Power inspection drone parachute protection device

Abstract

A parachute protection device for an electric power inspection UAV belongs to the technical field of UAV accessories. The purpose of the present invention is to add a landing protection device to a UAV, so as to provide an electric power inspection UAV parachute protection device that can effectively protect the UAV during its descent. The servo of the present invention is installed above the UAV body, and a parachute compartment is fixedly installed on the UAV body. A partition plate is fixedly installed in the parachute compartment, and two telescopic springs are symmetrically fixedly installed on the top of the partition plate. The same parachute is fixedly installed on the top of the two telescopic springs, and two rotating holes are symmetrically opened on both sides of the parachute compartment. The same rotating shaft is fixedly installed on the inner walls on both sides of the rotating holes, and a connecting block is rotatably sleeved on the rotating shaft. The two connecting blocks are fixedly installed with the same compartment cover, and the compartment cover is in contact with the parachute. The present invention effectively prevents the UAV from hitting the ground. And the function of improving the installation stability of the parachute compartment is achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicle matching. Background Art

[0002] In recent years, with the development of industry-level drone technology, overhead power transmission line inspection is changing from manual inspection to collaborative inspection mode dominated by drone inspection. Power inspection drones have extensive and irreplaceable applications in transmission line channel hidden danger inspection, line autonomous inspection, disaster accident special inspection, drone laser point cloud modeling, etc. Most inspection drones are equipped with expensive equipment such as camera gimbals, infrared temperature measurement equipment, and laser radar equipment to assist in inspection operations. In the existing technology, most of the current line inspection drones are not equipped with out-of-control fall protection devices. After the drone loses control, the power of the drone motor cannot be cut off. The uncontrolled falling drone seriously threatens the safety of the line. At the same time, once the drone loses control, it will fall with the equipment on it, causing the equipment to break and causing great economic losses. Therefore, a parachute protection device for power inspection drones is needed to meet people's needs. Summary of the invention

[0003] The purpose of the present invention is to add a landing protection device to a UAV, so as to provide a parachute protection device for an electric power inspection UAV which can effectively protect the UAV during its descent.

[0004] The present invention comprises a drone body and a steering gear, wherein the steering gear is installed above the drone body, a parachute compartment is fixedly installed on the drone body, a partition plate is fixedly installed in the parachute compartment, two telescopic springs are symmetrically fixedly installed on the top of the partition plate, a same parachute is fixedly installed on the top of the two telescopic springs, two rotating holes are symmetrically arranged on both sides of the parachute compartment, a same rotating shaft is fixedly installed on the inner walls on both sides of the rotating holes, a connecting block is rotatably sleeved on the rotating shaft, a same compartment cover is fixedly installed on the two connecting blocks, the compartment cover is in contact with the parachute, the steering gear is fixedly installed on one side of the parachute compartment, a pressing block is slidably sleeved in the parachute compartment, four fixing blocks are symmetrically fixedly installed on the pressing block, a fixing rod is rotatably installed on the fixing block, the four fixing rods are all in contact with the drone body, and two sides of the parachute compartment are provided with a plurality of fixed holes. Two rotating grooves are symmetrically provided, and a limit block is rotatably installed in the rotating groove; a telescopic shaft is fixedly installed on the pressing block, a telescopic tube is slidably sleeved on the telescopic shaft, and the telescopic tube is fixedly installed on the bottom of the partition plate; the same return spring is slidably sleeved on the telescopic tube and the telescopic shaft, one end of the return spring is in contact with the partition plate, and the other end of the return spring is in contact with the pressing block; a buffer groove is provided on one side of the fixed rod, a positioning shaft is slidably installed in the buffer groove, and the positioning shaft is fixedly installed on the inner wall of the slot; two limit grooves are symmetrically provided on the fixed block, and the limit block is rotatably installed in the limit groove; the same limit shaft is fixedly installed on the inner walls on both sides of the limit groove, the limit block is rotatably sleeved on the limit shaft, a torsion spring is fixedly sleeved on the limit shaft, one end of the torsion spring is connected to the limit block, and the other end of the torsion spring is connected to the limit shaft.

[0005] The parachute compartment of the present invention is symmetrically provided with four slots on both sides, and four fixing rods are rotatably installed in the four slots respectively.

