Inspection unmanned aerial vehicle

Abstract

The utility model discloses an inspection unmanned aerial vehicle, relates to unmanned aerial vehicle technical field, the unmanned aerial vehicle includes crate, connecting rod, landing subassembly, said crate side wall is fixedly connected with four connecting rod, every two is opposite to each other, four connecting rod all is provided with the propeller, the lower surface of crate is provided with the monitoring probe, the landing subassembly is provided with the monitoring probe. A landing assembly is arranged on the upper surface of the machine box and comprises a first fixing plate, a parachute groove, a first rotating groove and a rotating cover groove are formed in the upper surface of the machine box, and two symmetrical first rotating shafts are rotationally connected to the inner side wall of the first rotating groove through bearings. Through the landing assembly, the falling speed of the unmanned aerial vehicle is reduced, impact force borne by the unmanned aerial vehicle is reduced, and damage to the unmanned aerial vehicle is reduced; and through the protection assembly, the monitoring probe is protected from directly colliding with stones when the unmanned aerial vehicle lands, and the monitoring probe is prevented from being damaged.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an inspection unmanned aerial vehicle. Background Art

[0002] A wind turbine is an electrical device that converts wind energy into mechanical work, which drives the rotor to rotate and ultimately outputs alternating current.

[0003] With the development of the times, the use of drones has become more and more extensive in the field of wind power generation. Wind turbine blades need to be inspected regularly, but due to the high position and large size of the blades, the previous method of manual climbing inspection has gradually been eliminated. Nowadays, drones are more often used for inspection, which is more efficient and safer. However, existing drones are easily damaged when they encounter strong objects such as walls during the inspection process, and they will experience secondary impact when they fall to the ground. Not only will the drones be seriously damaged, but the monitoring probes on the drones are also extremely susceptible to impact damage.

[0004] Based on this, a patrol drone is now provided to eliminate the drawbacks of existing devices. Utility Model Content

[0005] The purpose of the utility model is to provide an inspection drone to solve the shortcomings of modern products in the background technology.

[0006] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0007] A patrol inspection drone comprises a chassis, a connecting rod, and a landing assembly, wherein the side wall of the chassis is fixedly connected with four connecting rods facing each other, each of the four connecting rods is provided with a propeller, a monitoring probe is provided on the lower surface of the chassis, and a landing assembly is provided on the upper surface of the chassis;

[0008] The landing assembly includes a first fixed plate, and the upper surface of the chassis is provided with a parachute groove, a first rotating groove, and a rotating cover groove. The inner side wall of the first rotating groove is rotatably connected to two symmetrical first rotating shafts through bearings, and the inner side wall of the rotating cover groove is slidably connected to two relative rotating covers, the rotating cover is fixedly connected to one of the first rotating shafts, and the rotating cover is rotatably connected to the other first rotating shaft through bearings. The side wall of the rotating cover is fixedly connected to the first fixed plate, and the opposite side walls of the two first fixed plates are both provided with first electromagnets. A parachute is provided in the parachute groove, and a circuit breaker is provided in the chassis, and the circuit breaker is electrically connected to the first electromagnet.

[0009] On the basis of the above technical solutions, the present invention also provides the following optional technical solutions:

[0010] In an optional scheme: a protective component is provided on the lower surface of the chassis, and the protective component includes a second rotating shaft, a second rotating groove and a protective cover groove are opened on the lower surface of the chassis, the inner side wall of the second rotating groove is rotatably connected to two symmetrical second rotating shafts through bearings, a coil spring is fixedly connected between the second rotating shaft and the inner side wall of the second rotating groove, the second rotating shaft is fixedly connected to a protective cover, the protective cover is rotatably connected to another second rotating shaft through a bearing, a third fixed plate is fixedly connected to the lower surface of the chassis, a second electromagnet is provided on the side wall of the third fixed plate, a second fixed plate is fixedly connected to the side wall of the protective cover, a magnet is provided on the side wall of the second fixed plate, the protective cover is slidably connected to the inner side wall of the protective cover groove, and the second electromagnet is electrically connected to the circuit breaker.

[0011] In an optional solution: a buffer cavity is opened on the lower surface of the chassis, a buffer plate is slidably connected to the inner wall of the buffer cavity, a damper and a damping spring are fixedly connected between the buffer plate and the inner wall of the buffer cavity, and the lower surface of the buffer plate is fixedly connected to the monitoring probe.

[0012] In an optional solution: the side walls of the four connecting rods are all provided with protective mesh covers.

[0013] In an optional solution: a ventilation hole is opened on the lower surface of the chassis, and the ventilation hole is connected to the parachute slot.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0015] 1. The utility model reduces the falling speed of the drone through the landing component, reduces the impact force on the drone, and reduces the damage to the drone.

[0016] 2. The utility model uses a protective component to protect the monitoring probe from directly hitting stones when the drone lands, thereby avoiding damage to the monitoring probe. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural schematic diagram of the utility model.

[0018] Figure 2 This is a first viewing angle diagram of the present invention.

