Power endurance improving device and improving method thereof

Abstract

The application discloses a kind of power endurance promotion equipment and its promotion method, the power endurance promotion equipment includes aircraft one and aircraft two, communication base station is installed on aircraft one, aircraft one drives communication base station to fly to high altitude and provides communication connection signal for the specified area, aircraft two is installed with supply device, and aircraft two is used to supply power for the communication base station in the air, communication base station is installed with vertically arranged charging pipe, charging end is installed on supply device, and connecting mechanism is arranged between charging pipe and charging end.The application provides power supply for the communication base station in the air by supply aircraft, solves the problem that the existing communication base station in the air needs to return ground station to obtain supply, avoids communication interruption when the communication base station in the air is supplied, greatly increases the effective air retention time of the communication base station in the air, and then improves work efficiency and intelligent degree, and expands the working range of the communication base station in the air.

Description

Technical Field

[0001] This invention relates to the field of communication technology, and more specifically, to a power endurance enhancement device and method thereof. Background Technology

[0002] 5G base stations are the core equipment of 5G networks, providing wireless coverage and enabling wireless signal transmission between wired communication networks and wireless terminals. The architecture and form of base stations directly affect how 5G networks are deployed. Because higher frequencies result in greater signal attenuation during propagation, 5G networks require higher base station density. However, in some special environments, such as at sea, in forests, or where communication is disrupted due to natural disasters, it is impossible to quickly establish ground base stations. Therefore, aerial communication base stations using drones have emerged.

[0003] However, when drones perform long-distance missions, their limited battery life and payload capacity necessitate periodic battery replacements or recharging. Currently, battery replacements or recharging for drones typically require manual intervention on the ground, necessitating a return trip. However, the time and energy consumed by drones traveling between the air and ground significantly reduces the effective communication time provided by drone-based communication base stations, which is detrimental to rescue efforts in emergency situations such as disaster relief. Summary of the Invention

[0004] This invention provides a name for solving the technical problem in related technologies where airborne communication base stations are not convenient for replenishing power in the air.

[0005] The present invention provides the following technical solution: a power endurance enhancement device and its enhancement method, comprising an aircraft 1 and an aircraft 2. The aircraft 1 is equipped with a communication base station, which drives the communication base station to a high altitude and provides a communication connection signal for the designated area. The aircraft 2 is equipped with a refueling device, which is used to refuel the communication base station in the air. The communication base station is equipped with a vertically arranged charging tube, and the refueling device is equipped with a charging end adapted to the charging tube. A connection mechanism is provided between the charging tube and the charging end.

[0006] The connecting mechanism includes a centering tube, which is embedded in the supply device. The charging end is movably disposed in the centering tube, and the centering tube and the charging end are coaxially arranged. The top of the centering tube is provided with a horn. When the charging tube and the charging end are engaged, the horn brings the charging tube together, so that the charging tube and the charging end are coaxially engaged and plugged in.

[0007] In a preferred embodiment, the top of the supply device is provided with a centering mechanism, which includes a fixed frame coaxially arranged with the centering tube. Multiple sliders arranged in a circular array are mounted on the fixed frame, and the multiple sliders are all slidably arranged along the diameter of the fixed frame. A connecting frame is installed on one side of the sliders, and a positioning plate is installed at the end of the connecting frame away from the slide rail.

[0008] In a preferred embodiment, a coaxially arranged ring is placed on the top of the fixing frame, a connecting rod is hinged to the outside of the ring, the end of the connecting rod away from the ring is hinged to the slider, and multiple arrayed slide rails are installed on the fixing frame, with the slider slidingly disposed within the slide rails.

[0009] In a preferred embodiment, the ring sleeve is fitted over the centering tube, the outer side of the centering tube has an arc-shaped groove, and the inner side of the ring sleeve has a protrusion that is movably disposed within the arc-shaped groove.

[0010] In a preferred embodiment, a spring is fitted on the outside of the centering tube, with the two ends of the spring making contact with the flared part and the ring respectively.

