Air crash protection positioning device of high-low pressure inspection unmanned aerial vehicle

Abstract

The invention discloses an air crash protection positioning device of a high-low pressure inspection unmanned aerial vehicle, and relates to the technical field of inspection unmanned aerial vehicles. The device comprises a machine body, sliding grooves are evenly formed in the edge of the middle of the machine body, limiting grooves are symmetrically formed in the upper sides and the lower sides of the sliding grooves in the edge of the machine body, an undercarriage is arranged at the bottom of the machine body, a motor is fixedly installed in the center of the top of the machine body, and connecting rods are slidably connected to the sliding grooves in the machine body; and one end of the outer side of each connecting rod extends to the outer side of the machine body, and a propeller is fixedly mounted at one end of the outer side of each connecting rod. When the unmanned aerial vehicle crashes, the propellers and the vehicle body can be protected, the propellers are prevented from being damaged, meanwhile, normal operation of the positioning assemblies in the vehicle body is guaranteed, the unmanned aerial vehicle is convenient to find, the protection assemblies do not interfere with the moving stability and trafficability of the unmanned aerial vehicle, generated impact can be buffered, and the safety of the unmanned aerial vehicle is improved. And the air crash risk is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of inspection drones, and particularly to a crash protection and positioning device for high- and low-voltage inspection drones. Background Art

[0002] After the power system is built, in order to ensure the stable operation of the power system, it is necessary to regularly inspect the high- and low-voltage lines of the power system. Since the power lines are erected at high altitudes, drones are now mostly used for inspection. Due to the intricate power lines and electromagnetic interference, high- and low-voltage inspection drones have a greater risk of crashing, so the crash protection and positioning of drones are even more important.

[0003] However, the existing high- and low-voltage inspection drones still have the following defects during use:

[0004] 1. Most of the crash protection devices of existing drones are located at the bottom of the drones. When the drones lose control and roll and fall, they cannot effectively protect the propeller parts and the main body of the aircraft, which will lead to the damage of the drones and the failure of positioning. Some protection devices installed on the outer periphery of the aircraft body will reduce the moving stability of the drones and also reduce the passing performance of the drones.

[0005] 2. After the propeller wings of the existing inspection drones take off, their positions are relatively fixed. When facing complex power lines, they cannot be telescopically adjusted accordingly, and the passing performance needs to be improved. At the same time, they cannot provide anti-collision protection after touching the power lines, increasing the risk of crashing. Summary of the Invention

[0006] The purpose of the present invention is to solve the problems that the propeller parts and the main body of the aircraft cannot be effectively protected, which will lead to the damage of the drones and the failure of positioning, installing protection devices will reduce the moving stability and passing performance of the drones, and there is no anti-collision protection after touching the power lines, increasing the risk of crashing. The present invention provides a crash protection and positioning device for high- and low-voltage inspection drones.

[0007] The present invention specifically adopts the following technical solutions to achieve the above purpose:

[0008] A crash protection and positioning device for a high - low voltage inspection unmanned aerial vehicle, comprising a fuselage. At the edge of the middle part of the fuselage, sliding grooves are evenly opened. On both the upper and lower sides of the sliding grooves at the edge of the fuselage, limiting grooves are symmetrically opened. A landing gear is arranged at the bottom of the fuselage. A motor is fixedly installed at the center of the top of the fuselage. Connecting rods are slidably connected to the sliding grooves inside the fuselage. One end of the outer side of the connecting rod extends to the outside of the fuselage, and propellers are fixedly installed at one ends of the outer sides of the connecting rods. An adjusting assembly is arranged inside the fuselage on the inner sides of the connecting rods. The adjusting assembly is used for synchronously telescoping and adjusting the connecting rods and the propellers. Protective assemblies are arranged on the upper and lower sides of the adjusting assembly. The protective assemblies are used for protecting the propellers and the fuselage. A camera is rotatably connected to the bottom of the fuselage in a limited way, and the camera is used to realize the inspection of high - low voltage lines.