[0019] Figure 3 It is a schematic diagram of the opening of the parachute of the utility model.

[0020] Figure 4 It is a schematic diagram of the internal structure of the chassis of the present utility model.

[0021] Figure 5 For the utility model Figure 2 Enlarged view of point A in the middle.

[0022] Figure 6 For the utility model Figure 3 Enlarged view of point B in the middle.

[0023] Figure 7 It is a schematic diagram of the structure of the landing assembly of the utility model.

[0024] Figure 8 This is a schematic diagram of the protective component structure of the utility model.

[0025] Notes on figure numbers: 1 chassis, 2 ventilation holes, 3 protective mesh, 4 connecting rod, 5 parachute, 6 landing assembly, 7 protective assembly, 8 parachute slot, 9 first rotating slot, 10 rotating cover, 11 first fixed plate, 12 first rotating axis, 14 protective cover, 15 second fixed plate, 16 second rotating slot, 17 monitoring probe, 18 second rotating axis, 20 third fixed plate, 21 magnet, 22 buffer plate, 23 buffer chamber, 24 damper, 25 damping spring, 26 first electromagnet, 27 second electromagnet. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0027] In one embodiment, Figure 1-Figure 8 As shown, a patrol drone includes a chassis 1, a connecting rod 4, and a landing assembly 6. The side wall of the chassis 1 is fixedly connected with four connecting rods 4 that are opposite to each other, and the four connecting rods 4 are all provided with propellers. A monitoring probe 17 is provided on the lower surface of the chassis 1, and a landing assembly 6 is provided on the upper surface of the chassis 1;

[0028] The landing assembly 6 includes a first fixed plate 11, and a parachute groove 8, a first rotating groove 9, and a rotating cover groove are provided on the upper surface of the chassis 1. The inner wall of the first rotating groove 9 is rotatably connected to two symmetrical first rotating shafts 12 through bearings, and the inner wall of the rotating cover groove is slidably connected to two relative rotating covers 10. The rotating cover 10 is fixedly connected to one of the first rotating shafts 12, and the rotating cover 10 is rotatably connected to the other first rotating shaft 12 through bearings. The side wall of the rotating cover 10 is fixedly connected to the first fixed plate 11, and the opposite side walls of the two first fixed plates 11 are provided with first electromagnets 26. A parachute 5 is provided in the parachute groove 8, and a circuit breaker is provided in the chassis 1, and the circuit breaker is electrically connected to the first electromagnet 26.

[0029] When the drone hits a wall or obstacle and the propeller of the drone is damaged, the circuit breaker works. The circuit breaker can automatically cut off the power supply when the circuit is overloaded or short-circuited, thereby playing a protective role. At this time, no current flows inside the aircraft, the first electromagnet 26 loses its magnetism, and the two rotating covers 10 are unfolded under the drive of the coil spring. The parachute 5 emerges from the parachute slot 8 and opens under the action of the airflow, thereby reducing the falling speed of the drone, reducing the impact force on the drone, and reducing the damage to the drone.

[0030] In one embodiment, Figure 5 and Figure 8 As shown, a protective component 7 is provided on the lower surface of the chassis 1, and the protective component 7 includes a second rotating shaft 18. A second rotating groove 16 and a protective cover groove are opened on the lower surface of the chassis 1. The inner wall of the second rotating groove 16 is rotatably connected to two symmetrical second rotating shafts 18 through bearings, and a coil spring is fixedly connected between the second rotating shaft 18 and the inner wall of the second rotating groove 16. The second rotating shaft 18 is fixedly connected to a protective cover 14, and the protective cover 14 is rotatably connected to another second rotating shaft 18 through a bearing. A third fixed plate 20 is fixedly connected to the lower surface of the chassis 1, and a second electromagnet 27 is provided on the side wall of the third fixed plate 20. The side wall of the protective cover 14 is fixedly connected to the second fixed plate 15, and a magnet 21 is provided on the side wall of the second fixed plate 15. The protective cover 14 is slidably connected to the inner wall of the protective cover groove, and the second electromagnet 27 is electrically connected to the circuit breaker.

[0031] The magnet 21 is no longer attracted by the second electromagnet 27. Under the action of the coil spring, the two protective covers 14 move toward each other and close, wrapping the monitoring probe 17 inside the protective cover 14. When the drone lands, the monitoring probe 17 is protected from directly hitting the stone, avoiding damage to the monitoring probe 17.

[0032] In one embodiment, Figure 4 As shown, a buffer cavity 23 is opened on the lower surface of the chassis 1, and a buffer plate 22 is slidably connected to the inner wall of the buffer cavity 23. A damper 24 and a damping spring 25 are fixedly connected between the buffer plate 22 and the inner wall of the buffer cavity 23, and the lower surface of the buffer plate 22 is fixedly connected to the monitoring probe 17.

[0033] When the chassis 1 falls and impacts the ground, the damping spring 25 and the damper 24 cooperate to provide a buffer for the monitoring probe 17, thereby reducing the impact force received by the monitoring probe 17.

