Unmanned aerial vehicle charging system, charging unmanned aerial vehicle and unmanned aerial vehicle system

Abstract

Provided are a UAV charging system, a charging UAV, and a UAV system. The UAV charging system comprises a charging UAV, a charging module, a first battery pack and a second battery pack, both of which are composed of lithium-carbon supercapacitors. The charging UAV is provided with a take-off and landing platform. The first battery pack is installed on the charging UAV, and the second battery pack is installed on a task UAV. The take-off and landing platform is provided with a locking mechanism. The charging module comprises a first control unit, a first charging component, and a second charging component. The first charging component is arranged on the locking mechanism and is connected with the first battery pack. The first control unit is connected with the first battery pack. The second charging component is arranged on the landing gear of the task UAV and is connected with the second battery pack. The landing gear of the task UAV is clamped by the locking mechanism. The first charging component and the second charging component are electrically connected. The first control unit can control the first battery pack to charge the second battery pack, so as to realize in-flight power compensation.

Description

Technical Field

[0001] This disclosure relates to the field of unmanned aerial vehicles (UAVs), and more particularly to a UAV charging system, a charging UAV, and a UAV system. Background Technology

[0002] Drones offer advantages such as low cost, convenient remote control, flexible deployment, and high maneuverability, making them widely used in logistics, data collection, environmental monitoring, area detection, and communications. Currently, drones primarily use lithium batteries as their power source; however, the limited capacity of lithium batteries results in short flight times and restricted operational range. If a drone runs out of power during a mission, it must abort the mission and return to the ground to recharge before resuming operations, which reduces its operational efficiency. Utility Model Content

[0003] The purpose of this disclosure is to provide a drone charging system, a charging drone, and a drone system that can quickly charge drones in the air, thereby improving the drone's working efficiency.

[0004] To address this, a drone charging system is provided for in-flight recharging of a mission drone. The system includes a charging drone, a charging module, a first battery pack, and a second battery pack, both composed of lithium-carbon supercapacitors. The charging drone is equipped with a landing platform for the mission drone to dock. The first battery pack is mounted on the charging drone, and the second battery pack is mounted on the mission drone. A locking mechanism is provided on the landing platform to hold the landing gear of the mission drone. The charging module includes a first control unit, a first charging component, and a second charging component. The first charging component is disposed on the locking mechanism. The first battery pack is electrically connected to the first charging component, and the first control unit is communicatively connected to the first battery pack. The second charging component is disposed on the landing gear and electrically connected to the second battery pack. With the landing gear held in place by the locking mechanism, the first charging component and the second charging component are electrically connected. The first control unit can control the first battery pack to charge the second battery pack.

[0005] A rechargeable drone is used to recharge a mission drone in mid-air. The rechargeable drone includes a take-off and landing platform, a locking mechanism, a first battery pack, a first control unit, and a first charging component. The take-off and landing platform is used for the mission drone to dock and charge. The locking mechanism is located on the take-off and landing platform and is used to clamp the landing gear of the mission drone. The first battery pack is composed of lithium-carbon supercapacitors. The first charging component is located on the locking mechanism and is electrically connected to the first battery pack. The first battery pack is also communicatively connected to the first control unit. The first charging component is used to: after the mission drone docks on the take-off and landing platform and the landing gear of the mission drone is clamped and locked by the locking mechanism, electrically connect with the second charging component of the mission drone, so that the first control unit controls the first battery pack to quickly charge the second battery pack of the mission drone, which is electrically connected to the second charging component and is composed of lithium-carbon supercapacitors.

[0006] An unmanned aerial vehicle (UAV) system includes a mission UAV and the aforementioned charging UAV. The mission UAV is equipped with landing gear, a second battery pack, and a second charging component. The second battery pack is composed of lithium-carbon supercapacitors and can power the mission UAV. The second charging component is electrically connected to the second battery pack.

[0007] The beneficial effects of this disclosure are as follows: When the mission drone's battery is low, it can fly to a nearby charging drone and dock on the charging drone's take-off and landing platform to recharge. During recharging, the locking mechanism can lock the mission drone, ensuring that the first charging component and the second charging component remain in close contact, achieving electrical conduction. At this time, the first control unit can control the first battery pack to charge the second battery pack.

