Vertical take-off and landing unmanned aerial vehicle with morphing wings

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a variant wing vertical take-off and landing unmanned aerial vehicle which is characterized in that an equipment main body is adjusted through an adjusting structure so as to adapt to different flight environments, a wing can be quickly replaced after being damaged, and the adjusting position of the adjusting structure is fixed through a fixing device, so that the unmanned aerial vehicle is convenient to use. By means of the lifting device, the equipment has the lifting capacity at the fixed position, and the practicability of the device is improved; comprising an adjusting structure, a fixing structure and a lifting device, the fixing structure is installed on the adjusting structure, and the lifting device is installed on the adjusting structure.

Description

Technical Field

[0001] This utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a variant-wing vertical take-off and landing (VTOL) UAV. Background Technology

[0002] Unmanned aerial vehicles (UAVs) have extremely wide applications, especially in surveillance, reconnaissance, and mapping. Currently, UAVs can be broadly classified into fixed-wing UAVs, unmanned helicopters, multi-rotor UAVs, and vertical takeoff and landing (VTOL) UAVs. Fixed-wing UAVs and VTOL UAVs generate aerodynamic lift through their wings, giving them an advantage over rotary-wing UAVs in terms of range, speed, and ceiling. However, fixed-wing UAVs have higher requirements and more restrictions for takeoff and landing sites. While VTOL UAVs can achieve the vertical takeoff and landing functions of fixed-wing UAVs, the hovering power components in fixed-wing mode cause significant weight and aerodynamic drag, reducing efficiency in fixed-wing mode.

[0003] The existing Chinese utility model patent with application number CN201920668099.0 relates to a variant wing vertical take-off and landing unmanned aerial vehicle (UAV), which includes multiple sets of wings, power components, connecting lugs, rotating shafts, drive motors, transmission shafts, and worm gears, etc. It can overcome the maneuverability problem of UAV take-off and landing, and at the same time optimize the stability and handling performance of UAV during take-off and landing.

[0004] However, in actual use, when the device changes shape in the air, the position and direction of the power components also change, and during this period, the device has difficulty controlling its own flight status and direction. Utility Model Content

[0005] To solve the above-mentioned technical problems, this utility model provides a variant wing-mounted vertical take-off and landing UAV that adjusts the main body of the device through an adjustment structure to adapt to different flight environments and can be quickly replaced after the wing is damaged. The adjustment position of the adjustment structure is fixed by a fixing device, and the take-off and landing device enables the device to take off and land in a fixed position, thereby improving the practicality of the device.

[0006] This utility model discloses a variant wing vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV); it includes an adjustment structure, a fixed structure, and a take-off and landing device. The fixed structure is installed on the adjustment structure, and the take-off and landing device is installed on the adjustment structure. The main body of the device is adjusted by the adjustment structure to adapt to different flight environments and can be quickly replaced after the wing is damaged. The fixed structure fixes the adjustment position of the adjustment structure, and the take-off and landing device enables the device to take off and land in a fixed position, thus improving the practicality of the device.

[0007] Preferably, the adjustment structure includes a fuselage, wing mounts, connecting slots, and flexible wings. A set of wing mounts is installed on the left and right sides of the front of the fuselage, and connecting slots are provided on the outer surface of the wing mounts. The two sets of flexible wings are respectively inserted into the two sets of connecting slots. The position of the flexible wings in the wing mounts can be adjusted according to the weight of the fuselage and the flight environment, and it is easy to replace the flexible wings after they are worn or damaged, which improves the practicality of the device.

[0008] Preferably, the fixing structure includes a connecting kit, a connecting protrusion, a docking groove, and fixing bolts. The connecting kit is fitted onto the flexible wing. The connecting kit itself is frustoconical and has a through hole in the middle through which the flexible wing can pass. The docking groove is provided on the outer edge of the rear end face of the wing mount. The connecting protrusion is provided on the side of the rear end face of the connecting kit that is close to the fuselage. The connecting protrusion can be inserted into the docking groove. Two sets of fixing bolts are installed on the left and right sides of the rear end face of the connecting protrusion. The two sets of fixing bolts on the left are connected to the docking groove, and the two sets of fixing bolts on the right press the flexible wing to fix its position. The connecting kit provides a transition between the connection position of the wing mount and the flexible wing and assists in fixing the position of the flexible wing, which facilitates the disassembly and quick installation of the flexible wing, reduces turbulence at the connection position during flight, and improves the practicality of the device.