[0006] The present invention effectively prevents the UAV from colliding with the ground and causing losses to personnel and property during power transmission line inspection operations, and can drive the fixing rod to fix the UAV, thereby achieving the function of improving the installation stability of the parachute compartment. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1 It is a structural schematic diagram of the parachute protection device for the power inspection UAV proposed by the present invention;

[0008] Figure 2 It is a schematic diagram of the side cross-sectional structure of the connection block in the parachute protection device of the power inspection UAV proposed by the present invention;

[0009] Figure 3 It is a schematic diagram of the side cross-sectional structure of the pressing block in the parachute protection device for the power inspection UAV proposed by the present invention;

[0010] Figure 4 It is a structural schematic diagram of a pressing block in a parachute protection device for an electric power inspection UAV proposed by the present invention;

[0011] Figure 5 It is a structural schematic diagram of the parachute compartment in the parachute protection device for the power inspection UAV proposed by the present invention;

[0012] Figure 6 It is a schematic diagram of the side cross-sectional structure of the parachute compartment in the parachute protection device for the power inspection UAV proposed by the present invention;

[0013] In the figure: 1. UAV body; 2. parachute compartment; 3. partition plate; 4. telescopic spring; 5. parachute; 6. rotating hole; 7. rotating shaft; 8. connecting block; 9. compartment cover; 10. pressing block; 11. fixing block; 12. fixing rod; 13. buffer groove; 14. positioning shaft; 15. card slot; 16. limit groove; 17. rotating slot; 18. limit shaft; 19. torsion spring; 20. limit block; 21. telescopic shaft; 22. telescopic tube; 23. reset spring; 24. servo. DETAILED DESCRIPTION

[0014] The present invention comprises a drone body 1 and a steering gear 24, wherein the steering gear 24 is installed above the drone body 1, a parachute compartment 2 is fixedly installed on the drone body 1, a partition plate 3 is fixedly installed in the parachute compartment 2, two telescopic springs 4 are symmetrically fixedly installed on the top of the partition plate 3, a same parachute 5 is fixedly installed on the top of the two telescopic springs 4, two rotating holes 6 are symmetrically opened on both sides of the parachute compartment 2, a same rotating shaft 7 is fixedly installed on the inner walls of both sides of the rotating holes 6, a connecting block 8 is rotatably sleeved on the rotating shaft 7, two connecting blocks 8 are fixedly installed with a same compartment cover 9, the compartment cover 9 is in contact with the parachute 5, and the steering gear 24 is fixedly installed on the parachute compartment 2. It is fixedly installed on one side of the parachute compartment 2, and a pressing block 10 is slidably sleeved in the parachute compartment 2. Four fixing blocks 11 are symmetrically fixedly installed on the pressing block 10, and a fixing rod 12 is rotatably installed on the fixing block 11. The four fixing rods 12 are all in contact with the UAV body 1. Two rotating grooves 17 are symmetrically provided on both sides of the parachute compartment 2, and a limit block 20 is rotatably installed in the rotating groove 17. When the UAV body 1 loses control and falls during flight, the steering gear 24 starts to rotate, and the telescopic spring 4 pushes the parachute 5 to pop out of the parachute compartment 2, completing the deployment of the parachute 5, reducing the falling speed of the UAV body 1, and thereby reducing the impact it receives.

[0015] The pressing block 10 of the present invention is fixedly mounted with a telescopic shaft 21 , on which a telescopic tube 22 is slidably sleeved, and the telescopic tube 22 is fixedly mounted at the bottom of the partition plate 3 . The telescopic tube 22 and the telescopic shaft 21 are used to improve the sliding stability of the pressing block 10 .

[0016] The telescopic tube 22 and the telescopic shaft 21 of the present invention are slidably sleeved with a same return spring 23, one end of the return spring 23 contacts the partition plate 3, and the other end of the return spring 23 contacts the pressing block 10. The return spring 23 drives the telescopic tube 22 and the telescopic shaft 21 to push the pressing block 10 to pop outward.

[0017] Four slots 15 are symmetrically provided on both sides of the parachute compartment 2 of the present invention. Four fixing rods 12 are rotatably installed in the four slots 15 , respectively. The slots 15 are used to control the sliding range of the fixing rods 12 .

[0018] A buffer groove 13 is provided on one side of the fixing rod 12 of the present invention. A positioning shaft 14 is slidably installed in the buffer groove 13. The positioning shaft 14 is fixedly installed on the inner wall of the slot 15. The buffer groove 13 and the positioning shaft 14 interact with each other, so that the fixing rod 12 slides more smoothly.

[0019] The fixing block 11 of the present invention is symmetrically provided with two limiting grooves 16 , and the limiting block 20 is rotatably installed in the limiting groove 16 , so that the pressing block 10 is prevented from automatically sliding out of the parachute compartment 2 by the limiting block 20 .

[0020] The same limiting shaft 18 is fixedly installed on the inner walls of both sides of the limiting groove 16 of the present invention, and the limiting block 20 is rotatably sleeved on the limiting shaft 18. A torsion spring 19 is fixedly sleeved on the limiting shaft 18. One end of the torsion spring 19 is connected to the limiting block 20, and the other end of the torsion spring 19 is connected to the limiting shaft 18. The torsion spring 19 and the limiting shaft 18 work together to prevent the limiting block 20 from being unable to buckle into the limiting groove 16.