[0009] Furthermore, the adjusting assembly includes an arc - shaped strip. The arc - shaped strip is rotatably connected to the inner side of the middle part of the fuselage in a limited way. Installation clamping plates are evenly fixedly installed on the inner side of the arc - shaped strip. The connecting rod penetrates through the arc - shaped strip inward and is slidably connected to the arc - shaped strip in a limited way. A first rack is fixedly installed on the inner side of the connecting rod. The first rack is located between the installation clamping plates and is slidably connected to the installation clamping plates in a limited way, so that the connecting rod and the first rack can perform stable telescopic movement. At the upper and lower ends of the inner side of the installation clamping plate, installation seats are symmetrically fixedly installed. At one ends of the installation seats far away from the installation clamping plates, limiting frames are fixedly installed. The limiting frames extend inward. Rack two are slidably connected to the inside of the limiting frames in a limited way. Gears are rotatably connected to the inner sides of the upper and lower symmetric installation seats in a limited way. A threaded disk is rotatably connected to the middle part inside the fuselage. Cylindrical barrels are symmetrically fixedly installed at one ends of the upper and lower limiting frames far away from each other.

[0010] Furthermore, teeth are opened on both the upper and lower sides of the first rack, and teeth are opened on the adjacent side of the upper and lower rack two. The gears are located between the first rack and the upper and lower rack two and are meshed with the first rack and the rack two respectively. Therefore, when the first rack moves, the upper and lower rack two can be driven to move in the opposite direction through the action of the gears.

[0011] Furthermore, the threaded disk is in transmission connection with the motor, and the threaded disk is composed of two upper - and - lower symmetric disks and a central fixed column. Upper - and - lower symmetric spiral teeth are opened on the adjacent side of the two upper - and - lower symmetric disks, and the motor is used to drive the threaded disk to rotate.

[0012] Further, when the connecting rod and the first rack extend to the outermost side, the inner end of the first rack is still located inside the mounting splint, and the inner end of the first rack extends between the disks that are symmetrically arranged above and below the threaded disk. The teeth on both the upper and lower sides of the first rack mesh with the spiral teeth on the side adjacent to the middle disk of the threaded disk. Therefore, when the threaded disk rotates, it can drive the first rack to perform telescopic movement. The motor is remotely controlled, and a weightlessness sensing component is provided in the control system. That is, when the drone crashes and experiences weightlessness, it can trigger the motor to rotate in one direction, and the rotation direction is to drive the threaded disk to retract the first rack inward, thereby causing the first rack to drive the connecting rod and the propeller to retract.

[0013] Further, the symmetrically arranged cylindrical tubes above and below both extend into the interior of the fuselage and are rotationally connected to the fuselage with limited rotation, improving the stability of the adjustment component installed inside the fuselage. The end of the cylindrical tube away from the limit frame is evenly and fixedly installed with protrusions. The protrusions are slidably connected with limited movement inside the fuselage, and springs are fixedly connected between both sides of the protrusions and the inner wall of the fuselage, enabling the adjustment component, the connecting rod, and the propeller to perform elastic rotation.

[0014] Further, the protection component includes a slider. The slider is slidably connected with limited movement inside the limit groove. A rolling ball is rotatably connected with limited movement in the middle of the inner side of the slider. A protection rod is arranged between the rolling ball and the second rack. One end of the protection rod is hinged to the outer end of the second rack, and the other side passes through the rolling ball and extends to the outside of the fuselage and is slidably connected with the rolling ball. Cooperating with the rotation of the rolling ball, the protection rod can perform telescopic movement around the rolling ball.

[0015] Further, the outer end of the protection rod is in the shape of a spherical ball with a larger diameter, and the protection rod is made of an elastic material, which can buffer the impact.

[0016] The beneficial effects of the present invention are as follows:

[0017] 1. In the present invention, through the cooperation of the adjustment component and the protection component, when the drone crashes, the propeller can be retracted. At the same time, the protection rods on the periphery of the fuselage extend outward and unfold. When the drone crashes and tumbles and contacts the ground in an indefinite direction, it can protect the propeller and the fuselage, avoid damage to the propeller, and ensure the normal operation of the positioning component inside the fuselage, facilitating the search for the drone. At the same time, when the drone is operating normally, the protection rods are in a retracted state and will not interfere with the stability and passability of the drone's movement.