[0008] Therefore, the drone charging system, charging drone, and drone system disclosed herein can charge the mission drone in the air, so that the mission drone does not need to return to the ground to charge. Moreover, both the first battery pack and the second battery pack use lithium-carbon supercapacitors as energy storage elements, which have high energy density and fast charging and discharging capabilities. This not only ensures the mission drone's endurance but also significantly reduces the mission drone's charging time, thereby improving the mission drone's working efficiency. Attached Figure Description

[0009] Figure 1 This is a schematic diagram of the structure of the unmanned aerial vehicle (UAV) system and the UAV charging system disclosed herein.

[0010] Figure 2 This is a simplified structural diagram of the unmanned aerial vehicle (UAV) system and the UAV charging system disclosed herein;

[0011] Figure 3 A perspective view of an example of the unmanned aerial vehicle (UAV) system and UAV charging system disclosed herein;

[0012] Figure 4A perspective view of another example of the drone system and drone charging system disclosed herein.

[0013] The reference numerals in the attached figures are explained as follows:

[0014] 100 Mission UAV 2032 Second Grip Arm

[0015] 101 landing gear 204 slide

[0016] 1011 First Support Part 205 Positioning Mark

[0017] 1012 Second Support Section 300 First Battery Pack

[0018] 102 Vision Inspection Components 400 Second Battery Pack

[0019] 200-charge drone 500 first control unit

[0020] 201 Power Source 600 First Charging Component

[0021] 202 takeoff and landing platform 601 first positive extreme volt

[0022] 203 Locking Mechanism 602 First Negative End Pole

[0023] 2031 First clamping arm 700 Second charging component Detailed Implementation

[0024] The technical solution of this disclosure will be further described below with reference to the accompanying drawings and specific embodiments.

[0025] In the description of this disclosure, unless otherwise expressly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this disclosure based on the specific circumstances.

[0026] In the description herein, it should be understood that the terms "upper," "lower," etc., refer to the orientation or positional relationship shown in the accompanying drawings, and are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this disclosure. Furthermore, the terms "first" and "second" are used merely for descriptive distinction and have no special meaning.

[0027] [Drone systems and drone charging systems]

[0028] Reference Figure 1 and Figure 2 The mission drone 100 is equipped with landing gear 101, a second battery pack 400, and a second charging component 700. The second battery pack 400 provides power to the mission drone. The second battery pack 400 is composed of lithium-carbon supercapacitors. The second charging component 700 is located on the landing gear 101 of the mission drone 100 and is electrically connected to the second battery pack 400.

[0029] Reference Figure 1 and Figure 2 The charging drone 200 is used to recharge the mission drone 100 in mid-air. The charging drone 200 includes a landing platform 202, a locking mechanism 203, a first battery pack 300, a first control unit 500, and a first charging component 600. The landing platform 202 provides a docking and charging point for the mission drone 100. The locking mechanism 203 is mounted on the landing platform 202 and is used to hold the landing gear 101 of the mission drone 100. The first battery pack 300 is composed of lithium-carbon supercapacitors. The first charging component 600 is mounted on the locking mechanism 203, electrically connected to the first battery pack 300, and communicatively connected to the first control unit 500. The first charging component 600 is used to: after the mission drone 100 is docked on the take-off and landing platform 202 and the landing gear 101 of the mission drone 100 is clamped and locked by the locking mechanism 203, it is electrically connected to the second charging component 700 of the mission drone 100, so as to control the first battery pack 300 to quickly charge the second battery pack 400 of the mission drone 100 which is electrically connected to the second charging component 700 through the first control unit 500.

[0030] The mission drone 100 and the charging drone 200 constitute a drone system. The first charging component 600, the second charging component 700, and the first control unit 500 constitute a charging module. The charging drone 200, the charging module, and the first battery pack 300 and the second battery pack 400, both composed of lithium-carbon supercapacitors, constitute a drone charging system.

[0031] In other words, the drone charging system is used to recharge the mission drone 100 in mid-air. (See reference...) Figure 1 and Figure 2The drone charging system includes a charging drone 200, a charging module, and a first battery pack 300 and a second battery pack 400, both composed of lithium-carbon supercapacitors. The first battery pack 300 is mounted on the charging drone 200, and the second battery pack 400 is mounted on the mission drone 100, providing power to the mission drone. The charging drone 200 also includes a landing platform 202 for the mission drone 100 to dock and charge. A locking mechanism 203 is installed on the landing platform 202 to hold the landing gear 101 of the mission drone 100. The charging module includes a first charging component 600, a second charging component 700, and a first control unit 500. The first charging component 600 is mounted on the locking mechanism 203 and electrically connected to the first battery pack 300, which is also communicatively connected to the first control unit 500. The second charging component 700 is mounted on the landing gear 101 of the mission drone 100 and electrically connected to the second battery pack 400.