[0034] In one embodiment, Figure 1 As shown, the side walls of the four connecting rods 4 are all provided with protective mesh covers 3.

[0035] The protective net 3 can protect the propeller of the drone from damage when the drone does not collide with the wall seriously.

[0036] In one embodiment, Figure 2 As shown, the lower surface of the chassis 1 is provided with a ventilation hole 2, and the ventilation hole 2 is connected to the parachute slot 8. When the drone lands, air flows through the ventilation hole 2 to prop up the parachute 5.

[0037] The above embodiment discloses an inspection drone. When the drone hits a wall or obstacle during the inspection process, causing the drone propeller to be damaged and unable to rotate, the circuit breaker works. The circuit breaker can automatically cut off the power supply when the circuit is overloaded or short-circuited, thereby playing a protective role. At this time, no current flows inside the aircraft, the first electromagnet 26 loses its magnetism, the two rotating covers 10 are deployed under the drive of the coil spring, and the parachute 5 emerges from the parachute slot 8 and is opened under the action of the airflow, thereby reducing the falling speed of the drone, reducing the impact force on the drone, and reducing the damage to the drone.

[0038] At the same time, since there is no current flowing in the drone, the magnet 21 is no longer attracted by the second electromagnet 27. Under the action of the coil spring, the two protective covers 14 move towards each other and close, wrapping the monitoring probe 17 inside the protective cover 14. When the drone lands, the monitoring probe 17 is protected from directly hitting the stone, thereby avoiding damage to the monitoring probe 17.

[0039] When the chassis 1 falls and impacts the ground, the damping spring 25 and the damper 24 cooperate to provide a buffer for the monitoring probe 17, thereby reducing the impact force received by the monitoring probe 17;

[0040] The protective net cover 3 can protect the propeller of the drone from being damaged when the drone collides with the wall in a minor manner.

[0041] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art who is familiar with the present technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. A patrol drone, characterized in that: The invention comprises a chassis (1), a connecting rod (4), and a landing assembly (6); the side wall of the chassis (1) is fixedly connected with four connecting rods (4) which are opposite to each other in pairs; the connecting rods (4) are provided with propellers; the lower surface of the chassis (1) is provided with a monitoring probe (17); and the upper surface of the chassis (1) is provided with a landing assembly (6); The landing assembly (6) comprises a first fixed plate (11); the upper surface of the chassis (1) is provided with a parachute slot (8), a first rotating slot (9), and a rotating cover slot; the inner side wall of the first rotating slot (9) is rotatably connected to two symmetrical first rotating shafts (12) via a bearing; the inner side wall of the rotating cover slot is slidably connected to two opposite rotating covers (10); the rotating cover (10) is fixedly connected to one of the first rotating shafts (12); the rotating cover (10) is rotatably connected to the other first rotating shaft (12) via a bearing; the side wall of the rotating cover (10) is fixedly connected to the first fixed plate (11); the opposite side walls of the two first fixed plates (11) are both provided with a first electromagnet (26); a parachute (5) is provided in the parachute slot (8); a circuit breaker is provided in the chassis (1); the circuit breaker is electrically connected to the first electromagnet (26).

2. The inspection drone according to claim 1, characterized in that: The lower surface of the chassis (1) is provided with a protective component (7), the protective component (7) comprising a second rotating shaft (18), the lower surface of the chassis (1) is provided with a second rotating groove (16) and a protective cover groove, the inner side wall of the second rotating groove (16) is rotatably connected to two symmetrical second rotating shafts (18) via bearings, a coil spring is fixedly connected between the second rotating shaft (18) and the inner side wall of the second rotating groove (16), the second rotating shaft (18) is fixedly connected to a protective cover (14), and the protective cover (14) is fixedly connected to the protective cover. The protective cover (14) is rotatably connected to another second rotating shaft (18) via a bearing; a third fixed plate (20) is fixedly connected to the lower surface of the chassis (1); a second electromagnet (27) is provided on the side wall of the third fixed plate (20); a second fixed plate (15) is fixedly connected to the side wall of the protective cover (14); a magnet (21) is provided on the side wall of the second fixed plate (15); the protective cover (14) is slidably connected to the inner side wall of the protective cover groove; and the second electromagnet (27) is electrically connected to the circuit breaker.

3. The inspection drone according to claim 2, characterized in that: A buffer cavity (23) is provided on the lower surface of the chassis (1); a buffer plate (22) is slidably connected to the inner wall of the buffer cavity (23); a damper (24) and a damping spring (25) are fixedly connected between the buffer plate (22) and the inner wall of the buffer cavity (23); and the lower surface of the buffer plate (22) is fixedly connected to the monitoring probe (17).

4. The inspection drone according to claim 1, characterized in that: The side walls of the four connecting rods (4) are all provided with protective mesh covers (3).

5. The inspection drone according to claim 1, characterized in that: A ventilation hole (2) is provided on the lower surface of the chassis (1), and the ventilation hole (2) is connected to the parachute slot (8).

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