Multi-rotor patrol unmanned aerial vehicle

Abstract

The utility model relates to the field of unmanned aerial vehicles, in particular to a multi-rotor routing inspection unmanned aerial vehicle, and adopts the technical scheme that the multi-rotor routing inspection unmanned aerial vehicle comprises an unmanned aerial vehicle main body, a blade protection frame, a falling frame, a buffer air bag and a supporting frame. When the unmanned aerial vehicle body accidentally falls off, the buffering air bag breaks the aluminum bottom plate to be rapidly unfolded between the two sets of falling frames so as to carry out additional falling protection and buffering on the unmanned aerial vehicle body, and a conical blade protection frame wrapping a propeller of the unmanned aerial vehicle body can protect the propeller of the unmanned aerial vehicle body in the falling process; and the supporting frame installed in a buckling mode absorbs part of falling force in a disassembly mode, so that the impact force generated when the unmanned aerial vehicle body falls accidentally is reduced, and the problems that an existing multi-rotor inspection unmanned aerial vehicle is prone to being damaged when falling accidentally, and anti-falling protection measures are insufficient are solved.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicles (UAVs), specifically relating to a multi-rotor inspection UAV. Background Technology

[0002] Multi-rotor inspection drones are aircraft that use multiple rotors to provide lift and propulsion. They are widely used in various inspection tasks, especially in the inspection and maintenance of infrastructure such as power lines, wind turbines, communication towers, and bridges.

[0003] Existing multi-rotor inspection drones have limited protective structures. In actual use, drones often fall due to unexpected situations such as battery depletion, loss or interference of communication signals, and severe weather, which can cause the flight control system to fail to maintain normal flight. During the fall, the drone's propellers and blades are easily damaged by foreign objects (such as branches and stones). Furthermore, the impact force of falling from a high altitude can cause the drone to suffer significant damage or even disintegration.

[0004] Therefore, in response to the problems of existing multi-rotor inspection drones being easily damaged in accidental falls and having insufficient fall protection measures, a new multi-rotor inspection drone is developed. By adding a blade protection structure, a fall airbag structure, and a disintegration buffer landing gear structure to the drone, the safety of the multi-rotor inspection drone in the event of an accidental fall can be effectively improved, and the damage it suffers after a fall can be greatly reduced. Utility Model Content

[0005] To overcome the problems of existing multi-rotor inspection drones being easily damaged in accidental falls and having insufficient fall protection measures.

[0006] The technical solution of this utility model is as follows: A multi-rotor inspection drone includes a drone body, a blade protection frame, a landing gear, a buffer airbag, and a support frame. A first mounting groove is formed at the rear end of the drone body, a second mounting groove is formed at the front end of the first mounting groove, and a third mounting groove is formed at the lower end of the second mounting groove. An airbag groove is formed at the lower end of the drone body, and a through hole is formed on the upper inner wall of the airbag groove. A gas cylinder rack is installed in the third mounting groove, and three sets of high-pressure gas cylinders are installed in the gas cylinder rack. The lower end of the gas cylinder rack passes through a pipe... The drone body has a gas nozzle fixed to the hole, a buffer airbag in the airbag slot, an extension frame fixed to the lower end of the drone body, an aluminum base plate installed on the lower inner wall of the extension frame, slots at the left and right edges of the drone body, two sets of support frames symmetrically distributed front and back installed at the upper end of the landing gear, a locking block fixed to the edge of the support frame near the drone body, a blade protection frame installed at the edge of the drone body propeller, air pressure sensors installed at the lower end of the four propeller frames of the drone body, and an accelerometer installed at the upper end of the drone body.

[0007] Preferably, the card block is adapted to the card slot, and the air inlet of the buffer airbag is connected to the gas nozzle.

[0008] Preferably, the aluminum base plate has a breakage groove at its center, and the blade protection frame is conical and fitted around the propeller of the drone body.

[0009] Preferably, the left and right ends of the first mounting slot are provided with limit slots, the front end of the power control module is fixedly connected to a battery, and the rear end of the power control module is fixedly connected to a handle.

[0010] Preferably, the power control module has a second slot at both ends, and a first slot is formed on the inner wall of the end of the second slot closest to the battery.

[0011] Preferably, a spring is installed in the first tank, and a limit base is fixedly connected to the end of the spring away from the battery. A switch button is fixedly connected to the end of the limit base away from the battery.