[0011] In a preferred embodiment, the centering tube is provided with an elastic support mechanism, which includes a piston and an end plate. The piston contacts the inner wall of the centering tube, the charging terminal is installed on the top of the piston, the end plate is fixedly connected to the centering tube, and a spring telescopic rod is installed between the piston and the end plate. The top of the spring telescopic rod contacts the bottom of the piston, and the bottom of the spring telescopic rod is fixedly connected to the end plate.

[0012] In a preferred embodiment, the centering tube is a cylindrical structure with an open top and a closed bottom. A high-pressure zone is formed between the bottom of the inner cavity of the centering tube and the bottom of the end plate. An exhaust pipe is fixedly installed on the outer side of the bottom of the centering tube. The exhaust pipe is connected to the high-pressure zone, and the jet direction of the exhaust pipe is tangent to the outer periphery of the centering tube. Both ends of the connecting rod are hinged to the ring and the slider through ball joints or universal joints. A valve is installed inside the exhaust pipe. When the internal air pressure of the high-pressure zone is greater than the valve threshold, the valve is always open, and the gas in the high-pressure zone is ejected from the exhaust pipe.

[0013] In a preferred embodiment, a high-pressure gas cylinder is installed inside the centering tube. The high-pressure gas cylinder is located in the high-pressure zone. When the charging tube extends to its limit position and abuts against the charging terminal, the high-pressure gas cylinder opens, and the gas in the high-pressure zone is ejected from the exhaust pipe, driving the centering tube to rotate around its axis, and the ring moves upward along the axis of the centering tube.

[0014] In a preferred embodiment, the inner wall of the centering tube is provided with an air intake channel, the bottom end of which is always located below the piston. The air intake channel is equipped with a one-way valve to limit the leakage of gas in the high-pressure zone through the air intake channel. The top of the end plate is provided with a through hole, and the bottom end of the centering tube is equipped with a limiting sleeve. The limiting sleeve is equipped with an elastic bladder inside, which is connected to the high-pressure zone. When the second aircraft ascends, the piston moves to below the top of the air intake channel, and air enters the high-pressure zone through the air intake channel. When the second aircraft hovers in the air, the piston moves to above the top of the air intake channel.

[0015] In a preferred embodiment, a limiting wheel is movably mounted on the inner side of the positioning plate, and the limiting wheel restricts the charging tube from rotating along its axis.

[0016] A method for improving the battery life of an electric vehicle includes the following steps:

[0017] Step 1: The aircraft flies to a high altitude within the designated area and establishes a communication network in the designated area. The ground power detection device monitors the battery power of the aircraft in real time.

[0018] Step 2: The second aircraft, carrying the resupply equipment, ascends to the power resupply location;

[0019] Step 3: The telescopic mechanism controls the charging tube to extend and connect with the charging terminal inside the centering tube, establishing an electrical connection between the communication base station and the resupply device, and supplying power to the aircraft.

[0020] The beneficial effects of this invention are as follows:

[0021] 1. This invention provides power replenishment to airborne communication base stations by a resupply aircraft, which solves the problem that existing airborne communication base stations need to return to the ground station to obtain supplies. It avoids communication interruption during resupply of airborne communication base stations, greatly increases the effective airborne loiter time of airborne communication base stations, thereby improving work efficiency and intelligence, and expanding the working range of airborne communication base stations.

[0022] 2. In this invention, after the charging tube and the charging end are locked together by interlocking, the centering tube rotates horizontally, driving the centering mechanism to move centripetally. After the centering mechanism finishes guiding the charging tube, it can still clamp the middle section of the charging tube wall again during the replenishment process, reducing the large swing of the charging tube in the air during the charging process and affecting the charging effect. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the communication device of the present invention during resupply.

[0024] Figure 2 This is a schematic diagram of the initial state of the supply device of the present invention.

[0025] Figure 3 This is a schematic diagram of the state during refueling using the refueling device of the present invention.

[0026] Figure 4 This is a schematic diagram of the centering mechanism of the present invention.

[0027] Figure 5 This is a top view of the centering mechanism of the present invention.

[0028] Figure 6 This is a top view of the centering mechanism of the present invention when it is clamped.

[0029] Figure 7 This is a top view schematic diagram of the centering pipe and exhaust pipe of the present invention.

[0030] Figure 8 This is a top view schematic diagram of the centering tube and multiple exhaust pipes of the present invention.