[0032] When the mission drone 100 runs out of power during a mission, it can dock on the landing platform 202 of the charging drone 200 for in-flight charging. After docking, the locking mechanism 203 clamps the landing gear 101 of the mission drone 100 to lock it in place, preventing it from shaking. This also ensures that the first charging component 600 and the second charging component 700 are in close contact, thus enabling electrical conduction. Therefore, after the mission drone 100 is locked, the first control unit 500 can control the first battery pack 300 to quickly charge the second battery pack 400.

[0033] The disclosed drone charging system enables in-flight charging of the mission drone 100, eliminating the need for the drone to return to the ground for recharging. Both the first battery pack 300 and the second battery pack 400 utilize lithium-carbon supercapacitors as energy storage elements. Lithium-carbon supercapacitors are a type of hybrid supercapacitor. While the negative electrode material is the same as that of traditional supercapacitors (EDLC, Electrical Double Layer Capacitor), the positive electrode has been modified. Through ion adsorption and shallow lithium ion insertion / extraction, the positive electrode of the lithium-carbon supercapacitor significantly improves energy density and achieves a high charge / discharge rate. This ensures the mission drone 100's endurance while simultaneously enabling the first battery pack 300 to rapidly charge the second battery pack 400, drastically reducing the charging time of the mission drone 100 and thus improving its operational efficiency. Any suitable disclosed lithium-carbon supercapacitor cell can be used. For example, the ZFC4.2V15000F(7AH) cell manufactured by Fuwade Electronics (Dongguan) Co., Ltd. (now Fuwade New Energy Technology (Dongguan) Co., Ltd.).

[0034] Moreover, compared with traditional wireless charging methods that use electromagnetic induction or magnetic resonance technology, the drone charging system of this utility model adopts a contact-type wireless charging method, which has no electromagnetic radiation, is not easily interfered with, and can significantly reduce power transmission loss and has good power transmission efficiency, which is conducive to further improving the charging speed. In addition, it eliminates the coil module required by traditional wireless charging, reducing hardware complexity and cost, while reducing the space occupied in the drone's internal space, which is conducive to the drone's lightweight and thin design.

[0035] In addition, the charging drone 200 is equipped with a power source 201, which can use a lithium battery or a fuel engine to provide kinetic energy for the drone's flight. A first battery pack 300 is connected to the power source 201. When the first battery pack 300 has a low charge, the power source 201 can replenish its power to ensure that the first battery pack 300 has sufficient power during the recharging of the mission drone 100.

[0036] The first battery pack 300 is also equipped with a power interface, through which an external power source can be connected to the first battery pack 300 to directly charge the first battery pack 300.

[0037] Specifically, within 3-5 minutes, the first battery pack 300 charges the second battery pack 400 to over 90% capacity.

[0038] In one example, the full-charge voltage of the first battery pack 300 is greater than the nominal voltage of the second battery pack 400, so that there is a sufficient voltage difference between the first battery pack 300 and the second battery pack 400, allowing the first battery pack 300 to directly discharge to quickly charge the second battery pack 400. For example, the full-charge voltage of the first battery pack 300 is 2V-3V higher than the nominal voltage of the second battery pack 400.

[0039] Furthermore, the first battery pack 300 is equipped with a boost unit, which can employ a boost circuit from the prior art. As the output voltage of the first battery pack 300 decreases, and its output voltage becomes lower than the nominal voltage of the second battery pack 400, the first battery pack 300 charges the second battery pack 400 through the boost unit. The boost unit can increase the output voltage of the first battery pack 300 so that its output voltage is always greater than the nominal voltage of the second battery pack 400. Specifically, the size of the charging drone 200 is larger than that of the mission drone 100; for example, the charging drone 200 can be a medium to large-sized drone to meet the docking requirements of the mission drone 100.

