Unmanned aerial vehicle navigation mark inspection device

Abstract

The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle navigation mark inspection device which comprises undercarriages fixedly installed at the two ends of the bottom of an unmanned aerial vehicle, the bottoms of the undercarriages are symmetrically and fixedly connected with connecting columns, and the bottoms of the two connecting columns are jointly and fixedly connected with a soaking pipe. The two ends of the water immersion pipe are fixedly connected with gas combination pipes, the top of the water immersion pipe is fixedly connected with a water inlet in a through mode, a water immersion sensor is fixedly assembled between the undercarriage and the water immersion pipe, and the detection end of the water immersion sensor is arranged in the water immersion pipe; according to the utility model, the water immersion sensor is used for detecting water filled into the water immersion pipe and transmitting a signal to the high-speed electromagnetic valve to control the double-valve gas cylinder to inflate the gas closing pipe, so that the gas bag is expanded and opened, and the unmanned aerial vehicle falling into the water floats to the water surface, so that the fishing difficulty is reduced, the property loss is avoided, and the delay of the inspection work efficiency is prevented.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a UAV navigation mark inspection device. Background Technology

[0002] A drone-based navigation aid inspection device is an intelligent drone system specifically designed for inspecting navigation aids (such as lighthouses and buoys) at sea or in waterways. In layman's terms, it can be understood as an "intelligent inspection robot for navigation aids in waterways" or an "automatic inspection aircraft." It mainly consists of a drone body, a collision avoidance structure, intelligent control equipment, and inspection equipment. Using high-definition cameras and infrared devices, it quickly identifies whether the navigation aid is damaged, displaced, or has abnormal lighting. No personnel are required to be on-site; the ground control station receives images in real time and analyzes the data.

[0003] The working area of ​​existing drone navigation mark inspection devices is mainly over water. Drones may accidentally fall into the water due to factors such as operational errors, environmental factors, and equipment failures. Although drones have a certain degree of waterproof performance, the drone will sink to the bottom of the water after a period of time. Due to factors such as light, water flow, and water turbidity, direct retrieval is often difficult. Moreover, if the operation is not done properly during the retrieval process, it is easy to cause secondary damage to the drone, which will not only cause property loss, but also delay subsequent inspection work. Utility Model Content

[0004] The purpose of this invention is to provide a drone navigation mark inspection device that uses a water immersion sensor to detect water entering the immersion pipe and sends a signal to a high-speed solenoid valve to control a dual-valve gas cylinder to inflate the gas pipe, causing the airbag to expand and open, thereby allowing the drone that has fallen into the water to float to the surface, reducing the difficulty of salvage, avoiding property damage, and preventing delays in inspection work.

[0005] The specific technical solution adopted by this utility model is as follows:

[0006] A drone navigation mark inspection device includes landing gear fixedly installed at both ends of the bottom of the drone. Symmetrically fixed connecting posts are fixedly connected to the bottom of each landing gear. A water immersion pipe is fixedly connected to the bottom of both connecting posts. A gas-sealing pipe is fixedly connected to both ends of the water immersion pipe. A water inlet is fixedly connected to the top of the water immersion pipe. A water immersion sensor is fixedly assembled between the landing gear and the water immersion pipe. The detection end of the water immersion sensor is located inside the water immersion pipe. A threaded tube is threaded onto the inner wall of the gas-sealing pipe, with one end of the threaded tube extending outwards. Extending to the outside of the gas pipe, a connecting sleeve is fixedly connected to the inner wall of the spiral tube. One end of the connecting sleeve is fixedly connected to an air bladder, and one end of the air bladder is fixedly connected to a cap. When the air bladder is not inflated, a split plate is arranged around its outer periphery. The two ends of the split plate are fixedly connected to the gas pipe and the cap respectively through brittle connecting plates. When the air bladder is inflated, the brittle connecting plate breaks under tensile force, and the split plate is released from its constraint and disperses outward. An air supply device is fixedly assembled on the inner side of the landing gear for supplying gas to the gas pipe.

[0007] The outer walls of the landing gear and the immersion pipe are fixedly connected to support plates, and a screw is rotatably connected between the two support plates.