[0009] Preferably, it also includes a tail fin and a propeller. The tail fin is provided at the rear of the fuselage, and the propeller is installed on the rear end face of the fuselage. The propeller is driven by an electric motor. The propeller provides power for the straight flight of the fuselage, and the tail fin helps the fuselage maintain a level state during flight, which improves the practicality of the device.

[0010] Preferably, the takeoff and landing device includes a storage frame, a pivot seat, a rotating arm, a power unit, and a storage compartment. The storage frame is installed in the middle of the lower end face of the fuselage, and a storage compartment is set in the middle of the storage frame. A set of pivot seats is vertically installed at each of the four corner positions of the storage frame, and a set of rotating arms is fitted on each of the four sets of pivot seats. The power unit is installed at the end of the rotating arm. By rotating the rotating arm, the rotating arm and the power unit are stored in the storage compartment, which reduces wind resistance during the fuselage's straight flight, reduces the space occupied by the equipment during transportation, and reduces collision damage. By activating the four sets of power units, the equipment is provided with the ability to take off and land vertically, which improves the practicality of the device.

[0011] Preferably, it also includes a drive motor, which is mounted on the rotating shaft seat; the drive motor provides power to the rotating shaft seat to drive the rotating arm on the rotating shaft seat to rotate, and the rotating arm and power components are stored inside the storage compartment. When maintaining straight flight, the flight resistance of the equipment is reduced, and when performing vertical take-off and landing, the rotating arm is rotated to the outside, which improves the practicality of the device.

[0012] Compared with the prior art, the beneficial effects of this utility model are as follows: the main body of the equipment can be adjusted by adjusting the structure to adapt to different flight environments, and the wings can be quickly replaced after damage. The adjustment position of the adjustment structure is fixed by the fixing device, and the take-off and landing device enables the equipment to take off and land in a fixed position, thus improving the practicality of the device. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the first isometric structure of this utility model;

[0014] Figure 2 This is a schematic diagram of the second isometric structure of this utility model;

[0015] Figure 3 This is a cross-sectional structural diagram of the present invention;

[0016] Figure 4 This is a partially enlarged structural schematic diagram of the present invention;

[0017] The following are labeled in the attached diagram: 1. Fuselage; 2. Wing mount; 3. Connecting slot; 4. Flexible wing; 5. Connecting kit; 6. Connecting protrusion; 7. Docking groove; 8. Fixing bolt; 9. Tail fin plate; 10. Propeller; 11. Storage rack; 12. Rotary shaft mount; 13. Rotating arm; 14. Power unit; 15. Storage compartment; 16. Drive motor. Detailed Implementation

[0018] To facilitate understanding of this utility model, a more complete description will be given below with reference to the accompanying drawings. This utility model can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to make the disclosure of this utility model more thorough and complete.

[0019] Example 1

[0020] Figure 1 , Figure 2 , Figure 3 , Figure 4 As shown, the fixed structure is installed on the adjustable structure, and the lifting device is installed on the adjustable structure.

[0021] First, the equipment is given vertical lifting capability by activating the four sets of power components 14. Then, the main propeller 10 is activated to provide horizontal thrust to the equipment. At the same time, the drive motor 16 is activated to provide power to the rotating arm 13 on the rotating arm 12, which is then rotated. The rotating arm 13 and the power components 14 are stored in the storage compartment 15. After the flexible wing 4 is worn or damaged by collision, the fixing bolts 8 on the connecting protrusion 6 can be loosened to quickly replace the connecting kit 5.

[0022] The adjustment structure includes a fuselage 1, wing mounts 2, connecting slots 3, and flexible wings 4. A set of wing mounts 2 is installed on the left and right sides of the front part of the fuselage 1. Connecting slots 3 are provided on the outer side of the wing mounts 2. The two sets of flexible wings 4 are respectively inserted into the two sets of connecting slots 3.

[0023] The fixing structure includes a connecting kit 5, a connecting protrusion 6, a docking groove 7, and fixing bolts 8. The connecting kit 5 is fitted on the flexible wing 4. The connecting kit 5 itself is truncated cone-shaped and has a through hole in the middle through which the flexible wing 4 can pass. The docking groove 7 is provided on the outer edge of the rear end face of the wing seat 2. The connecting protrusion 6 is provided on the side of the rear end face of the connecting kit 5 that is close to the fuselage 1. The connecting protrusion 6 can be inserted into the docking groove 7. Two sets of fixing bolts 8 are installed on the left and right sides of the rear end face of the connecting protrusion 6, respectively. The two sets of fixing bolts 8 on the left are connected to the docking groove 7, and the two sets of fixing bolts 8 on the right press the flexible wing 4 to fix the position of the flexible wing 4.