[0040] In one example, refer to Figure 1 , Figure 3 as well as Figure 4The landing gear 101 includes a first support portion 1011 and a second support portion 1012 disposed opposite to each other. The locking mechanism 203 includes a first clamping arm 2031 and a second clamping arm 2032 disposed opposite to each other, forming a landing space between the first clamping arm 2031 and the second clamping arm 2032 to accommodate the mission drone 100. Both the first clamping arm 2031 and the second clamping arm 2032 are connected to a driving member (not shown in the figure). The driving member can be a motor, used to drive the first clamping arm 2031 and the second clamping arm 2032 to move or rotate, so that the first clamping arm 2031 and the second clamping arm 2032 can respectively clamp the first support portion 1011 and the second support portion 1012, thereby locking the mission drone 100.

[0041] Specifically, the first charging component 600 includes a first positive terminal 601 and a first negative terminal 602. The first positive terminal 601 is disposed on the first clamping arm 2031 and connected to the positive terminal of the first battery pack 300, and the first negative terminal 602 is disposed on the second clamping arm 2032 and connected to the negative terminal of the first battery pack 300. The second charging component 700 includes a second positive terminal and a second negative terminal (not shown in the figure). The second positive terminal is disposed on the first support portion 1011 and connected to the positive terminal of the second battery pack 400, and the second negative terminal is disposed on the second support portion 1012 and connected to the negative terminal of the second battery pack 400.

[0042] When locking onto the mission drone 100, the first clamping arm 2031 clamps the first support part 1011, which enables the first positive terminal 601 to come into contact with the second positive terminal, and the second clamping arm 2032 clamps the second support part 1012, which enables the first negative terminal 602 to come into contact with the second negative terminal, thereby realizing the electrical conduction of the first charging component 600 and the second charging component 700.

[0043] In one example, the first clamping arm 2031, the second clamping arm 2032, the first support portion 1011, and the second support portion 1012 are all made of conductive materials, such as conductive metals like copper and aluminum. This allows the first clamping arm 2031 to directly serve as the first positive terminal 601 and connect to the positive terminal of the first battery pack 300; the second clamping arm 2032 to directly serve as the first negative terminal 602 and connect to the negative terminal of the first battery pack 300; the first support portion 1011 to directly serve as the second positive terminal and connect to the positive terminal of the second battery pack 400; and the second support portion 1012 to directly serve as the second negative terminal and connect to the negative terminal of the second battery pack 400. With this design, when the first clamping arm 2031 and the second clamping arm 2032 clamp the first support portion 1011 and the second support portion 1012 respectively, the first charging component 600 and the second charging component 700 can achieve electrical conduction without precise alignment, which helps reduce the difficulty of aligning the first charging component 600 and the second charging component 700.

[0044] In one example, refer to Figure 3 The first clamping arm 2031 and the second clamping arm 2032 are slidably disposed on the landing platform 202. The first clamping arm 2031 and the second clamping arm 2032 can move away from each other or towards each other. Before the mission drone 100 lands on the landing platform 202, the first clamping arm 2031 and the second clamping arm 2032 can move away from each other to facilitate the landing of the mission drone 100. After the mission drone 100 lands on the landing platform 202, the first clamping arm 2031 and the second clamping arm 2032 can move towards each other to abut against the first support part 1011 and the second support part 1012 respectively, thereby clamping the landing gear 101. This design can clamp mission drones 100 of different sizes by driving the first clamping arm 2031 and the second clamping arm 2032 to move.

[0045] Furthermore, the lifting platform 202 is provided with a slide groove 204, the length of which extends along the relative direction of the first clamping arm 2031 and the second clamping arm 2032. The first clamping arm 2031 and the second clamping arm 2032 are slidably disposed in the slide groove 204. The slide groove 204 can restrict the movement direction of the first clamping arm 2031 and the second clamping arm 2032 to prevent the first clamping arm 2031 and the second clamping arm 2032 from deviating.

[0046] Specifically, the first clamping arm 2031 and the second clamping arm 2032 each include a sliding part and a clamping part connected to each other. Two slide grooves 204 are provided. The sliding part of the first clamping arm 2031 and the sliding part of the second clamping arm 2032 are respectively slidably disposed in the two slide grooves 204 to limit the movement direction of the first clamping arm 2031 and the second clamping arm 2032. The clamping part of the first clamping arm 2031 and the clamping part of the second clamping arm 2032 are slidably disposed on the top surface of the lifting platform 202 to clamp the first support part 1011 and the second support part 1012 respectively.

