An unmanned aerial vehicle wireless charging coupling system, a coil winding method and an unmanned aerial vehicle

Abstract

The application discloses an unmanned aerial vehicle wireless charging coupling system, a coil winding method and an unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicle charging. The charging coupling system comprises a transmitting device and a receiving device, the transmitting device comprises a transmitting coil, the receiving device comprises a receiving coil, and further comprises a landing device, the receiving device is arranged on the landing device, and the transmitting device is arranged in a parking area; the transmitting device comprises a ferrite, the ferrite comprises a connecting portion and a stepped symmetrical protruding structure extending outward at the end of the connecting portion, the ferrite as a whole is in a U shape, and the transmitting coil is wound vertically in the U-shaped structure of the ferrite; the receiving device comprises a soft magnet, the receiving coil is wound on both sides of the landing device, a rectangular gap is arranged in the middle of the receiving coil, the soft magnet is arranged in the rectangular gap, and the lower part of the soft magnet is attached to the lower part of the rectangular gap. The coupling system has small space occupation, large coupling coefficient, can realize efficient energy transmission, and is convenient to install and does not affect the flight performance of the unmanned aerial vehicle.

Description

Technical Field

[0001] This invention belongs to the field of drone charging technology, and more specifically, relates to a drone wireless charging coupling system, a coil winding method, and a drone. Background Technology

[0002] With the increasingly widespread application of drone technology, charging technologies for various drones have developed rapidly, and wireless power transfer technology plays an important role in providing contactless, safe and reliable power replenishment for the drone industry.

[0003] Compound-wing UAVs, combining the takeoff and landing flexibility and endurance advantages of fixed-wing and multi-rotor aircraft, are widely used in aerial surveying, inspection, and other fields. However, wireless charging technology in their landing gear area still has significant shortcomings. This area has a complex spatial structure and is constrained by the landing gear and apron layout. Existing wireless charging coupling devices mostly use planar coil structures, which are difficult to adapt to the three-dimensional installation space. Furthermore, the ferrite core layout lacks targeted design, resulting in severe magnetic leakage. More importantly, traditional devices have weak anti-offset capabilities; when the UAV's landing position is inaccurate, the coupling efficiency drops sharply, failing to meet the needs of compound-wing UAVs for efficient and stable charging in the landing gear area. These technical deficiencies severely restrict the application of wireless charging for compound-wing UAVs. Summary of the Invention

[0004] This invention addresses the technical problems existing in the prior art by providing a wireless charging coupling system for unmanned aerial vehicles (UAVs), a coil winding method, and an UAV.

[0005] To solve the above-mentioned technical problems, the present invention provides the following technical solution: A wireless charging coupling system for unmanned aerial vehicles (UAVs) includes a transmitter and a receiver. The transmitter includes a transmitting coil, and the receiver includes a receiving coil. The system also includes a landing device, with the receiver mounted on the landing device and the transmitter positioned in the parking area. The transmitting device includes a ferrite, which includes a connecting part and a stepped symmetrical protruding structure extending outward from the end of the connecting part. The ferrite is U-shaped in general, and the transmitting coil is vertically wound in the U-shaped structure of the ferrite. The receiving device includes a soft magnet, a receiving coil wound on both sides of the landing device, a rectangular gap in the middle of the receiving coil, the soft magnet being placed in the rectangular gap, and the lower part of the soft magnet being in contact with the lower part of the rectangular gap.

[0006] Preferably, the landing gear includes a landing gear, which includes a horizontal support section, a Y-shaped transition connection section, and a strut section.

[0007] Preferably, the width of the Y-shaped transition connection section is W1, the width of the coverage area of ​​the transmitting coil is W2, W2 > W1; and the distance between the transmitting coil and the ferrite is h1, h1 > W2 / 3 - W2 / 2.

[0008] Preferably, the receiving coil is wound on the Y-shaped transition connecting section and the strut section of the landing gear, and is attached to the composite side of the inclined and vertical surfaces of the landing gear; the coil is wound from the outside to the inside starting from the lower side of the inclined surface, and after winding a set number of turns clockwise or counterclockwise on the composite surface, it passes through the landing gear to the other side and is wound from the inside to the outside, with the winding directions of the coils on both sides being opposite and the number of turns being the same.

[0009] Preferably, the plane of the receiving device forms an angle of 45°-90° with the plane of the transmitting device.