[0031] Figure 9 This is a schematic diagram of the state of the connecting mechanism when it rises in Embodiment 4 of the present invention.

[0032] Figure 10 This is a schematic diagram of the state of the connecting mechanism when it is hovering in the air in Embodiment 4 of the present invention.

[0033] In the diagram: 1. Aircraft 1; 11. Communication base station; 12. Charging tube; 2. Aircraft 2; 21. Resupply device; 3. Centering mechanism; 31. Fixing frame; 32. Slide rail; 33. Ring sleeve; 331. Protrusion; 34. Slider; 35. Connecting rod; 36. Connecting frame; 37. Positioning plate; 371. Limiting wheel; 4. Connecting mechanism; 41. Centering tube; 411. Horn part; 412. Arc groove; 42. Charging end; 43. Spring; 44. Elastic support mechanism; 441. Piston; 442. Spring telescopic rod; 443. End plate; 45. Exhaust pipe; 46. Air intake channel; 5. Elastic bladder; 6. Limiting sleeve. Detailed Implementation

[0034] The subject matter described herein will now be discussed with reference to exemplary embodiments. It should be understood that these embodiments are discussed only to enable those skilled in the art to better understand and implement the subject matter described herein, and changes may be made to the function and arrangement of the elements discussed without departing from the scope of this specification. Various processes or components may be omitted, substituted, or added as needed in the examples. Furthermore, features described in some examples may be combined in other examples.

[0035] Example 1

[0036] Refer to the instruction manual appendix Figures 1-6A power endurance enhancement device and its enhancement method include an aircraft 1 and an aircraft 2. The aircraft 1 is equipped with a communication base station 11. The aircraft 1 drives the communication base station 11 to a high altitude and provides a communication connection signal for the designated area. The aircraft 2 is equipped with a refueling device 21. The aircraft 2 is used to refuel the communication base station 11 in the air. The communication base station 11 is equipped with a vertically arranged charging tube 12. The refueling device 21 is equipped with a charging end 42 adapted to the charging tube 12. A connecting mechanism 4 is provided between the charging tube 12 and the charging end 42.

[0037] The connecting mechanism 4 includes a centering tube 41, which is embedded in the supply device 21. The charging end 42 is movably disposed in the centering tube 41, and the centering tube 41 and the charging end 42 are coaxially arranged. The top end of the centering tube 41 is provided with a horn portion 411. When the charging tube 12 and the charging end 42 are engaged, the horn portion 411 gathers the charging tube 12, so that the charging tube 12 and the charging end 42 are coaxially engaged and inserted.

[0038] It should be noted that the designated area to which the aircraft 1 flies is an area designated according to the actual situation that requires the provision of air communication support. For example, it is an area where communication support is established in the forest area for searching and rescuing people lost in the forest, or other areas where communication is lost due to natural disasters. The supply device 21 is a power replenishment device. Specifically, when the communication base station 11 on the aircraft 1 or the aircraft 1 itself needs to replenish power, that is, when the ground power detection device detects that the battery power of the aircraft 1 or the communication base station 11 is lower than a preset threshold, it is determined that the battery power of the aircraft 1 or the communication base station 11 is insufficient. Therefore, the aircraft 2 on the ground is controlled to carry the power replenishment device and fly to the power replenishment position corresponding to the hovering position of the aircraft 1. Specifically, the aircraft 2 flies to the direct below the aircraft 1, so that the charging tube 12 and the centering tube 41 are coaxial.

[0039] Furthermore, the charging tube 12 and the charging terminal 42 are connected by a concave-convex insertion fit. The charging terminal 42 is movably disposed inside the centering tube 41, which provides a buffer zone when the charging tube 12 and the charging terminal 42 are engaged, thus avoiding damage to the wire core due to rigid contact. The part of the centering tube 41 that slides up and down inside the supply device 21 is a conductor structure. The supply device 21 provides power support to the charging terminal 42 by establishing an electrical connection with the centering tube 41.