[0047] In another example, refer to Figure 4 The first clamping arm 2031 and the second clamping arm 2032 both include a connecting rod and a hook. The connecting rod is movably disposed inside the landing platform 202. One end of the hook is connected to the connecting rod, and the other end of the hook extends to the outside of the landing platform 202. The driving member is connected to the connecting rod and can drive the connecting rod to rotate so that the hook can rotate, so that the hook can clamp the landing gear 101 by its own shape after rotation.

[0048] Furthermore, the landing platform 202 is provided with clearance holes at the positions corresponding to the catch hooks. When rotating, the end of the catch hook away from the connecting rod can be inserted into the clearance holes to stably clamp the landing gear 101.

[0049] In one example, continue to refer to Figure 3 and Figure 4To ensure a good locking effect and avoid damaging the landing gear 101, the charging drone 200 also includes a second control unit and a pressure detection component (not shown in the figure). The pressure detection component is located on the locking mechanism 203 and is used to measure the clamping force of the locking mechanism 203 in real time. The second control unit is connected to the pressure detection component and the drive component respectively. The second control unit can control the drive component according to the measured clamping force to adjust the clamping force of the first clamping arm 2031 and the second clamping arm 2032.

[0050] During the locking process of the landing gear, the pressure detection component can detect the clamping force of the locking mechanism 203 in real time. When the clamping force of the locking mechanism 203 is within the preset range, the second control unit can control the drive component to drive the first clamping arm 2031 and the second clamping arm 2032 to maintain the clamping state, so as to keep the clamping force of the locking mechanism 203 within the preset range, thereby avoiding damage to the landing gear 101 due to excessive clamping force.

[0051] Preferably, the clamping force of the locking mechanism 203 is preset to be twice the weight M of the mission UAV 100, i.e., F = 2 * M * G. Wherein, G is the gravitational acceleration at the Earth's surface, which is 9.8 m / s².

[0052] In one example, refer to Figure 4 The take-off and landing platform 202 is equipped with a positioning marker 205, which may be a positioning image or a positioning luminous ring, etc. The positioning marker 205 may be set in the landing space between the first clamping arm 2031 and the second clamping arm 2032. The mission UAV 100 is equipped with a visual detection component 102, which can use a camera and is used to identify the positioning marker 205.

[0053] Before the mission drone 100 lands on the landing platform 202, the mission drone 100 can identify the positioning mark 205 through the vision detection component 102 to determine whether the landing gear 101 of the mission drone 100 is aligned with the locking mechanism 203, ensuring that the drone lands in the landing space between the first clamping arm 2031 and the second clamping arm 2032, so that after landing, the first clamping arm 2031 and the second clamping arm 2032 can respectively clamp the first support part 1011 and the second support part 1012 of the landing gear 101.

[0054] Furthermore, the mission drone 100 and / or the landing platform 202 are equipped with a distance detection component (not shown in the figure). The distance detection component can be a lidar or a distance sensor. The distance detection component is used to measure the distance between the mission drone 100 and the landing platform 202 to determine whether the mission drone 100 has landed on the landing platform 202. When the distance detection component measures that the distance between the mission drone 100 and the landing platform 202 is consistent with a preset distance value, it indicates that the mission drone 100 has landed on the landing platform 202. At this time, the locking mechanism 203 can lock the mission drone 100.

[0055] In one example, both the mission drone 100 and the charging drone 200 are equipped with a flight attitude control module (not shown in the figure). The flight attitude control module includes a measurement unit (e.g., a wind direction and speed sensor) for detecting the wind direction and speed of the surrounding environment, a drive motor for changing the drone's flight attitude, and a third control unit. The third control unit is connected to the measurement unit and the drive motor respectively. The second control unit can control the drive motor according to the wind direction and speed to change the drone's flight attitude and adjust the drone's attitude angle.

[0056] During the landing of the mission drone 100 onto the take-off and landing platform 202, the measurement unit can detect the wind speed and direction of the surrounding environment in real time. The second control unit can calculate the attitude deviation value of the mission drone 100 and the charging drone 200 based on the measured wind speed and direction information, and control the drive motor to adjust the attitude angle of the mission drone 100 and the charging drone 200 based on the attitude deviation value, thereby preventing the mission drone 100 and the charging drone 200 from being blown sideways by the wind after alignment, and ensuring the alignment accuracy of the mission drone 100 and the charging drone 200.