[0008] The two connecting columns are slidably connected to a sliding frame on their sidewalls. The sliding frame is threadedly connected to the screw. The sidewall of the sliding frame is fixedly connected to a plug cap for movably engaging with the water inlet.

[0009] An auxiliary power supply is fixedly mounted on the bottom of the drone, and the auxiliary power supply is electrically connected to the water immersion sensor via a power supply cable.

[0010] A partition is fixedly connected to one end of the inner tube, and an air nozzle is fixedly installed on the axis of the partition.

[0011] The air supply device includes symmetrically fixed frames connected to the inside of the landing gear, and a double-valve air cylinder is fixedly installed between the two fixed frames. High-speed solenoid valves are fixedly assembled at both ends of the double-valve air cylinder.

[0012] An inflation hose is fixedly connected to the inner axis of the air mixing pipe, and one end of the inflation hose extends outward and is fixedly connected to the high-speed solenoid valve in a through-type manner. The high-speed solenoid valve is electrically connected to the water immersion sensor through a signal line.

[0013] The landing gear and the water immersion pipe are fixedly connected to the inner wall of the protective shell, and the protective shell covers the outside of the dual-valve gas cylinder and the high-speed solenoid valve.

[0014] The technical effect achieved by this utility model is as follows: by detecting the water entering the immersion pipe through the water immersion sensor, the signal is sent to the high-speed solenoid valve to control the dual-valve gas cylinder to inflate the gas pipe, so that the air bag expands and opens, thereby making the drone that has fallen into the water float to the surface, reducing the difficulty of salvage, avoiding property loss, and preventing delays in the efficiency of inspection work. Attached Figure Description

[0015] Figure 1 This is an overall view of the drone navigation mark inspection device provided in the embodiments of this utility model;

[0016] Figure 2 yes Figure 1 A magnified view of a section at point A in the middle;

[0017] Figure 3 This is a structural diagram showing the removal of the drone and the protective shell after it is covered, according to an embodiment of this utility model.

[0018] Figure 4 yes Figure 3 A magnified view of a section at point B in the middle;

[0019] Figure 5 This is a sectional view of the immersion pipe and gas mixing pipe provided in the embodiment of this utility model;

[0020] Figure 6 yes Figure 5 A magnified view of a section at point C;

[0021] Figure 7 This is a structural assembly diagram of the split plate provided in an embodiment of this utility model.

[0022] The attached diagram lists the components represented by each number as follows:

[0023] 1. Unmanned Aerial Vehicle (UAV); 101. Landing Gear; 102. Connecting Column; 103. Immersion Pipe; 104. Water Inlet; 105. Support Plate; 106. Screw; 107. Sliding Frame; 108. Plug Cap; 109. Water Immersion Sensor; 110. Auxiliary Power Supply; 111. Power Supply Cable; 2. Combination Pipe; 201. Screw Pipe; 202. Connecting Sleeve; 203. Airbag; 204. Partition Plate; 205. Air Nozzle; 206. Inflation Hose; 207. End Cap; 208. Split Plate; 209. Brittle Connecting Plate; 3. Dual-Valve Air Cylinder; 301. Fixing Frame; 302. High-Speed ​​Solenoid Valve; 303. Signal Cable; 304. Protective Shell. Detailed Implementation

[0024] To make the objectives and advantages of this utility model clearer, the following detailed description is provided in conjunction with embodiments. It should be understood that the following text is merely used to describe one or more specific embodiments of this utility model and does not strictly limit the scope of protection specifically claimed by this utility model.