[0018] 2. In the present invention, through the design of the adjustment component, when facing complex power lines, the connecting rod and the propeller can be telescopically adjusted, improving the passability of the drone. At the same time, when the connecting rod and the propeller collide, they can perform elastic swinging, thereby buffering the impact and reducing the risk of crashing. Brief Description of the Drawings

[0019] Figure 1 is a schematic three - dimensional structure of the present invention Figure 1 ;

[0020] Figure 2 is a schematic three - dimensional structure of the present invention Figure 2 ;

[0021] Figure 3 is a schematic sectional three - dimensional structure diagram of the present invention;

[0022] Figure 4 is a schematic internal three - dimensional structure diagram of the present invention;

[0023] Figure 5 is a schematic internal partial three - dimensional structure diagram of the present invention;

[0024] Figure 6 is an exploded view of the internal partial three - dimensional structure of the present invention;

[0025] Figure 7 is a schematic three - dimensional structure diagram of the adjusting component and the protection component of the present invention;

[0026] Figure 8 is a schematic sectional three - dimensional structure diagram of the adjusting component and the protection component of the present invention;

[0027] Figure 9 is a schematic three - dimensional structure diagram of the second rack and the protection component of the present invention;

[0028] Figure 10 is a schematic three - dimensional structure of the cylindrical barrel of the present invention Figure 1 ;

[0029] Figure 11 is a schematic three - dimensional structure of the cylindrical barrel of the present invention Figure 2 。

[0030] Reference Numerals: 1, body; 11, chute; 12, limit groove; 2, landing gear; 3, motor; 4, connecting rod; 5, propeller; 6, adjusting component; 61, arc bar; 62, mounting clamp; 63, first rack; 64, mounting seat; 65, limit frame; 66, second rack; 67, gear; 68, threaded disc; 69, cylindrical barrel; 691, convex block; 692, spring; 7, protection component; 71, slider; 72, ball; 73, protection rod; 8, camera. Detailed Description of the Invention

[0031] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0032] A crash protection and positioning device for a high-low voltage inspection UAV according to a preferred embodiment of the present invention will be described in detail below. As Figures 1 - 3 shown, a crash protection and positioning device for a high-low voltage inspection UAV includes a fuselage 1. Slide grooves 11 are evenly formed at the edges of the middle part of the fuselage 1. Limit grooves 12 are symmetrically formed on both the upper and lower sides of the slide grooves 11 at the edges of the fuselage 1. A landing gear 2 is arranged at the bottom of the fuselage 1. A motor 3 is fixedly installed at the center of the top of the fuselage 1. Connecting rods 4 are slidably connected to the inside of the slide grooves 11 of the fuselage 1. One end of the outer side of the connecting rod 4 extends to the outside of the fuselage 1, and propellers 5 are fixedly installed at one ends of the outer sides of the connecting rods 4. An adjusting assembly 6 is arranged inside the fuselage 1 on the inner sides of the connecting rods 4. The adjusting assembly 6 is used for synchronously telescoping and adjusting the connecting rods 4 and the propellers 5. Protective assemblies 7 are arranged on both the upper and lower sides of the adjusting assembly 6. The protective assemblies 7 are used for protecting the propellers 5 and the fuselage 1. The bottom of the fuselage 1 is rotatably connected in a limited way with a camera 8, and the inspection of high-low voltage lines is realized by using the camera 8.

[0033] During the inspection, the propellers 5 are used to drive the fuselage 1 to rise and move. At the same time, with the multi-angle adjustable rotation of the camera 8, the high-low voltage lines are inspected. During the inspection process, when encountering a relatively narrow line spacing, the connecting rods 4 and the propellers 5 can be synchronously telescoped and adjusted through the adjusting assembly 6, so as to improve the passing performance of the UAV. When an accident occurs and the UAV crashes, the protective assemblies 7 can protect the propellers 5 and the fuselage 1, avoid the damage of the propellers 5, and ensure the normal operation of the positioning assembly inside the fuselage 1, which is convenient for finding the UAV.