[0057] [Charging methods for mission drones]

[0058] The charging method for mission drones includes the following steps:

[0059] Step S1: The mission drone 100 communicates with the charging drone 200. When the mission drone 100 is low on power, the mission drone 100 flies toward the nearby charging drone 200 and hovers above the charging drone 200.

[0060] Step S2: The mission drone 100 and the charging drone 200 are positioned and aligned.

[0061] Step S3: After positioning and alignment, the mission drone 100 lands on the take-off and landing platform 202 on top of the charging drone 200.

[0062] Step S4: After landing, the locking mechanism 203 locks the landing gear of the mission drone 100, and at the same time, the first conductive component 600 and the second conductive component 700 are electrically connected.

[0063] Step S5: The first control unit 500 controls the first battery pack 300 to charge the second battery pack 400.

[0064] In one example, step S2 specifically includes: the mission drone 100 identifies the positioning mark 205 on the positioning take-off and landing platform 202 through the vision detection component 102, and adjusts its attitude through its own drive motor, aligning the landing gear 101 with the locking mechanism 203, thereby positioning and aligning the mission drone 100 with the charging drone 200.

[0065] In one example, step S3 specifically includes: after positioning and alignment, the mission drone 100 lands on the landing platform 202. During the landing process, the mission drone 100 and the charging drone 200 detect the wind speed and direction of the surrounding environment in real time through wind speed and direction sensors, and calculate the attitude deviation values ​​of the mission drone 100 and the charging drone 200 respectively based on the measured wind speed and direction information. If the attitude deviation value exceeds a preset threshold, the mission drone 100 and the charging drone 200 can adjust their own attitude angles through their own drive motors according to the attitude deviation value to ensure that the mission drone 100 and the charging drone 200 always remain aligned during the landing process.

[0066] Meanwhile, the distance detection component measures the real-time distance between the mission drone 100 and the charging drone 200 to determine whether the measured real-time distance is consistent with the preset distance value. If they are consistent, it means that the mission drone 100 has landed successfully.

[0067] In one example, step S4 specifically includes: the driving member of the locking mechanism 203 drives the first clamping arm 2031 and the second clamping arm 2032 of the locking mechanism 203 to move or rotate, so as to clamp the first support portion 1011 and the second support portion 1012 of the landing gear 101 of the mission drone 100, so that the first positive terminal 601 on the first clamping arm 2031 is in close contact with the second positive terminal of the first support portion 1011, and the first negative terminal 602 on the second clamping arm 2032 is in close contact with the second negative terminal of the first support portion 1011, thereby electrically connecting the first conductive component 600 and the second conductive component 700.

Claims

1. A drone charging system for replenishing the power of a mission drone (100) in mid-air, characterized in that, The drone charging system includes a charging drone (200), a charging module, a first battery pack (300) and a second battery pack (400), both composed of lithium-carbon supercapacitors. The first battery pack (300) is installed on the charging drone (200), and the second battery pack (400) is installed on the mission drone (100); The charging drone (200) is equipped with a landing platform (202) for the mission drone (100) to dock. A locking mechanism (203) is provided on the landing platform (202) for clamping the landing gear (101) of the mission drone (100). The charging module includes a first control unit (500), a first charging component (600), and a second charging component (700). The first charging component (600) is disposed on the locking mechanism (203), and the first charging component (600) is connected to the landing gear (101) of the mission drone (100). The first battery pack (300) is electrically connected, the first control unit (500) is communicatively connected to the first battery pack (300), the second charging component (700) is disposed on the landing gear (101) and electrically connected to the second battery pack (400), the landing gear (101) is clamped by the locking mechanism (203), the first charging component (600) and the second charging component (700) are electrically connected, and the first control unit (500) can control the first battery pack (300) to charge the second battery pack (400).

2. The drone charging system according to claim 1, characterized in that, The full-charge voltage of the first battery pack (300) is greater than the nominal voltage of the second battery pack (400); The first battery pack (300) is provided with a boost unit. When the output voltage of the first battery pack (300) is less than the nominal voltage of the second battery pack (400), the first battery pack (300) charges the second battery pack (400) through the boost unit.