[0040] In this embodiment, the specific implementation scenario is as follows: when communication is lost in a designated area and a communication connection needs to be established, the aircraft is controlled to fly to a high altitude in the designated area to establish a communication connection for that area;

[0041] After the airborne communication base station 11 has been in operation for a long time, the communication base station 11 on the aircraft 1 or the aircraft 1 itself needs to be recharged to maintain the airborne base station status. The ground power detection device detects that the battery power of the aircraft 1 or the communication base station 11 is lower than the preset threshold, that is, the battery power of the aircraft 1 or the communication base station 11 is insufficient. Therefore, the ground-based aircraft 2 carrying the resupply device 21 is controlled to fly up to the power resupply position corresponding to the hovering position of the aircraft 1.

[0042] Then, the telescopic mechanism installed inside the aircraft 11 or the communication base station 11 controls the charging tube 12 to extend out from its interior and connect with the charging terminal 42 inside the centering tube 41, thereby establishing an electrical connection between the communication base station 11 and the supply device 21, and replenishing the power of the aircraft 11 or the communication base station 11.

[0043] By setting a horn portion 411 at the top of the centering tube 41, the charging tube 12 contacts the horn portion 411 first during the process of moving into the centering tube 41. As the charging tube 12 continues to elongate, the lateral squeezing force on the inside of the horn portion 411 increases, thereby guiding the charging tube 12 to move into the centering tube 41. This reduces the difficulty of coordination between aircraft 1 and aircraft 2 at high altitudes and facilitates the rapid coordination between the charging tube 12 and the charging end 42 to achieve the function of resupplying the communication base station 11.

[0044] The top of the supply device 21 is provided with a centering mechanism 3. The centering mechanism 3 includes a fixed frame 31 coaxially arranged with the centering tube 41. Multiple sliders 34 arranged in a ring array are installed on the fixed frame 31, and the multiple sliders 34 are all slidably arranged along the diameter of the fixed frame 31. A connecting frame 36 is installed on one side of the slider 34, and a positioning plate 37 is installed at the end of the connecting frame 36 away from the slide rail 32.

[0045] It should be noted that during the process of connecting the charging tube 12 and the charging terminal 42, the driving component on the fixing frame 31 drives the slider 34 to move centripetally, and at the same time drives the connecting frame 36 and the positioning plate 37 to move centripetally, pushing the position of the charging tube 12 so that it is coaxial with the charging terminal 42, which facilitates the connection.

[0046] A ring 33 is placed on the top of the fixed frame 31, and a connecting rod 35 is hinged to the outside of the ring 33. The end of the connecting rod 35 away from the ring 33 is hinged to the slider 34. Multiple arrayed slide rails 32 are installed on the fixed frame 31, and the slider 34 is slidably disposed in the slide rails 32.

[0047] It should be noted that the ring 33 rotates in both directions, and through the connecting rod 35, it simultaneously pulls multiple sliders 34 to make centripetal or concentric movements, thereby reducing the number of driving components that drive the sliders 34 to move.

[0048] The ring 33 is fitted outside the centering tube 41. An arc groove 412 is provided on the outer side of the centering tube 41. A protrusion 331 is installed on the inner side of the ring 33. The protrusion 331 is movably disposed in the arc groove 412.

[0049] It should be noted that when the charging tube 12 extends and squeezes the horn section 411, the centering tube 41 moves downward under force, that is, the arc groove 412 moves downward. With its cooperation with the protrusion 331, the centering tube 41 moves downward and the ring 33 rotates. That is, by the charging tube 12 squeezing the horn section 411, not only does the horn section 411 itself guide and center the end of the charging tube 12, but the downward movement of the horn section 411 under pressure also drives the centering mechanism 3 to move, causing the positioning plate 37 to center and restrict the tube wall of the charging tube 12. This further improves the accuracy and precision of the charging tube 12 in its cooperation with the charging end 42, and helps to reduce the deformation and swaying of the charging tube 12 caused by external wind speed and other environmental factors when it extends at high altitudes.

[0050] A spring 43 is fitted on the outside of the centering tube 41, and the two ends of the spring 43 are in contact with the horn part 411 and the ring 33 respectively.