[0034] Furthermore, as Figures 3 - 8 、 Figure 10 、 Figure 11 shown, the adjusting assembly 6 includes an arc strip 61. The arc strip 61 is rotatably connected in a limited way to the inner side of the middle part of the fuselage 1. Mounting clamping plates 62 are evenly and fixedly installed on the inner side of the arc strip 61. The connecting rod 4 penetrates through the arc strip 61 inward and is slidably connected to the arc strip 61 in a limited way. A first rack 63 is fixedly installed on the inner side of the connecting rod 4. The first rack 63 is located between the mounting clamping plates 62 and is slidably connected to the mounting clamping plates 62 in a limited way, so that the connecting rod 4 and the first rack 63 can perform stable telescoping movement.

[0035] Inside the body 1, a threaded disc 68 is rotatably connected in the middle in a limited manner. When the connecting rod 4 and the first rack 63 extend to the outermost side, the inner end of the first rack 63 is still located inside the mounting clamp 62, and the inner end of the first rack 63 extends between the discs that are symmetrically arranged above and below the threaded disc 68. The teeth on the upper and lower sides of the first rack 63 mesh with the spiral teeth on the adjacent side of the disc in the threaded disc 68. Therefore, when the threaded disc 68 rotates, it can drive the first rack 63 to move telescopically. The motor 3 is remotely controlled, and the control system is provided with a weightlessness sensing component. That is, when the drone crashes and experiences weightlessness (by remotely controlling the rotation of the motor or the electric machine, and the sensing of weightlessness is an existing conventional means, which is not elaborated much in this invention application), it can trigger the motor 3 to rotate in one direction, and the rotation direction is to drive the threaded disc 68 to retract the first rack 63 inward, and then the first rack 63 drives the connecting rod 4 and the propeller 5 to retract.

[0036] The principle of synchronously adjusting the telescopic movement of the connecting rod 4 and the propeller 5 through the adjusting component 6 is as follows:

[0037] When the drone needs to pass through a narrow line spacing, the remote control system drives the motor 3 to rotate through the remote control system, and then drives the threaded disc 68 to rotate. By using the design that the spiral teeth on the adjacent side of the disc in the threaded disc 68 mesh with the teeth on the upper and lower sides of the first rack 63, during the rotation of the threaded disc 68, it can drive the first rack 63 to contract inward synchronously, and then drive the connecting rod 4 and the propeller 5 to contract synchronously to pass through the narrow line spacing. After passing through, the motor 3 is used to drive the reverse rotation of the threaded disc 68 to make the connecting rod 4 and the propeller 5 extend outward again, and stably drive the body 1 to lift and move.

[0038] Further, as Figures 4 - 9 shown, at the upper and lower ends inside the mounting clamp 62, mounting seats 64 are symmetrically and fixedly installed. At the ends of the mounting seats 64 away from the mounting clamp 62, limit frames 65 are fixedly installed. The limit frames 65 extend inward. Inside the limit frames 65, second racks 66 are slidably connected in a limited manner. Inside the symmetrically arranged upper and lower mounting seats 64, gears 67 are rotatably connected in a limited manner. Teeth are provided on the upper and lower sides of the first rack 63, and teeth are provided on the adjacent sides of the upper and lower second racks 66. The gears 67 are located between the first rack 63 and the upper and lower second racks 66 and mesh with both the first rack 63 and the second racks 66. Therefore, when the first rack 63 moves, through the action of the gears 67, it can drive the upper and lower second racks 66 to move in opposite directions simultaneously.

[0039] The protection component 7 includes a slider 71. The slider 71 is internally and limit - slidably connected to the limit groove 12. In the middle of the inner side of the slider 71, a rolling ball 72 is limit - rollingly connected. Between the rolling ball 72 and the second rack 66, there is a protection rod 73. One end of the protection rod 73 is hinged to the outer end of the second rack 66. The other side passes through the rolling ball 72 and extends to the outside of the machine body 1 and is slidably connected to the rolling ball 72. Cooperating with the rotation of the rolling ball 72, the protection rod 73 can telescopically move around the rolling ball 72.

[0040] One end of the outer side of the protection rod 73 is in the shape of a spherical ball with a larger diameter, and the protection rod 73 is made of an elastic material, which can buffer impacts.