[0021] When the parachute chamber 2 is used, the present invention directly presses the parachute chamber 2 on the drone body 1, and the drone body 1 squeezes the pressing block 10, driving the pressing block 10 to slide into the parachute chamber 2, thereby driving the fixing rod 12 to rotate around the positioning shaft 14, so that the fixing rod 12 is fixedly buckled on the drone body 1, thereby ensuring the installation stability of the parachute chamber 2. When the drone body 1 loses control and falls during flight, the steering gear 24 starts to rotate, and the telescopic spring 4 pushes the parachute 5 to pop out of the parachute chamber 2, completing the deployment of the parachute 5, reducing the falling speed of the drone body 1, thereby reducing the impact it receives, and protecting the drone body 1. When the pressing block 10 slides upward, the limit The engagement of the groove 16 with the limit block 20 prevents the pressing block 10 from directly pushing open the drone body 1 under the action of the return spring 23. When the parachute compartment 2 needs to be disassembled, it is only necessary to pull the limit block 20 to make it disengage from the limit groove 16. Under the action of the return spring 23, the telescopic tube 22 and the telescopic shaft 21 push the pressing block 10 to pop out, drive the fixing rod 12 to expand outward, release the drone body 1, and complete the disassembly of the parachute compartment 2. Among them, the torsion spring 19 and the limit shaft 18 work together to prevent the limit block 20 from being unable to buckle into the limit groove 16. The buffer groove 13 and the positioning shaft 14 interact with each other, making the sliding of the fixing rod 12 smoother and also improving the stability of the fixing rod 12.

[0022] The present invention has a parachute compartment fixedly mounted on the drone body, and a parachute is arranged in the parachute compartment, so that the parachute can be deployed when the drone falls out of control, and the drone can land smoothly through the parachute, thereby protecting the drone body, and also protecting the expensive equipment carried on the drone body, and effectively preventing the drone from colliding with the ground and causing losses to personnel and property during the power transmission line inspection operation.

[0023] The present invention utilizes the linkage between the pressing block and the fixing rod to reduce the difficulty of disassembling and assembling the parachute bin, so that when installing the parachute bin, the user only needs to press the parachute bin directly on the drone, and the drone is squeezed by the pressing block to drive the fixing rod to fix the drone, thereby achieving the function of improving the installation stability of the parachute bin.

Claims

1. A parachute protection device for an electric power inspection drone, comprising a drone body (1) and a steering gear (24), wherein the steering gear (24) is mounted above the drone body (1), and is characterized in that: A parachute compartment (2) is fixedly mounted on a drone body (1), a partition plate (3) is fixedly mounted inside the parachute compartment (2), two telescopic springs (4) are symmetrically fixedly mounted on the top of the partition plate (3), a same parachute (5) is fixedly mounted on the top of the two telescopic springs (4), two rotating holes (6) are symmetrically provided on both sides of the parachute compartment (2), a same rotating shaft (7) is fixedly mounted on the inner walls of both sides of the rotating holes (6), a connecting block (8) is rotatably sleeved on the rotating shaft (7), a same compartment cover (9) is fixedly mounted on the two connecting blocks (8), and the compartment cover (9) is connected to the parachute compartment (2) and the parachute compartment (2) is connected to the parachute compartment (2). The parachute compartment (2) is in contact with a parachute (5), a steering gear (24) is fixedly mounted on one side of the parachute compartment (2), a pressing block (10) is slidably sleeved in the parachute compartment (2), four fixing blocks (11) are symmetrically fixedly mounted on the pressing block (10), a fixing rod (12) is rotatably mounted on the fixing block (11), and the four fixing rods (12) are all in contact with the drone body (1), two rotating grooves (17) are symmetrically provided on both sides of the parachute compartment (2), and a limit block (20) is rotatably mounted in the rotating groove (17); a telescopic shaft (21) is fixedly mounted on the pressing block (10), and the telescopic shaft (21 ) is slidably sleeved with a telescopic tube (22), which is fixedly mounted on the bottom of the partition plate (3); a same return spring (23) is slidably sleeved on the telescopic tube (22) and the telescopic shaft (21), one end of the return spring (23) is in contact with the partition plate (3), and the other end of the return spring (23) is in contact with the pressing block (10); a buffer groove (13) is provided on one side of the fixing rod (12), a positioning shaft (14) is slidably mounted in the buffer groove (13), and the positioning shaft (14) is fixedly mounted on the inner wall of the card groove (15); symmetrically provided on the parachute compartment (2) are Two limit grooves (16), and a limit block (20) is rotatably mounted in the limit groove (16); a same limit shaft (18) is fixedly mounted on the inner walls of both sides of the limit groove (16), the limit block (20) is rotatably sleeved on the limit shaft (18), a torsion spring (19) is fixedly sleeved on the limit shaft (18), one end of the torsion spring (19) is connected to the limit block (20), and the other end of the torsion spring (19) is connected to the limit shaft (18); four clamping grooves (15) are symmetrically opened on both sides of the parachute compartment (2), and four fixing rods (12) are rotatably mounted in the four clamping grooves (15) respectively.

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