[0051] In this embodiment, the charging tube 12 elongates, and its bottom first abuts against the inner side of the horn portion 411. As the charging tube 12 continues to elongate, the pressure exerted on the charging tube 12 by the horn portion 411 increases. Guided by the inner inclined wall of the horn portion 411, the charging tube 12 moves towards the interior of the centering tube 41. Simultaneously, the centering tube 41, under pressure, causes the arc-shaped groove 412 to move downward. With the cooperation of the arc-shaped groove 412 and the protrusion 331, the ring 33 rotates as the centering tube 41 moves downward, driving multiple sliders 34 to move centripetally, and simultaneously driving the connecting frame 36 and... The positioning plate 37 also pushes the position of the charging tube 12 centripetally, making it coaxial with the charging end 42, which facilitates the rapid cooperation between the charging tube 12 and the charging end 42 to achieve the function of replenishing the communication base station 11; the centering mechanism 3 and the horn part 411 are combined in a double manner, which greatly improves the accuracy and precision of the charging tube 12 in cooperation with the charging end 42, which helps to reduce the deformation and sway of the charging tube 12 caused by external wind speed and other environmental factors when it is extended at high altitude, and reduces the difficulty of replenishing the power supply of aircraft 1 and aircraft 2 in high altitude.

[0052] Example 2

[0053] Based on Embodiment 1, this embodiment provides an implementation method in which the charging terminal 42 is driven to rotate and engage with the charging tube 12 after contacting the charging tube 12;

[0054] Refer to the instruction manual appendix Figures 1-10The centering tube 41 is provided with an elastic support mechanism 44 inside. The elastic support mechanism 44 includes a piston 441 and an end plate 443. The piston 441 is in contact with the inner wall of the centering tube 41. The charging end 42 is installed on the top of the piston 441. The end plate 443 is fixedly connected to the centering tube 41. A spring telescopic rod 442 is installed between the piston 441 and the end plate 443. The top of the spring telescopic rod 442 is in contact with the bottom of the piston 441. That is, the spring telescopic rod 442 and the piston 441 are separately arranged. The bottom of the spring telescopic rod 442 is fixedly connected to the end plate 443.

[0055] It should be noted that the elastic support mechanism 44 is set up for the same reason as the charging end 42 is movably set inside the centering tube 41. Both are to provide a buffer zone when the charging tube 12 and the charging end 42 are engaged, so as to avoid the two from rigidly contacting and damaging the wire core.

[0056] The centering tube 41 is a cylindrical structure with an open top and a closed bottom. A high-pressure zone is formed between the bottom of the inner cavity of the centering tube 41 and the bottom of the end plate 443. An exhaust pipe 45 is fixedly installed on the outer side of the bottom of the centering tube 41. The exhaust pipe 45 is connected to the high-pressure zone, and the jet direction of the exhaust pipe 45 is tangent to the outer periphery of the centering tube 41. Both ends of the connecting rod 35 are hinged to the ring 33 and the slider 34 through ball joints or universal joints. A valve is installed inside the exhaust pipe 45. When the internal air pressure of the high-pressure zone is greater than the valve threshold, the valve is always open, and the gas in the high-pressure zone is ejected from the exhaust pipe 45.

[0057] It should be noted that the exhaust pipe 45 has one or multiple pipes arranged in a circumferential array. The high-pressure zone is equipped with an air source, and the valve can be a plug. When the air pressure in the high-pressure zone is greater than the plug's tightening force, the plug is forced open from the exhaust pipe 45, and the exhaust pipe 45 continuously exhausts air.

[0058] In this embodiment, the specific implementation scenario is as follows: when the charging tube 12 extends and is coaxial with the charging end 42, the end of the charging tube 12 separates from the horn portion 411, and the centering tube 41 returns to its original shape under the action of the spring 43. Then, the charging tube 12 continues to extend and cooperates with the charging end 42 to compress it. The elastic support mechanism 44 is pressed down, leaving a buffer zone for the cooperation between the charging tube 12 and the charging end 42. When the charging tube 12 extends to its limit position, the internal air source of the high-pressure zone begins to release air. When the internal air pressure of the high-pressure zone is greater than the valve threshold, the valve opens, and the gas in the high-pressure zone is ejected from the exhaust pipe 45. Since the exhaust pipe 45 and the outer circumference of the centering tube 41 are tangential... Therefore, the exhaust pipe 45 exhaust will generate a tangential force in the centering pipe 41, thereby realizing the horizontal rotation of the centering pipe 41. When the centering pipe 41 initially rotates, the friction between the inner wall of the centering pipe 41 and the piston 441 causes the centering pipe 41 to drive the piston 441 and the charging end 42 to rotate horizontally. This causes the charging end 42 to come into contact with the charging pipe 12. The horizontal rotation of the charging end 42 adjusts the position of the charging end 42 so that it is properly inserted and engaged with the charging pipe 12. After the engagement is complete, the spring telescopic rod 442 provides elastic force to lock the charging pipe 12 and the charging end 42 in a concave-convex engagement.