[0024] It also includes a tail fin 9 and a propeller 10. The tail fin 9 is provided at the tail of the fuselage 1, and the propeller 10 is installed on the rear end face of the fuselage 1. The propeller 10 is driven by an electric motor.

[0025] The take-off and landing device includes a storage frame 11, a pivot seat 12, a rotating arm 13, a power unit 14, and a storage compartment 15. The storage frame 11 is installed in the middle of the lower end face of the fuselage 1. The storage compartment 15 is set in the middle of the storage frame 11. A set of pivot seats 12 is vertically installed at each of the four corner positions of the storage frame 11. A set of rotating arms 13 is fitted on each of the four sets of pivot seats 12. The power unit 14 is installed at the end of the rotating arm 13.

[0026] It also includes a drive motor 16, which is mounted on the rotating shaft seat 12;

[0027] The main body of the equipment can be adjusted by adjusting the structure to adapt to different flight environments and can be quickly replaced after the wing is damaged. The adjustment position of the adjustment structure is fixed by the fixing device, and the take-off and landing device enables the equipment to take off and land in a fixed position, thus improving the practicality of the device.

[0028] like Figures 1 to 4 As shown, this utility model discloses a variant wing vertical take-off and landing (VTOL) drone. During operation, it first activates four sets of power components 14 to provide the device with vertical take-off and landing capabilities. Then, it activates the main propeller 10 to provide horizontal thrust to the device. At the same time, it activates the drive motor 16 to provide power to the pivot seat 12, driving the rotating arm 13 on the pivot seat 12 to rotate. The rotating arm 13 and the power components 14 are stored inside the storage compartment 15. After the flexible wing 4 is worn or damaged by collision, the fixing bolts 8 on the connecting protrusion 6 can be loosened to quickly replace the connecting kit 5.

[0029] The power assembly 14 and drive motor 16 of this utility model's variant wing vertical take-off and landing UAV are commercially available. Those skilled in the industry only need to install and operate them according to the accompanying instruction manual, without requiring any creative effort from those skilled in the art.

[0030] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. A variant-wing vertical takeoff and landing unmanned aerial vehicle (UAV); characterized in that, The system includes an adjustment structure, a fixed structure, and a take-off and landing device. The fixed structure is installed on the adjustment structure, and the take-off and landing device is installed on the adjustment structure. The adjustment structure includes a fuselage (1), wing mounts (2), connecting slots (3), and flexible wings (4). A set of wing mounts (2) is installed on the left and right sides of the front part of the fuselage (1). Connecting slots (3) are provided on the outer surface of the wing mounts (2). The two sets of flexible wings (4) are inserted into the two sets of connecting slots (3) respectively. The fixed structure includes a connecting kit (5), a connecting protrusion (6), a docking groove (7), and a fixing bolt (8). The connecting kit (5) is fitted on the flexible wing (4). The connecting kit (5) itself is truncated cone-shaped and has a through hole in the middle that can pass through the flexible wing (4). The outer edge of the rear end face of the wing mount (2) is provided with a docking groove (7). The side of the rear end face of the connecting kit (5) close to the fuselage (1) is provided with a connecting protrusion (7). A connecting protrusion (6) is provided, which can be inserted into the docking groove (7). Two sets of fixing bolts (8) are installed on the left and right sides of the rear end face of the connecting protrusion (6). The two sets of fixing bolts (8) on the left are connected to the docking groove (7), and the two sets of fixing bolts (8) on the right press the flexible wing (4) to fix the position of the flexible wing (4). The take-off and landing device includes a storage frame (11), a pivot seat (12), a rotating arm (13), a power component (14), and a storage compartment (15). A storage frame (11) is installed in the middle of the lower end face of the fuselage (1). A storage compartment (15) is set in the middle of the storage frame (11). A set of pivot seats (12) is vertically installed at the four corner positions of the storage frame (11). A set of rotating arms (13) is fitted on each of the four sets of pivot seats (12). A power component (14) is installed on the end of the rotating arm (13).

2. A variant-wing vertical takeoff and landing unmanned aerial vehicle as described in claim 1, characterized in that, It also includes a tail fin (9) and a propeller (10). The tail fin (9) is provided at the tail of the fuselage (1), and the propeller (10) is installed on the rear end face of the fuselage (1). The propeller (10) is driven by an electric motor.

3. A variant-wing vertical takeoff and landing unmanned aerial vehicle as described in claim 2, characterized in that, It also includes a drive motor (16), which is mounted on the shaft seat (12).

Images