[0041] The principle of protecting the propeller 5 and the machine body 1 by the protection component 7 is as follows:

[0042] When the drone suffers an accident and crashes, the drone will be in a weightless state. Then, through the design of the weight - loss induction component in the remote control system of the motor 3, the motor 3 can be triggered to drive the threaded disk 68 to rotate unidirectionally, and the rotation direction is to drive the threaded disk 68 to make the first rack 63 retract inward. While the first rack 63 drives the connecting rod 4 and the propeller 5 to retract synchronously, by the action of the gear 67 meshing between the first rack 63 and the second rack 66, the upper and lower second racks 66 can be driven to move outward in the limit frame 65. During the process of the second rack 66 moving outward, through the hinge connection between the outer end of the second rack 66 and the protection rod 73, and the limit of the protection rod 73 by the rolling ball 72 in the slider 71, the upper and lower protection rods 73 can be pushed to extend outward. Thus, when the drone crashes and tumbles and contacts the ground in an indefinite direction, the retracted threaded disk 68 and the machine body 1 can be protected.

[0043] During normal take - off and operation, the propeller 5 and the connecting rod 4 extend outward, and the first rack 63 also extends outward. The gear 67 drives the second rack 66 to move inward in the limit frame 65, and then pulls the protection rod 73 to retract, which will not interfere with the stability and passability of the drone's movement.

[0044] Furthermore, as Figures 3 - 4 shown, symmetrically fixed at the mutually - distant ends of the upper and lower limit frames 65 are cylindrical barrels 69. The upper and lower symmetric cylindrical barrels 69 both extend into the machine body 1 and are limit - rotationally connected to the machine body 1, improving the stability of the installation of the adjustment component 6 inside the machine body 1. At the end of the cylindrical barrel 69 far from the limit frame 65, uniformly fixed are convex blocks 691. The convex blocks 691 are limit - slidably connected inside the machine body 1, and between both sides of the convex blocks 691 and the inner wall of the machine body 1, spring 692 are fixedly connected, enabling the adjustment component 6 and the connecting rod 4 and the propeller 5 to perform elastic rotation.

[0045] Through the sliding connection of the connecting rod 4 in the sliding groove 11 and the sliding connection of the slider 71 in the limiting groove 12, the adjusting component 6 and the protection component 7 can swing synchronously. With the action of the spring 692 between the convex block 691 on the cylindrical barrel 69 and the inner wall of the body 1, when the propeller 5 collides with the connecting rod 4, it can swing elastically, thereby buffering the impact and reducing the risk of crashing.

[0046] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be obvious to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to these embodiments shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A crash protection positioning device for a high-low voltage inspection UAV, comprising a body (1), characterized in that: The middle edge of the machine body (1) is evenly provided with a slide groove (11), and the upper and lower sides of the slide groove (11) at the edge of the machine body (1) are symmetrically provided with a limit groove (12). The bottom of the machine body (1) is provided with a landing gear (2), and the center of the top of the machine body (1) is fixedly installed with a motor (3). The slide groove (11) inside the machine body (1) is slidably connected with a connecting rod (4), and the outer end of the connecting rod (4) extends to the outside of the machine body (1), and the outer end of the connecting rod (4) is fixedly installed with a propeller (5). The inner side of the connecting rod (4) inside the machine body (1) is provided with an adjustment component (6), and the adjustment component (6) is used for synchronously telescopically adjusting the connecting rod (4) and the propeller (5). The upper and lower sides of the adjustment component (6) are provided with a protective component (7), and the protective component (7) is used for protecting the propeller (5) and the machine body (1).