[0010] Preferably, the ferrite connection section is rectangular, the ferrite has a horizontal rectangle as the core, and the two ends have a symmetrical protruding structure of "double-layer steps", with a U-shaped groove in the middle, and the transmitting coil is vertically wound in the U-shaped groove. The side view of the transmitting coil is rectangular.

[0011] Preferably, the transmitting device further includes a heat dissipation layer, which is attached to the side of the ferrite away from the transmitting coil. The heat dissipation layer is made of graphene heat sink or aluminum alloy heat sink, and its thickness is 0.5-1mm.

[0012] Furthermore, the present invention also provides a coil winding method for a drone wireless charging coupling system, which is applied to a drone wireless charging coupling system and includes at least one of the following winding methods: 1) Tight winding: The coil turns are tightly fitted together. The winding starts from the first side inside the ferrite U-shaped structure. After the first turn is completed, the second turn is tightly fitted to the first turn in the horizontal direction until the second side of the ferrite U-shaped structure is reached. The coil spacing is evenly distributed. The lower coil of the ferrite can be tightly wound or double-layered. At this time, the distance h1 between the lower end of the coil rectangle and the ferrite is greater than W2 / 2. 2) Sparse winding: The coil turns are left with uniform gaps. The winding starts from the first side inside the ferrite U-shaped structure. After the first turn is completed, the second turn is kept at a set interval from the first turn until the second side of the ferrite U-shaped structure is reached. The coil spacing is uniform. At this time, the distance h1 between the lower end of the coil rectangle and the ferrite is greater than W2 / 3. 3) Uneven winding: The coil has different turn spacing in different areas within the ferrite U-shaped structure. Starting from the first side of the ferrite U-shaped structure, after the first turn is completed, the second turn is spaced apart from the first turn and the spacing between each coil is different until the second side of the ferrite U-shaped structure. The overall distribution of the coil is uneven. 4) Gradient winding: The coil turn spacing changes in a gradient. The winding starts from the first side inside the ferrite U-shaped structure. After the first turn is completed, the second turn is spaced apart from the first turn. The coil turn spacing is the same in different areas, and the turn spacing is different between different areas, until the second side of the ferrite U-shaped structure is reached. 5) Double-layer coil winding: Two layers of coils are tightly wound, starting from the first side inside the ferrite U-shaped structure. After the first turn is wound, the second turn is close to the upper part of the first turn, and the third turn is close to the horizontal side of the first turn. The winding continues until the second side of the ferrite U-shaped structure is reached, and the coils are evenly distributed.

[0013] Preferably, the coil winding method is applied to the transmitting coil; The transmitting device transmits electrical energy through the coupling of the transmitting coil and the receiving coil of the receiving device. When high-frequency alternating current is applied to the transmitting coil, a high-frequency alternating magnetic field is generated. Under the coupling effect of the alternating magnetic field, the receiving coil generates an induced electromotive force and forms an induced current, thus realizing the wireless transmission of electrical energy from the transmitting end to the receiving end.

[0014] Furthermore, the present invention also provides a drone, including a fuselage body, a receiving device in a drone wireless charging coupling system, a fixed-wing lift assembly, and a vertical take-off and landing power assembly, wherein the drone is charged using the drone wireless charging coupling system.