[0012] Preferably, the outer wall of the power control module is fitted with the inner wall of the first mounting slot, the outer wall of the battery is fitted with the inner wall of the second mounting slot, the outer wall of the limiting base is fitted with the inner wall of the first slot, and the outer wall of the switch button is fitted with the inner walls of the second slot and the limiting slot.

[0013] The beneficial effects of this utility model are:

[0014] 1. The air pressure sensor and accelerometer on the drone body can monitor the flight attitude of the drone body in real time. When the drone body is rapidly descending or the distance to the ground is rapidly shortening, the high-pressure gas cylinder is activated, and high-pressure gas is output to the buffer airbag through the gas nozzle. The buffer airbag is rapidly deployed and breaks through the aluminum base plate to deploy between the two sets of landing gear to provide additional fall protection and cushioning for the drone body.

[0015] 2. The conical blade protection frame wrapped around the drone's main propeller can prevent the propeller from breaking during a fall;

[0016] 3. The snap-on support frame can absorb some of the falling force by disassembling during the descent of the drone body, thereby reducing the impact force on the drone body in the event of an accidental fall. Attached Figure Description

[0017] Figure 1 The diagram shown is a three-dimensional structural schematic of the multi-rotor inspection drone of this utility model.

[0018] Figure 2 The diagram shown is a three-dimensional disassembled view of the multi-rotor inspection drone of this utility model.

[0019] Figure 3 The diagram shown is a first three-dimensional structural schematic of the main body and blade protection frame of the multi-rotor inspection drone of this utility model.

[0020] Figure 4 The diagram shown is a second three-dimensional structural schematic of the main body and blade protection frame of the multi-rotor inspection drone of this utility model.

[0021] Figure 5 The diagram shows a three-dimensional structure of the battery, power control module, and switch button of the multi-rotor inspection drone of this utility model.

[0022] Figure 6 The diagram shown is a three-dimensional structural disassembly of the extension frame and aluminum base plate of the multi-rotor inspection drone of this utility model.

[0023] Figure 7 The diagram shown is a three-dimensional structural breakdown of the buffer airbag, gas nozzle, gas cylinder frame, and high-pressure gas cylinder of the multi-rotor inspection drone of this utility model.

[0024] Figure 8 The diagram shown is a three-dimensional disassembled view of the landing gear and support frame of the multi-rotor inspection drone of this utility model.

[0025] Explanation of reference numerals in the attached diagram: 1-UAV body, 2-blade protection frame, 3-landing gear, 4-power control module, 5-extension frame, 6-battery, 7-barometric pressure sensor, 8-airbag slot, 9-through hole, 10-slot, 11-limiting slot, 12-first mounting slot, 13-second mounting slot, 14-third mounting slot, 15-accelerometer, 16-spring, 17-first slot, 18-second slot, 19-limiting base, 20-switch button, 21-handle

[0026] 22-Aluminum base plate, 23-Buffer airbag, 24-Gas nozzle, 25-Gas cylinder rack, 26-High-pressure gas cylinder, 27-Support frame, 28-Clamping block. Detailed Implementation

[0027] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0028] Please see Figures 1-8This utility model provides an embodiment: a multi-rotor inspection drone, including a drone body 1, a blade protection frame 2, a landing gear 3, a buffer airbag 23, and a support frame 27. A first mounting groove 12 is formed at the rear end of the drone body 1, a second mounting groove 13 is formed at the front end of the first mounting groove 12, and a third mounting groove 14 is formed at the lower end of the second mounting groove 13. An airbag groove 8 is formed at the lower end of the drone body 1, and a through hole 9 is formed through the upper inner wall of the airbag groove 8. A gas cylinder rack 25 is installed in the third mounting groove 14, and three sets of high-pressure gas cylinders 26 are installed in the gas cylinder rack 25. The lower end of the gas cylinder rack 25 is connected to a pipe. A gas nozzle 24 is fixedly connected through the through hole 9. A buffer airbag 23 is set in the airbag groove 8. An extension frame 5 is fixedly connected to the lower end of the drone body 1. An aluminum base plate 22 is installed on the inner wall of the lower end of the extension frame 5. Slots 10 are opened at the left and right edges of the drone body 1. Two sets of support frames 27 are symmetrically distributed front and back on the upper end of the landing gear 3. A locking block 28 is fixedly connected to the edge of the support frame 27 near the drone body 1. A blade protection frame 2 is installed at the edge of the propeller of the drone body 1. A pressure sensor 7 is installed at the lower end of the four propeller frames of the drone body 1. An accelerometer 15 is installed at the upper end of the drone body 1.