[0059] After the charging tube 12 and the charging end 42 are locked together by the interlocking of the concave and convex parts, the centering tube 41 continues to rotate horizontally. The centering tube 41 and the piston 441 slide relative to each other, that is, the charging end 42 no longer rotates with the centering tube 41. Since the ring sleeve 33 is fitted outside the centering tube 41, when the centering tube 41 rotates horizontally, the ring sleeve 33 moves upward along the axis of the centering tube 41 under the cooperation of the protrusion 331 and the arc groove 412, thereby pulling the slider 34 to move centripetally. This ensures that after the charging tube 12 and the charging end 42 are engaged, the positioning plate 37 can still clamp the middle section of the charging tube 12, reducing the occurrence of the charging tube 12 swinging greatly in the air during the charging process, which would affect the charging effect.

[0060] Example 3

[0061] Based on Embodiment 2, this embodiment implements the rotation of the centering tube 41 around its axis by setting a high-pressure gas cylinder inside the high-pressure zone of the centering tube 41 to act as the gas source in the high-pressure zone.

[0062] The centering tube 41 is equipped with a high-pressure gas cylinder, which is located in the high-pressure zone. When the charging tube 12 extends to its limit position and comes into contact with the charging end 42, the high-pressure gas cylinder opens, and the gas in the high-pressure zone is ejected from the exhaust pipe 45, which drives the centering tube 41 to rotate around its axis, and the ring 33 moves upward along the axis of the centering tube 41.

[0063] In this embodiment, the specific implementation scenario is as follows: the gas source in the high-pressure zone is a high-pressure gas cylinder. After the charging tube 12 and the charging terminal 42 are properly matched, the high-pressure gas cylinder releases gas, causing the high-pressure zone to exhaust gas outward through the exhaust pipe 45, driving the centering tube 41 to rotate around its axis.

[0064] Example 4

[0065] Based on Embodiment 2, and different from Embodiment 3, this embodiment provides an implementation method in which an elastic bladder 5 and a limiting sleeve 6 are provided at the bottom of the high-pressure zone of the centering tube 41, so that the elastic bladder 5 is unidirectionally inflated with the second aircraft 2 during flight to increase the gas density in the high-pressure zone, and the high-pressure zone exhausts gas unidirectionally to drive the centering tube 41 to rotate horizontally during charging.

[0066] An air intake channel 46 is provided on the inner wall of the centering tube 41. The bottom end of the air intake channel 46 is always located below the piston 441. A one-way valve is provided inside the air intake channel 46 to limit the leakage of gas in the high-pressure area through the air intake channel 46. A through hole is provided on the top of the end plate 443. A limit sleeve 6 is installed at the bottom end of the centering tube 41. An elastic bladder 5 is provided inside the limit sleeve 6. The elastic bladder 5 is connected to the high-pressure area. When the second aircraft 2 rises, the piston 441 moves to the bottom of the top of the air intake channel 46 and air enters the high-pressure area through the air intake channel 46. When the second aircraft 2 hovers in the air, the piston 441 moves to the top of the top of the air intake channel 46.

[0067] It should be noted that the elastic bladder 5 is designed to prevent air from flowing back into the high-pressure area during the flight of the aircraft 22, and to open the valve of the exhaust pipe 45 in advance to exhaust the air.

[0068] A limiting wheel 371 is movably mounted on the inner side of the positioning plate 37, and the limiting wheel 371 restricts the charging tube 12 from rotating along its axis.