[0015] Compared with the prior art, the present invention has the following beneficial effects: This invention addresses the problems of existing technologies by providing a wireless charging coupling system and coil winding method for drones that offers wide adaptability, high transmission efficiency, and low loss. The receiving device is mounted on the drone's landing gear and includes a receiving coil and a soft magnet. The transmitting device includes a transmitting coil and a ferrite core. The transmitting device is coupled to the receiving coil via the transmitting coil. Optimized ferrite core layout significantly reduces magnetic leakage, and the application of high-permeability materials significantly reduces hysteresis and eddy current losses, improving the stability and lifespan of the energy conversion. The coupling device in this application has a small footprint, a large coupling coefficient, and achieves efficient energy transmission. It is also easy to install and does not affect the drone's flight performance. For different scenarios, the winding method can be changed to make it more adaptable, effectively improving the power density, heat dissipation performance, magnetic field adaptability, position tolerance, and anti-interference capability of the drone wireless charging system in different scenarios. Various coil winding methods allow for a wider range of applications for this coupling device. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this application, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the structure of a wireless charging coupling system according to one embodiment of the present invention; Figure 2 This is a schematic axial cross-sectional view of a wireless charging coupling system according to one embodiment of the present invention; Figure 3 This is a schematic diagram of the main structure of one embodiment of the present invention; Figure 4 This is a schematic cross-section of a tightly wound transmitting coil according to one embodiment of the present invention. Figure 1 ; Figure 5 This is a schematic cross-section of a tightly wound transmitting coil according to one embodiment of the present invention. Figure 2 ; Figure 6 This is a schematic cross-sectional view of a sparsely wound transmitting coil according to one embodiment of the present invention; Figure 7 This is a schematic cross-section of a non-uniformly wound transmitting coil according to one embodiment of the present invention. Figure 1 ; Figure 8 This is a schematic cross-section of a non-uniformly wound transmitting coil according to one embodiment of the present invention. Figure 2 ; Figure 9 This is a schematic cross-section of a non-uniformly wound transmitting coil according to one embodiment of the present invention. Figure 3 ; Figure 10 This is a schematic cross-sectional view of a gradient-wound transmitting coil according to one embodiment of the present invention; Figure 11 This is a schematic diagram of a cross-section of a double-layer coil for transmitting the coil according to one embodiment of the present invention; Figure 12 This is a schematic diagram of the experimental connection of a receiving device and its compensation capacitor according to one embodiment of the present invention; Figure 13 This is a schematic diagram of the experimental connection of the transmitting device and its compensation capacitor according to one embodiment of the present invention; Figure 14 This is a schematic diagram of the connection structure of the experimental platform according to one embodiment of the present invention; Figure 15 This is a curve showing the coupling coefficient variation of tightly wound and gradient wound coils according to one embodiment of the present invention; Figure 16This is an efficiency variation curve of tightly wound and gradient wound coils according to one embodiment of the present invention; Figure 17 This is a schematic diagram illustrating the simulation changes of the coupling coefficient in the X direction for various winding methods according to one embodiment of the present invention; Figure 18 This is a schematic diagram illustrating the simulation changes of the coupling coefficient in the Y direction for various winding methods according to one embodiment of the present invention; Figure 19 This is a schematic diagram illustrating the simulation changes of the coupling coefficient in the Z direction for various winding methods according to one embodiment of the present invention; Figure 20 This is a simulation cloud diagram of the magnetic induction intensity of a tightly wound coil according to one embodiment of the present invention; Figure 21 This is a simulation cloud diagram of the magnetic induction intensity of a sparsely wound coil according to one embodiment of the present invention; Figure 22 This is a simulation cloud diagram of the magnetic induction intensity of a coil gradient winding method according to one embodiment of the present invention; Figure 23 This is a simulation cloud diagram of the magnetic induction intensity of a coil with uneven winding in one embodiment of the present invention; Figure 24 This is a simulation cloud diagram of the magnetic induction intensity of a double-layer coil winding method according to one embodiment of the present invention.

[0018] Explanation of symbols in the diagram: 1. Transmitting device; 11. Transmitting coil; 12. Ferrite; 2. Receiving device; 21. Receiving coil; 22. Soft magnet; 3. Landing device; 31. Landing gear; 32. Horizontal support section; 33. Y-shaped transition connection section; 34. Strut section. Detailed Implementation

[0019] To make the technical problems, solutions, and beneficial effects of this application clearer, the following detailed description, in conjunction with the accompanying drawings and embodiments, provides a wireless charging coupling system, coil winding method, and drone provided by this application. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0020] Example 1 Please see Figure 1 This invention provides a wireless charging coupling system for unmanned aerial vehicles (UAVs), including a transmitting device 1 and a receiving device 2. The transmitting device 1 includes a transmitting coil 11, and the receiving device includes a receiving coil 21. The system also includes a take-off and landing device 3. The receiving device 2 is mounted on the take-off and landing device 3, and the transmitting device 1 is mounted in the parking area. The transmitting device 1 includes a ferrite 12, which includes a connecting part and a stepped symmetrical protruding structure extending outward from the end of the connecting part. The ferrite 12 is U-shaped in general, and the transmitting coil 11 is vertically wound in the U-shaped structure of the ferrite 12. The receiving device 2 includes a soft magnet 22, a receiving coil 21 wound on both sides of the landing device 3, a rectangular gap in the middle of the receiving coil 21, and the soft magnet 22 is placed in the rectangular gap, with the lower part of the soft magnet 22 in contact with the lower part of the rectangular gap.