[0029] The air pressure sensor 7 and accelerometer 15 on the drone body 1 can monitor the flight attitude of the drone body 1 in real time. When the drone body 1 is rapidly descending or the distance to the ground is rapidly decreasing, the high-pressure gas cylinder 26 is activated, and high-pressure gas is output through the gas nozzle 24 into the buffer airbag 23, causing the buffer airbag 23 to deploy rapidly and break through the aluminum base plate 22 to deploy between the two sets of landing gear 3, so as to provide additional fall protection and cushioning for the drone body 1. The conical blade protection frame 2 wrapped around the propeller of the drone body 1 can prevent the propeller on the drone body 1 from being damaged during the fall. The snap-on support frame 27 can absorb part of the falling force by disintegrating during the fall of the drone body 1, so as to reduce the impact force of the drone body 1 in the event of an accidental fall.

[0030] Please see Figures 3-8 In this embodiment, the card block 28 is adapted to the card slot 10, and the air inlet of the buffer airbag 23 is connected to the gas nozzle 24. In use, the gas nozzle 24 can deliver the high-pressure gas in the high-pressure gas cylinder 26 to the buffer airbag 23. The aluminum base plate 22 is provided with a breakage groove at the center. The blade protection frame 2 is conical and is fitted around the propeller of the drone body 1. In use, the conical blade protection frame 2 can provide a large-area wrap-around protection for the drone body 1, so as to improve the protection effect of the blade protection frame 2 on the propeller of the drone body 1.

[0031] Please see Figures 3-6In this embodiment, limiting grooves 11 are provided through the left and right ends of the first mounting groove 12. The front end of the power control module 4 is fixedly connected to the battery 6, and the rear end of the power control module 4 is fixedly connected to the handle 21. In use, the power control module 4 can control the re-discharge of the battery 6 to protect the service life of the battery 6. The left and right ends of the power control module 4 are provided with second grooves 18. The inner wall of the end of the second groove 18 near the battery 6 is provided with a first groove 17. In use, the first groove 17 and the second groove 18 are connected to each other so that the switch button 20 can slide along the inner wall of the limiting groove 11. A spring 16 is installed in the first groove 17. The end of the spring 16 away from the battery 6 is fixedly connected to the limiting base 19. The end of the limiting base 19 away from the battery 6 is fixedly connected to the switch button 20. In use, the switch button 20 can be extended and retracted by pressing the spring 16 so that the power control module 4 and the battery 6 can be quickly removed from the first mounting groove 12 and the second mounting groove 13 for replacement.

[0032] Please see Figures 3-5 In this embodiment, the outer wall of the power control module 4 is in contact with the inner wall of the first mounting groove 12, the outer wall of the battery 6 is in contact with the inner wall of the second mounting groove 13, the outer wall of the limiting base 19 is in contact with the inner wall of the first groove 17, and the outer wall of the switch button 20 is in contact with the inner walls of the second groove 18 and the limiting groove 11. In use, the limiting base 19 can prevent the switch button 20 from falling out of the first groove 17 and the second groove 18.

[0033] During the flight of the drone body 1, the air pressure sensor 7 and accelerometer 15 on the drone body 1 are used to monitor the flight attitude of the drone body 1 in real time. Once the drone body 1 is rapidly descending or the distance to the ground is rapidly shortening, the control module inside the drone body 1 will activate the high-pressure gas cylinder 26 to output high-pressure gas through the gas nozzle 24 into the buffer airbag 23, so that the buffer airbag 23 will quickly deploy and break through the aluminum base plate 22 and deploy between the two sets of landing gear 3 to provide additional fall protection and cushioning for the drone body 1.

[0034] During the descent of the drone, the blade protection frame 2, which is a cone-shaped wrapping around the propeller of the drone body 1, is used to prevent the propeller of the drone body 1 from being damaged during the fall. In addition, the snap-on support frame 27 can absorb part of the falling force by disintegrating during the fall of the drone body 1, so as to reduce the impact force of the drone body 1 when it falls unexpectedly.