[0025] like Figures 1-3 As shown, a drone navigation mark inspection device includes landing gear 101 fixedly installed at both ends of the bottom of a drone 1. Connecting columns 102 are symmetrically fixedly connected to the bottom of the landing gear 101. A water immersion pipe 103 is fixedly connected to the bottom of both connecting columns 102. Gas pipes 2 are fixedly connected to both ends of the water immersion pipe 103. A water inlet 104 is fixedly connected to the top of the water immersion pipe 103. Support plates 105 are fixedly connected to the outer walls of both the landing gear 101 and the water immersion pipe 103. A screw 106 is rotatably connected between the two support plates 105. The two connecting columns 102 are slidably connected to the side walls of a sliding frame 107. The sliding frame 107 is threadedly connected to the screw 106. The side wall of the sliding frame 107 is fixedly connected to a plug cap 108 for movably engaging with the water inlet 104. A water immersion sensor 109 is fixedly assembled between the landing gear 101 and the immersion pipe 103. The detection end of the water immersion sensor 109 is located inside the immersion pipe 103. An auxiliary power supply 110 is fixedly assembled at the bottom of the UAV 1. The auxiliary power supply 110 is electrically connected to the water immersion sensor 109 through a power supply line 111.

[0026] According to the above structure, the cap 108 covers the top of the water inlet 104 when the drone 1 is not working, preventing dust and moisture from entering the immersion pipe 103. Before the drone 1 takes off, the sliding frame 107 is limited in rotation angle by the sliding connection between the sliding frame 107 and the connecting column 102. When the screw 106 is rotated, the sliding frame 107 rises linearly along the axis of the screw 106, thereby causing the cap 108 to detach from the water inlet 104. This ensures that after the drone 1 falls into the water, water can enter the immersion pipe 103 through the water inlet 104. The detection end of the water immersion sensor 109 conducts electricity after touching water, and transmits the electrical signal to the coil of the high-speed solenoid valve 302. When the drone 1 is charging normally, part of the power is allocated to the auxiliary power supply 110 as an emergency power supply to ensure that the auxiliary power supply 110 can still provide power to the water immersion sensor 109 after the drone 1 is short-circuited and disconnected.

[0027] See attached document Figures 3-7The inner wall of the venting pipe 2 is threaded with a spiral tube 201. One end of the spiral tube 201 extends outward to the outside of the venting pipe 2. A connecting sleeve 202 is fixedly connected to the inner wall of the spiral tube 201. An air bladder 203 is fixedly connected to one end of the connecting sleeve 202. A partition 204 is fixedly connected to one end of the spiral tube 201. An air nozzle 205 is fixedly installed in the middle of the partition 204. A cap 207 is fixedly connected to one end of the air bladder 203. When the air bladder 203 is not inflated, a split plate 208 is circumferentially arranged around its outer side. Both ends of the split plate 208 are fixedly connected to the venting pipe 2 and the cap 207 respectively through brittle connecting plates 209. When the air bladder 203 is inflated, the brittle connecting plate 209 breaks under tensile force, and the split plate 208 is released from its constraint and disperses outward. An air supply device is fixedly assembled on the inner side of the landing gear 101 for supplying gas to the gas pipe 2. The air supply device includes a fixed frame 301 symmetrically fixedly connected to the inner side of the landing gear 101. A dual-valve gas cylinder 3 is fixedly installed between the two fixed frames 301. A high-speed solenoid valve 302 is fixedly assembled at both ends of the dual-valve gas cylinder 3. An inflation hose 206 is fixedly connected to the inner axis of the gas pipe 2. One end of the inflation hose 206 extends outward and is fixedly connected to the high-speed solenoid valve 302 in a through manner. The high-speed solenoid valve 302 is electrically connected to the water immersion sensor 109 through a signal line 303. A protective shell 304 is fixedly connected to the inner wall of the landing gear 101 and the water immersion pipe 103. The protective shell 304 covers the outer side of the dual-valve gas cylinder 3 and the high-speed solenoid valve 302.