3. The drone charging system according to claim 1, characterized in that, The landing gear (101) includes a first support portion (1011) and a second support portion (1012) disposed opposite to each other. The locking mechanism (203) includes a first clamping arm (2031) and a second clamping arm (2032) disposed opposite to each other. Both the first clamping arm (2031) and the second clamping arm (2032) are connected to a driving member. The driving member is used to drive the first clamping arm (2031) and the second clamping arm (2032) to move or rotate, so that the first clamping arm (2031) and the second clamping arm (2032) respectively clamp the first support part (1011) and the second support part (1012).

4. The drone charging system according to claim 3, characterized in that, The charging drone (200) also includes a second control unit and a pressure detection component. The pressure detection component is disposed on the locking mechanism (203) and is used to measure the clamping force of the locking mechanism (203). The pressure detection component is communicatively connected to the second control unit, which is connected to the drive component. The second control unit can adjust the drive component according to the measurement value of the pressure detection component.

5. The drone charging system according to claim 3, characterized in that, The first charging component (600) includes a first positive terminal (601) and a first negative terminal (602), the first positive terminal (601) being disposed on the first clamping arm (2031) and the first negative terminal (602) being disposed on the second clamping arm (2032); The second charging component (700) includes a second positive terminal and a second negative terminal. The second positive terminal is disposed on the first support portion (1011), and the second negative terminal is disposed on the second support portion (1012). The first clamping arm (2031) clamps the first support portion (1011) so that the first positive terminal and the second positive terminal abut against each other. The second clamping arm (2032) clamps the second support portion (1012) so that the first negative terminal and the second negative terminal abut against each other.

6. The drone charging system according to claim 3, characterized in that, The take-off and landing platform (202) is provided with a slide groove (204), the length of which extends along the relative direction of the first clamping arm (2031) and the second clamping arm (2032), and the first clamping arm (2031) and the second clamping arm (2032) are respectively slidably disposed in the slide groove (204).

7. The drone charging system according to claim 3, characterized in that, Both the first clamping arm (2031) and the second clamping arm (2032) include a connecting rod and a hook. The connecting rod is movably disposed inside the lifting platform and is connected to the driving member. One end of the hook is connected to the connecting rod, and the other end of the hook extends to the outside of the lifting platform. The driving member can drive the hook to rotate through the connecting rod.

8. The drone charging system according to claim 1, characterized in that, The take-off and landing platform is equipped with a positioning mark (205), and the mission drone (100) is equipped with a visual detection component (102). The visual detection component (102) is used to identify the positioning mark (205) to determine whether the landing gear (101) and the locking mechanism (203) are aligned.

9. The drone charging system according to claim 8, characterized in that, The mission drone (100) and / or the take-off and landing platform (202) are equipped with a distance detection component, which is used to measure the distance between the mission drone (100) and the take-off and landing platform (202) to determine whether the mission drone (100) has landed on the take-off and landing platform (202).

10. The drone charging system according to claim 1, characterized in that, Both the mission drone (100) and the charging drone (200) are equipped with a flight attitude control module. The flight attitude control module is used for a measurement unit for detecting the wind direction and speed of the surrounding environment, a drive motor for changing the flight attitude of the drone, and a third control unit. The third control unit is connected to the measurement unit and the drive motor respectively. The third control unit can control the drive motor according to the wind direction and speed to adjust the attitude angle of the drone.

11. The drone charging system according to claim 1, characterized in that, The charging drone (200) is equipped with a power source (201) for power supply, and the first battery pack (300) is connected to the power source (201), and the power source (201) can replenish the first battery pack (300) with power.

12. A rechargeable drone for in-flight recharging of a mission drone (100), the rechargeable drone (200) being provided with a take-off and landing platform (202), a locking mechanism (203), a first battery pack (300), a first control unit (500), and a first charging component (600). The take-off and landing platform (202) provides a docking and charging station for the mission drone (100). A locking mechanism (203) is installed on the take-off and landing platform (202) and is used to hold the landing gear (101) of the mission drone (100). The first battery pack (300) is composed of lithium-carbon supercapacitors. The first charging component (600) is installed on the locking mechanism (203) and is electrically connected to the first battery pack (300). The first battery pack (300) is also communicatively connected to the first control unit (500). The first charging component (600) is used to: after the mission drone (100) is docked on the landing platform (202) and the landing gear (101) of the mission drone (100) is clamped and locked by the locking mechanism (203), it is electrically connected to the second charging component (700) of the mission drone (100) so as to control the first battery pack (300) to quickly charge the second battery pack (400) of the mission drone (100) which is electrically connected to the second charging component (700) via the first control unit (500).