[0035] When the battery 6 needs to be replaced, the user can manually press the switch button 20 to push the spring 16 along the inner wall of the second groove 18 and the limiting groove 11 to compress it, so that the switch button 20 extends and retracts into the first groove 17. At the same time, the user can pull the handle 21 to remove the power control module 4 and the battery 6 from the first mounting groove 12 and the second mounting groove 13 on the drone body 1 for replacement or maintenance.

[0036] Through the above steps, the air pressure sensor 7 and accelerometer 15 on the drone body 1 can monitor the flight attitude of the drone body 1 in real time. When the drone body 1 is rapidly descending or the distance to the ground is rapidly shortening, the high-pressure gas cylinder 26 is activated, and high-pressure gas is output through the gas nozzle 24 into the buffer airbag 23, causing the buffer airbag 23 to deploy rapidly and break through the aluminum base plate 22 to deploy between the two sets of landing gear 3, so as to provide additional fall protection and cushioning for the drone body 1. The conical blade protection frame 2 wrapped around the propeller of the drone body 1 can prevent the propeller on the drone body 1 from being damaged during the fall. The snap-on support frame 27 can absorb part of the falling force by disintegrating during the fall of the drone body 1, so as to reduce the impact force of the drone body 1 when it falls accidentally. This solves the problem that existing multi-rotor inspection drones are easily damaged when they fall accidentally and have insufficient fall protection measures.

[0037] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present invention.

Claims

1. A multi-rotor inspection unmanned aerial vehicle, comprising an unmanned aerial vehicle body (1), characterized in that: It also includes a blade protection frame (2), a landing gear (3), a buffer airbag (23), and a support frame (27). A first mounting slot (12) is provided at the rear end of the UAV body (1), a second mounting slot (13) is provided at the front end of the first mounting slot (12), and a third mounting slot (14) is provided at the lower end of the second mounting slot (13). An airbag slot (8) is provided at the lower end of the UAV body (1). A through hole (9) is provided through the upper inner wall of the airbag slot (8). A gas cylinder rack (25) is installed in the third mounting slot (14). Three sets of high-pressure gas cylinders (26) are installed in the gas cylinder rack (25). A gas nozzle (24) is fixedly connected to the lower end of the gas cylinder rack (25) through a pipe passing through the through hole (9). A buffer airbag (23) is provided in the bladder slot (8). An extension frame (5) is fixed to the lower end of the drone body (1). An aluminum base plate (22) is installed on the inner wall of the lower end of the extension frame (5). Slots (10) are provided at the left and right edges of the drone body (1). Two sets of support frames (27) are symmetrically distributed at the front and back of the upper end of the landing gear (3). A locking block (28) is fixed to the edge of the support frame (27) near the drone body (1). A blade protection frame (2) is installed at the edge of the propeller of the drone body (1). A pressure sensor (7) is installed at the lower end of the four propeller frames of the drone body (1). An accelerometer (15) is installed at the upper end of the drone body (1).

2. The multi-rotor inspection drone according to claim 1, characterized in that: The card block (28) is adapted to the card slot (10), and the air inlet of the buffer airbag (23) is connected to the gas nozzle (24).

3. The multi-rotor inspection drone according to claim 2, characterized in that: A breakage groove is provided in the center of the aluminum base plate (22), and the blade protection frame (2) is conical and fitted around the propeller of the UAV body (1).

4. The multi-rotor inspection drone according to claim 3, characterized in that: Limiting grooves (11) are opened through the left and right ends of the first mounting groove (12). A battery (6) is fixedly connected to the front end of the power control module (4), and a handle (21) is fixedly connected to the rear end of the power control module (4).

5. The multi-rotor inspection drone according to claim 4, characterized in that: The power control module (4) has a second slot (18) at both ends, and a first slot (17) is provided on the inner wall of the end of the second slot (18) near the battery (6).

6. The multi-rotor inspection drone according to claim 5, characterized in that: A spring (16) is installed in the first groove (17). The end of the spring (16) away from the battery (6) is fixedly connected to a limit base (19). The end of the limit base (19) away from the battery (6) is fixedly connected to a switch button (20).

7. The multi-rotor inspection drone according to claim 6, characterized in that: The outer wall of the power control module (4) is in contact with the inner wall of the first mounting groove (12), the outer wall of the battery (6) is in contact with the inner wall of the second mounting groove (13), the outer wall of the limiting base (19) is in contact with the inner wall of the first groove (17), and the outer wall of the switch button (20) is in contact with the inner walls of the second groove (18) and the limiting groove (11).

Images