[0028] According to the above structure, the coil inside the high-speed solenoid valve 302 receives the electrical signal from the water immersion sensor 109 and is energized, generating a magnetic force. Its internal iron core is attracted by the magnetic force, opening the valve passage. The gas inside the dual-valve gas cylinder 3 rushes into the gas-combining pipe 2 instantly through the inflation hose 206. When the connecting sleeve 202 and the air bag 203 are not inflated, they are retracted inside the split plate 208 and the spiral tube 201. Several split plates 208 are arranged in a closed ring. The split plates 208 are fixed to one end of the gas-combining pipe 2 by the brittle connecting plate 209. The end cap 207 is also fixed to one end of the split plate 208 by the brittle connecting plate 209. At this time, the air nozzle 205 is connected to one end of the inflation hose 206. The gas from the dual-valve gas cylinder 3 flows through the inflation hose 206 and the gas-combining pipe 201. When the nozzle 205 enters the connecting sleeve 202, the airbag 203 expands outward, the split plate 208 is squeezed by tension, the brittle connecting plate 209 breaks, the split plate 208 scatters outward, and the airbag 203 also opens outward. Each water immersion pipe 103 has an airbag 203 at both ends, and each double-valve gas cylinder 3 provides gas to two airbags 203 respectively. A total of four airbags 203 are inflated, thereby increasing the buoyancy of the UAV 1 and making it float to the water surface. The protective shell 304 covers the outside of the double-valve gas cylinder 3, the high-speed solenoid valve 302, the inflation hose 206 and other components for waterproofing. After the airbag 203 opens, it can also be removed from the inside of the air pipe 2 by rotating one end of the screw tube 2 for replacement.

[0029] This invention uses a water immersion sensor 109 to detect the water entering the immersion pipe 103 and sends a signal to a high-speed solenoid valve 302 to control the dual-valve gas cylinder 3 to inflate the gas pipe 2, causing the airbag 203 to expand and open, thereby allowing the drone 1 that has fallen into the water to float to the surface, reducing the difficulty of salvage, avoiding property damage, and preventing delays in the efficiency of inspection work.

[0030] The working principle of this utility model is as follows: When the drone 1 is not in operation, the cap 108 covers the top of the water inlet 104 to prevent dust and moisture from entering the immersion pipe 103. Before the drone 1 takes off, the sliding frame 107 is limited in rotation angle by the sliding connection between the sliding frame 107 and the connecting column 102. When the screw 106 is rotated, the sliding frame 107 rises linearly along the axis of the screw 106, thereby causing the cap 108 to detach from the water inlet 104. This ensures that after the drone 1 falls into the water, water can enter the immersion pipe 103 through the water inlet 104. (Water immersion sensor...) When the detection end of the device 109 comes into contact with water, it becomes conductive and transmits an electrical signal to the coil of the high-speed solenoid valve 302. During normal charging of the drone 1, a portion of the power is allocated to the auxiliary power supply 110 as an emergency power source to ensure that the auxiliary power supply 110 can still provide power to the water immersion sensor 109 after a short circuit. The coil inside the high-speed solenoid valve 302 receives the electrical signal from the water immersion sensor 109 and is energized, generating a magnetic force. Its internal iron core is attracted by the magnetic force, opening the valve passage. The gas inside the dual-valve gas cylinder 3 rushes into the gas mixing pipe 2 instantly through the inflation hose 206. When the connecting sleeve 202 and airbag 203 are not inflated, they are retracted inside the split plate 208 and the spiral tube 201. Several split plates 208 are arranged in a closed loop. The split plates 208 are fixed to one end of the gas pipe 2 by the brittle connecting plate 209. The end cap 207 is also fixed to one end of the split plate 208 by the brittle connecting plate 209. At this time, the air nozzle 205 is connected to one end of the inflation hose 206. The gas from the double-valve gas cylinder 3 enters the connecting sleeve 202 through the inflation hose 206 and the air nozzle 205. The airbag 203 expands outward, and the split plates 208 are compressed by tension. The brittle connecting plate 209... When the tube breaks, the split plate 208 scatters outwards, and the airbags 203 also open outwards. Each water-immersing tube 103 has an airbag 203 at both ends. Each dual-valve air cylinder 3 provides gas to two airbags 203 respectively. A total of four airbags 203 are inflated, thereby increasing the buoyancy of the drone 1 and making it float to the water surface. The protective shell 304 covers the outside of components such as the dual-valve air cylinder 3, the high-speed solenoid valve 302, and the inflation hose 206 to waterproof them. After the airbags 203 open, they can also be removed from the inside of the air-combining tube 2 by rotating one end of the screw tube 2 for replacement.