2. The crash protection positioning device for high and low voltage inspection UAV according to claim 1 is characterized in that: The regulating component (6) comprises: An arc strip (61), the inner side of the middle part of the machine body (1) being rotationally connected with the arc strip (61); A mounting clamp (62), the inner side of the arc strip (61) is evenly and fixedly mounted with the mounting clamp (62); Rack 1 (63), the connecting rod (4) penetrates the arc bar (61) inwardly and is connected to the arc bar (61) in a limited sliding manner, the inner side of the connecting rod (4) is fixedly installed with rack 1 (63), the rack 1 (63) is located between the mounting clamps (62) and is connected to the mounting clamps (62) in a limited sliding manner; A mounting seat (64), the mounting seats (64) being symmetrically fixedly mounted on the upper and lower ends of the inner side of the mounting clamping plate (62); A limit frame (65), one end of the mounting seat (64) away from the mounting clamp (62) is fixedly mounted with the limit frame (65), and the limit frame (65) extends inwardly; Rack 2 (66), the interior of the limiting frame (65) is connected to rack 2 (66) in a limiting sliding manner; Gear (67), the inner sides of the upper and lower symmetrical mounting seats (64) are both connected with gears (67) for limited rotation; A threaded disc (68), the middle part of the body (1) being rotationally connected with the threaded disc (68); The cylindrical tube (69) is symmetrically fixedly mounted on the ends of the upper and lower limit frames (65) that are away from each other.

3. The crash protection positioning device for high and low voltage inspection UAV according to claim 2 is characterized in that: The upper and lower sides of the rack 1 (63) are provided with teeth, and the adjacent side of the rack 2 (66) on the upper and lower sides is provided with teeth. The gear (67) is located between the rack 1 (63) and the rack 2 (66) on the upper and lower sides, and is meshed with the rack 1 (63) and the rack 2 (66).

4. The crash protection positioning device for high and low voltage inspection UAV according to claim 2 is characterized in that: The threaded disc (68) is drivingly connected to the motor (3), and the threaded disc (68) is composed of two vertically symmetrical discs and a centrally fixed column, and vertically symmetrical vortex teeth are provided on adjacent sides of the two vertically symmetrical discs.

5. The crash protection positioning device for high and low voltage inspection UAV according to claim 4 is characterized in that: When the connecting rod (4) and the rack one (63) are extended to the outermost sides, the inner end of the rack one (63) is still located on the inner side of the mounting clamp (62), and the inner end of the rack one (63) extends between the upper and lower symmetrical disks of the threaded disk (68).

6. The crash protection positioning device for high and low voltage inspection UAV according to claim 5 is characterized in that: The teeth on the upper and lower sides of the rack (63) are meshed with the spiral teeth on the adjacent side of the circular disk in the threaded disk (68), so that when the threaded disk (68) rotates, the rack (63) can be driven to move telescopically. The motor (3) is remotely controlled, and a weightlessness sensing component is provided in the control system, that is, when the drone crashes and loses weight, the motor (3) can be triggered to rotate unidirectionally, and the direction of rotation is to drive the threaded disk (68) to make the rack (63) retract inward.

7. The crash protection positioning device for high and low voltage inspection UAV according to claim 2 is characterized in that: The cylindrical tubes (69) are symmetrical in both directions and extend into the interior of the machine body (1) and are connected to the machine body (1) in a limited rotation manner. A protrusion (691) is evenly fixedly mounted on one end of the cylindrical tube (69) away from the limit frame (65). The protrusion (691) is connected to the interior of the machine body (1) in a limited sliding manner, and springs (692) are fixedly connected between the two sides of the protrusion (691) and the inner wall of the machine body (1).

8. The crash protection positioning device for high and low voltage inspection UAV according to claim 2 is characterized in that: The protection component (7) comprises: A slider (71), the interior of the limiting groove (12) is connected to the slider (71) in a limiting sliding manner; A rolling ball (72), the middle portion of the inner side of the sliding block (71) is limitedly rollingly connected with the rolling ball (72); A protection rod (73) is provided between the rolling ball (72) and the second rack (66), one end of the protection rod (73) is hinged to the outer end of the second rack (66), and the other end of the protection rod (73) passes through the rolling ball (72) and extends to the outer side of the machine body (1), and is slidably connected to the rolling ball (72).

9. The crash protection positioning device for high and low voltage inspection UAV according to claim 8 is characterized in that: One end of the outer side of the protection rod (73) is in the shape of a sphere with a larger diameter, and the protection rod (73) is made of elastic material and can buffer impact.

10. The crash protection positioning device for high and low voltage inspection UAV according to any one of claims 1 to 9, characterized in that: The bottom of the machine body (1) is connected to a camera (8) in a limited rotation manner.

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