[0069] In this embodiment, the specific implementation scenario is as follows: When the second aircraft 2 carrying the resupply device 21 ascends to the power resupply position corresponding to the hovering position of the first aircraft 1 during its flight, the horn section 411 experiences high air resistance as the second aircraft 2 ascends, pressing the centering tube 41 down to its limit position. Then, the air resistance pushes the piston 441 to move towards the bottom of the centering tube 41 until the piston 441 is located below the top of the air intake channel 46. At this time, the air intake end of the air intake channel 46 is opened, the second aircraft 2 ascends, and air continuously flows back into the high-pressure area through the air intake channel 46, continuously inflating the high-pressure area until the elastic bladder 5 expands to the maximum state limited by the restrictive sleeve 6.

[0070] As the second aircraft 2 gradually approaches the power replenishment location, its speed decreases and the air resistance decreases. The air pressure inside the high-pressure zone gradually increases. When the air pressure resistance inside the high-pressure zone is greater than the external air resistance encountered by the upward piston 441 of the second aircraft 2, the piston 441 gradually moves upward to a position higher than its initial position. This means that the charging tube 12 can reach the charging terminal 42 before the charging end 42 in embodiments 1-3. As the charging tube 12 continues to move downward to push the charging end 42 and the piston 441, the air pressure in the high-pressure zone is continuously compressed until the air pressure in the high-pressure zone is greater than the threshold of the exhaust pipe 45 valve. The exhaust pipe 45 exhausts air outward, causing the centering tube 41 to rotate the charging end 42 and adjust the position of the charging end 42 so that it can be properly connected with the charging tube 12.

[0071] Moreover, when the exhaust pipe 45 is opened, the elastic bladder 5, in its own restoring deformation state, continuously discharges the gas in the high-pressure area from the exhaust pipe 45, driving the centering tube 41 to rotate, so that the positioning plate 37 of the centering mechanism 3 clamps the middle section of the charging tube 12, restricting the charging tube 12 from swinging in the air and avoiding affecting the charging efficiency.

[0072] Example 5

[0073] In one embodiment of the present invention, a method for improving the power endurance of a device is provided, comprising the following steps:

[0074] Step 1: The aircraft flies to a high altitude within the designated area and establishes a communication network in the designated area. The ground power detection device monitors the battery power of the aircraft in real time.

[0075] Step 2: The aircraft carrying the resupply device 21 ascends to the power resupply location;

[0076] Step 3: The telescopic mechanism controls the charging tube 12 to extend and connect with the charging terminal 42 inside the centering tube 41, establishing an electrical connection between the communication base station 11 and the supply device 21, and supplying power to the aircraft 1.

[0077] The embodiments of this example have been described above. However, this example is not limited to the specific implementation methods described above. The specific implementation methods described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms based on the guidance of this example, and all of them are within the protection scope of this example.

Claims

1. A power-endurance enhancement device, comprising an aircraft (1) and an aircraft (2), wherein an aircraft (1) is equipped with a communication base station (11), the aircraft (1) drives the communication base station (11) to a designated area and provides a communication connection signal to that area, and the aircraft (2) is equipped with a refueling device (21), the aircraft (2) being used to refuel the communication base station (11) in the air, characterized in that: The communication base station (11) is equipped with a vertically arranged charging tube (12), and the supply device (21) is equipped with a charging end (42) that is compatible with the charging tube (12). A connecting mechanism (4) is provided between the charging tube (12) and the charging end (42). The connecting mechanism (4) includes a centering tube (41), which is embedded in the supply device (21). The charging end (42) is movably disposed in the centering tube (41), and the centering tube (41) and the charging end (42) are coaxially arranged. The top end of the centering tube (41) is provided with a horn part (411). When the charging tube (12) and the charging end (42) are engaged, the horn part (411) gathers the charging tube (12) so that the charging tube (12) and the charging end (42) are coaxially engaged and inserted. The top of the supply device (21) is provided with a centering mechanism (3). The centering mechanism (3) includes a fixed frame (31) coaxially arranged with the centering tube (41). Multiple sliders (34) arranged in a ring array are installed on the fixed frame (31), and the multiple sliders (34) are all slidably arranged along the diameter of the fixed frame (31). A connecting frame (36) is installed on one side of the slider (34), and a positioning plate (37) is installed at the end of the connecting frame (36) away from the slide rail (32). The top of the fixed frame (31) is provided with a coaxially arranged ring (33), and a connecting rod (35) is hinged to the outside of the ring (33). The end of the connecting rod (35) away from the ring (33) is hinged to the slider (34). Multiple arrayed slide rails (32) are installed on the fixed frame (31), and the slider (34) is slidably disposed in the slide rails (32). The ring sleeve (33) is fitted outside the centering tube (41). An arc groove (412) is provided on the outer side of the centering tube (41). A protrusion (331) is installed on the inner side of the ring sleeve (33). The protrusion (331) is movably disposed in the arc groove (412). A spring (43) is fitted on the outside of the centering tube (41), and the two ends of the spring (43) are in abutting contact with the horn part (411) and the ring (33) respectively. The centering tube (41) is provided with an elastic support mechanism (44) inside. The elastic support mechanism (44) includes a piston (441) and an end plate (443). The piston (441) is in contact with the inner wall of the centering tube (41). The charging end (42) is installed on the top of the piston (441). The end plate (443) is fixedly connected to the centering tube (41). A spring telescopic rod (442) is installed between the piston (441) and the end plate (443). The top of the spring telescopic rod (442) is in contact with the bottom of the piston (441). The bottom of the spring telescopic rod (442) is fixedly connected to the end plate (443).