[0031] The above description is merely a preferred embodiment of this utility model. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principle of this utility model, and these improvements and modifications should also be considered within the scope of protection of this utility model. Structures, devices, and operating methods not specifically described or explained in this utility model, unless otherwise specified or limited, shall be implemented using conventional methods in the field.

Claims

1. An unmanned aerial vehicle beacon inspection device, comprising landing gears (101) fixedly installed at both ends of the bottom of an unmanned aerial vehicle (1), characterized in that: The bottom of the landing gear (101) is symmetrically fixedly connected with connecting columns (102), the bottoms of the two connecting columns (102) are fixedly connected with a water immersion pipe (103) in common, both ends of the water immersion pipe (103) are fixedly connected with a gas pipe (2), the top of the water immersion pipe (103) is fixedly connected with a water inlet (104) in a through manner, a water immersion sensor (109) is fixedly assembled between the landing gear (101) and the water immersion pipe (103), the detection end of the water immersion sensor (109) is arranged in the water immersion pipe (103), the inner wall of the gas pipe (2) is threadedly connected with a spiral pipe (201), one end of the spiral pipe (201) extends outward to the outside of the gas pipe (2), the inner wall of the spiral pipe (201) is fixedly connected with a connecting sleeve (202), one end of the connecting sleeve (202) is fixedly connected with an air bag (203), one end of the air bag (203) is fixedly connected with an end cover (207), in the state that the air bag (203) is not inflated, a split plate (208) is arranged on the outer side of the air bag (203) in a circumferential direction, the split plate (208) is fixedly connected with the gas pipe (2) and the end cover (207) through brittle connecting plates (209) at both ends, when the air bag (203) is inflated, the brittle connecting plates (209) are broken under the action of tension, the split plate (208) is separated from the constraint and disperses outward, the inner side of the landing gear (101) is fixedly assembled with a gas supply device for supplying gas to the gas pipe (2).

2. The unmanned aerial vehicle navigation beacon inspection device according to claim 1, characterized in that: The outer side walls of the landing gear (101) and the water immersion pipe (103) are fixedly connected with supporting plates (105), the two supporting plates (105) are rotatably connected with a screw rod (106). 3.The device according to claim 2, characterized in that: The side walls of the two connecting columns (102) are fixedly connected with a sliding frame (107) in common, the sliding frame (107) is threadedly connected with the screw rod (106), the side wall of the sliding frame (107) is fixedly connected with a plug cap (108) for movably embedding the water inlet (104).

4. The unmanned aerial vehicle navigation beacon inspection device of claim 1, wherein: The bottom of the unmanned aerial vehicle (1) is fixedly assembled with an additional power supply (110), the additional power supply (110) is electrically connected with the water immersion sensor (109) through a power supply line (111).

5. The unmanned aerial vehicle navigation beacon inspection device of claim 1, wherein: One end of the inside of the spiral pipe (201) is fixedly connected with a partition plate (204), the axis of the partition plate (204) is fixedly installed with an air nozzle (205).

6. The unmanned aerial vehicle navigation beacon inspection device of claim 1, wherein: The gas supply device comprises fixed frames (301) fixedly connected to the inner side of the landing gear (101) in a symmetric manner, a double-gate gas cylinder (3) is fixedly installed between the two fixed frames (301), both ends of the double-gate gas cylinder (3) are fixedly assembled with high-speed electromagnetic valves (302).

7. The unmanned aerial vehicle navigation beacon inspection device of claim 6, wherein: The inside of the gas pipe (2) is fixedly connected with an inflation hose (206) at the axis, one end of the inflation hose (206) extends outward and is fixedly connected with the high-speed electromagnetic valve (302) in a through manner, the high-speed electromagnetic valve (302) is electrically connected with the water immersion sensor (109) through a signal line (303).

8. The unmanned aerial vehicle navigation beacon inspection device of claim 6, wherein: The inner side wall of the landing gear (101) and the immersion pipe (103) is fixedly connected with a protective shell (304), and the protective shell (304) covers the outer side of the double-valve gas cylinder (3) and the high-speed electromagnetic valve (302).

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