13. The charging drone according to claim 12, characterized in that, The full-charge voltage of the first battery pack (300) is greater than the nominal voltage of the second battery pack (400); The first battery pack (300) is provided with a boost unit. When the output voltage of the first battery pack (300) is less than the nominal voltage of the second battery pack (400), the first battery pack (300) charges the second battery pack (400) through the boost unit.

14. The charging drone according to claim 12, characterized in that, The landing gear (101) includes a first support portion (1011) and a second support portion (1012) disposed opposite to each other. The locking mechanism (203) includes a first clamping arm (2031) and a second clamping arm (2032) disposed opposite to each other. Both the first clamping arm (2031) and the second clamping arm (2032) are connected to a driving member. The driving member is used to drive the first clamping arm (2031) and the second clamping arm (2032) to move or rotate, so that the first clamping arm (2031) and the second clamping arm (2032) respectively clamp the first support part (1011) and the second support part (1012).

15. The charging drone according to claim 14, characterized in that, The charging drone (200) also includes a second control unit and a pressure detection component. The pressure detection component is disposed on the locking mechanism (203) and is used to measure the clamping force of the locking mechanism (203). The pressure detection component is communicatively connected to the second control unit, which is connected to the drive component. The second control unit can adjust the drive component according to the measurement value of the pressure detection component.

16. The charging drone according to claim 14, characterized in that, The first charging component (600) includes a first positive terminal (601) and a first negative terminal (602), the first positive terminal (601) being disposed on the first clamping arm (2031) and the first negative terminal (602) being disposed on the second clamping arm (2032); The second charging component (700) includes a second positive terminal and a second negative terminal. The second positive terminal is disposed on the first support portion (1011), and the second negative terminal is disposed on the second support portion (1012). The first clamping arm (2031) clamps the first support portion (1011) so that the first positive terminal and the second positive terminal abut against each other. The second clamping arm (2032) clamps the second support portion (1012) so that the first negative terminal and the second negative terminal abut against each other.

17. The charging drone according to claim 14, characterized in that, The take-off and landing platform (202) is provided with a slide groove (204), the length of which extends along the relative direction of the first clamping arm (2031) and the second clamping arm (2032), and the first clamping arm (2031) and the second clamping arm (2032) are respectively slidably disposed in the slide groove (204).

18. The charging drone according to claim 14, characterized in that, Both the first clamping arm (2031) and the second clamping arm (2032) include a connecting rod and a hook. The connecting rod is movably disposed inside the lifting platform and is connected to the driving member. One end of the hook is connected to the connecting rod, and the other end of the hook extends to the outside of the lifting platform. The driving member can drive the hook to rotate through the connecting rod.

19. The charging drone according to claim 14, characterized in that, The take-off and landing platform (202) is equipped with positioning markers (205). The mission drone (100) is equipped with a visual detection component (102), which is used to identify the positioning mark (205) to determine whether the landing gear (101) and the locking mechanism (203) are aligned.

20. The charging drone according to claim 19, characterized in that, The mission drone (100) and / or the take-off and landing platform (202) are equipped with a distance detection component, which is used to measure the distance between the mission drone (100) and the take-off and landing platform (202) to determine whether the mission drone (100) has landed on the take-off and landing platform (202).

21. The charging drone according to claim 12, characterized in that, Both the mission drone (100) and the charging drone (200) are equipped with a flight attitude control module. The flight attitude control module is used for a measurement unit for detecting the wind direction and speed of the surrounding environment, a drive motor for changing the flight attitude of the drone, and a third control unit. The third control unit is connected to the measurement unit and the drive motor respectively. The third control unit can control the drive motor according to the wind direction and speed to adjust the attitude angle of the drone.

22. The charging drone according to claim 12, characterized in that, The charging drone (200) is equipped with a power source (201) for power supply, and the first battery pack (300) is connected to the power source (201), and the power source (201) can replenish the first battery pack (300) with power.

23. An unmanned aerial vehicle (UAV) system comprising a mission UAV (100) and a rechargeable UAV (200) according to any one of claims 12-22. The mission drone (100) is equipped with landing gear (101), a second battery pack (400), and a second charging component (700). The second battery pack (400) is composed of lithium-carbon supercapacitors and can power the mission drone. The second charging component (700) is electrically connected to the second battery pack (400).

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