

[0034] In this embodiment, by setting the support spring 15, after the weight is installed, the pressure plate 16 is pressed against the upper surface of the weight, which improves the stability of the weight and cushions the weight when the drone takes off and lands, reducing the damage to the equipment caused by the inertia of the weight.

[0035] The implementation principle of the above embodiment is: when loading heavy objects, the heavy objects are overlapped on the top of the two side support platforms 72, and then the hydraulic rod 9 is contracted. At this time, the hydraulic rod 9 stretches the front end drive member 4 downward to separate the front end drive member 4 from the wing 2, and in the process of the front end drive member 4 moving downward, the support platform 72 is pushed upward by the setting of the extension rod 73 and the horizontal platform 71, and the heavy object is lifted up, so that the front end drive member 4 and the heavy object are flush with each other or lower than the upper surface of the heavy object. Therefore, during vertical take-off, the center of gravity of the front end drive member 4 and the cargo and the drone body are close to each other, which can effectively improve the stability during flight and avoid the occurrence of the pendulum effect.

[0036] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A heavy-duty electric vertical take-off and landing fixed-wing UAV, characterized in that: The invention comprises a frame (1), wings (2) are arranged on both sides of the frame (1), positioning holes (3) are opened inside the wings (2), front-end driving components (4) are arranged inside the positioning holes (3), landing gears (5) are arranged on both sides of the bottom end of the frame (1), supporting rods (6) are arranged inside the landing gears (5), and supporting brackets (7) are arranged on the outer peripheral wall of the supporting rods (6); The supporting bracket (7) comprises a transverse platform (71), the transverse platform (71) is sleeved on the outer peripheral wall of the supporting rod (6) and is rotatably connected to the supporting rod (6), a supporting platform (72) is fixedly arranged at the bottom end of the transverse platform (71), an extension rod (73) is slidably arranged at the top end of the transverse platform (71), and the top end of the extension rod (73) is rotatably connected to the front end driving member (4); A mounting rod (8) is arranged on the side of the landing gear (5), and both ends of the mounting rod (8) are fixedly connected to the landing gear (5) through side plates. A hydraulic rod (9) is fixedly arranged on the upper end of the mounting rod (8), and the hydraulic rod (9) and the mounting rod (8) are arranged vertically. The telescopic part of the hydraulic rod (9) is fixedly connected to the front end driving member (4).

2. The heavy-duty electric vertical take-off and landing fixed-wing UAV according to claim 1, characterized in that: The front end driving member (4) comprises a positioning ring (41), a transmission frame (42) is fixedly arranged at the inner bottom end of the positioning ring (41), a driving motor (43) is arranged at the top end of the driving frame (42), a spiral fan blade (44) is arranged at the top end of the driving motor (43), and a mounting platform (45) is arranged on the side wall of the positioning ring (41).

3. The heavy-duty electric vertical take-off and landing fixed-wing UAV according to claim 2, characterized in that: An extension shaft (46) is provided on the side wall of the mounting platform (45), and the mounting platform (45) is rotatably connected to the extension rod (73) via the extension shaft (46). A connecting rod (47) is fixedly provided on one end of the side wall of the mounting platform (45) away from the extension shaft (46), and the connecting rod (47) is fixedly connected to the telescopic end of the hydraulic rod (9). An electric steering gear (48) is provided inside the mounting platform (45), and a drive shaft of the electric steering gear (48) is fixedly connected to the positioning ring (41).

4. The heavy-duty electric vertical take-off and landing fixed-wing UAV according to claim 3, characterized in that: A battery pack (10) is arranged at the rear end of the frame (1), tail wings (11) are fixedly arranged on both sides of the battery pack (10), a tail hole (12) is provided inside the tail wing (11), and a tail drive member (13) is arranged inside the tail hole (12).

5. The heavy-duty electric vertical take-off and landing fixed-wing UAV according to claim 4, characterized in that: The tail end driving member (13) comprises a tail end ring (131), a tail end frame (132) is arranged at the bottom end of the tail end ring (131), a control motor (133) is arranged at the top end of the tail end frame (132), a tail end fan blade (134) is arranged at the top end of the control motor (133), and two synchronous steering gears (135) are arranged on the inner wall of the tail end hole (12), and the shafts of the two synchronous steering gears (135) are coaxially arranged and are both fixedly connected to the tail end ring (131).

6. The heavy-duty electric vertical take-off and landing fixed-wing UAV according to claim 5, characterized in that: The support platform (72) comprises a connecting plate (721) which is fixedly connected to the bottom end of the horizontal platform (71); four corners of the side wall of the connecting plate (721) are threadedly connected to adjusting rods (722); the ends of the adjusting rods (722) are commonly connected to an L-shaped support plate (723); and a universal shaft is provided at the connection between the adjusting rod (722) and the L-shaped support plate (723).

7. The heavy-duty electric vertical take-off and landing fixed-wing UAV according to claim 6, characterized in that: A connecting platform (724) is provided on the inner side of the L-shaped supporting plate (723), and a plurality of buffer members (725) are provided between the connecting platform (724) and the L-shaped supporting plate (723).

8. The heavy-duty electric vertical take-off and landing fixed-wing UAV according to claim 7, characterized in that: An expansion plate (14) is arranged at the middle of the bottom end of the frame (1), support springs (15) are arranged at the four corners of the bottom end of the expansion plate (14), a pressure plate (16) is arranged at the bottom end of the support springs (15), and a damping rod (17) is arranged inside the support spring (15).

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