2. The power endurance enhancement device according to claim 1, characterized in that: The centering tube (41) is a cylindrical structure with an open top and a closed bottom. A high-pressure zone is formed between the bottom of the inner cavity of the centering tube (41) and the bottom of the end plate (443). An exhaust pipe (45) is fixedly installed on the outer side of the bottom of the centering tube (41). The exhaust pipe (45) is connected to the high-pressure zone, and the jet direction of the exhaust pipe (45) is tangent to the outer periphery of the centering tube (41). Both ends of the connecting rod (35) are hinged to the ring (33) and the slider (34) through ball joints or universal joints. A valve is installed inside the exhaust pipe (45). When the internal air pressure of the high-pressure zone is greater than the valve threshold, the valve is always open, and the gas in the high-pressure zone is ejected from the exhaust pipe (45).

3. The power endurance enhancement device according to claim 2, characterized in that: The centering tube (41) is equipped with a high-pressure gas cylinder. The high-pressure gas cylinder is located in the high-pressure zone. When the charging tube (12) extends to its limit position and abuts against the charging end (42), the high-pressure gas cylinder opens, and the gas in the high-pressure zone is ejected from the exhaust pipe (45), which drives the centering tube (41) to rotate around its axis. The ring (33) moves upward along the axis of the centering tube (41).

4. The power endurance enhancement device according to claim 2, characterized in that: The inner wall of the centering tube (41) is provided with an air inlet channel (46). The bottom end of the air inlet channel (46) is always located below the piston (441). The air inlet channel (46) is provided with a one-way valve inside. The one-way valve is used to limit the leakage of gas in the high-pressure area through the air inlet channel (46). The top of the end plate (443) is provided with a through hole. The bottom end of the centering tube (41) is installed with a limit sleeve (6). The limit sleeve (6) is provided with an elastic bladder (5) inside. 5) Connected to the high-pressure zone, when the second aircraft (2) rises, the piston (441) moves to the lower part of the top of the air intake channel (46), and air enters the high-pressure zone through the air intake channel (46); when the second aircraft (2) hovers in the air, the piston (441) moves to the upper part of the top of the air intake channel (46), and a limiting wheel (371) is movably installed on the inner side of the positioning plate (37), and the limiting wheel (371) restricts the charging tube (12) from rotating along its axis.

5. A method for lifting a power endurance enhancement device, implemented using the power endurance enhancement device according to any one of claims 1-4, characterized in that: Includes the following steps, Step 1: The aircraft (1) flies to the high altitude of the designated area and establishes a communication network in the designated area. The ground power detection device detects the battery power of the aircraft (1) in real time. Step 2: The second aircraft (2) carrying the resupply device (21) ascends to the power resupply location; Step 3: The telescopic mechanism controls the charging tube (12) to extend and connect with the charging terminal (42) inside the centering tube (41) to establish an electrical connection between the communication base station (11) and the supply device (21) and supply power to the aircraft (1).

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