[0021] This invention addresses the problems of existing technologies by providing a wireless charging coupling system for drones that is adaptable to various scenarios, has high transmission efficiency, and low loss. The receiving device 2 is mounted on the drone's landing gear 3 and includes a receiving coil 21 and a soft magnet 22. The transmitting device 1 includes a transmitting coil 11 and a ferrite core 12, and the transmitting device 1 is coupled to the receiving coil 21 via the transmitting coil 11. This embodiment significantly reduces magnetic leakage by optimizing the ferrite core 12 layout. Combined with the application of high permeability materials, it significantly reduces hysteresis and eddy current losses, improving the stability and lifespan of the energy conversion. The coupling device in this application has a small footprint, a large coupling coefficient, and achieves efficient energy transmission. It is also easy to install and does not affect the drone's flight performance. For different scenarios, the winding method can be changed to make it more adaptable, effectively improving the power density, heat dissipation performance, magnetic field adaptability, position tolerance, and anti-interference capability of the drone wireless charging system in different scenarios. Various coil winding methods can further expand the application of this coupling device.

[0022] In this embodiment, as Figures 1-3 As shown, the landing gear 3 includes a landing gear 31, which includes a horizontal support section 32, a Y-shaped transition connection section 33, and a strut section 34.

[0023] Specifically, the horizontal support section 32, the Y-shaped transition connection section 33, and the support column section 34 are integrated. The support column section 34 is vertically positioned for vertical load bearing; the Y-shaped transition connection section 33 is used to distribute the load; the horizontal support section 32 is located at the lower end of the Y-shaped transition connection section 33, and is used to increase the ground contact area to improve stability. The horizontal support section 32 is equipped with a horizontal support base plate, and the support column section is equipped with a support column. Load transfer and ground support are achieved through the landing gear.

[0024] In this embodiment, the launching device 1 is set in the parking apron of the parking area. The launching device 1 includes a launching coil 11 and a ferrite 12. The connecting part is a long rectangular connecting structure set horizontally in the middle of the ferrite. Both the left and right ends of the connecting part are provided with a "stepped" symmetrical protruding structure. The protruding structure first extends upwards by a section of rectangle, and then expands outwards into a wider rectangle, forming a double-step shape, which is roughly a U-shaped structure. This facilitates coil winding, gathers magnetic field lines, and reduces magnetic leakage. The coil is vertically wound in the U-shaped groove of the ferrite to reduce the width of the slot on the parking apron.

[0025] Furthermore, in this embodiment, the cross-section of the ferrite 12 connection is rectangular. The ferrite 12 has a horizontal rectangle as its core, with both ends forming a symmetrical "double-step" protruding structure. A U-shaped groove is provided in the middle, and the transmitting coil 11 is vertically wound in the U-shaped groove. The side view cross-section of the transmitting coil 11 is rectangular. Thus, by optimizing the layout of the ferrite 12, magnetic leakage is significantly reduced. Combined with the application of high permeability materials, hysteresis and eddy current losses are significantly reduced, improving the stability and service life of the device's energy conversion.

[0026] Furthermore, when the transmitting coil 11 is tightly wound, the transmitting coil 11 begins to be wound at a certain distance from one side of the ferrite 12 slot. During the winding, the coil is wound along the slotting direction, and the next turn is in close contact with the horizontal direction of the coil.

[0027] In this embodiment, the width of the Y-shaped transition connection section 33 is W1, and the coverage width of the transmitting coil 11 is W2, where W2 > W1. The number of turns of the coil is related to the width W1 of the Y-shaped structure of the HMI landing gear, and the distance between the lower rectangular edge of the transmitting coil 11 and the ferrite 12 is h1, which is related to the coil winding method, and h1 > W2 / 3 - W2 / 2. When the coil is tightly wound, h1 is greater than W2 / 2; when it is sparsely wound, h1 should be greater than W2 / 3. Depending on the coil winding method, the coupling device can be adapted to different application scenarios.

[0028] Furthermore, the receiving coil 21 is wound around the Y-shaped transition connecting section 33 and the strut section 34 of the landing gear, and is attached to the composite side of the inclined and vertical surfaces of the landing gear 31; the coil is wound from the outside to the inside starting from the lower side of the inclined surface, and after winding a set number of turns clockwise or counterclockwise on the composite surface, it passes through the landing gear to the other side and is wound from the inside to the outside, with the winding directions of the coils on both sides being opposite and the number of turns being the same.

[0029] Specifically, such as Figure 3 As shown, the receiving device 2 is mounted on the landing gear 31 of the UAV. The receiving device 2 includes a receiving coil 21 and a soft magnet 22. In order to improve the coupling coefficient, the coil is wound on both sides of the landing gear 31. The coil is wound on the Y-shaped transition connection section 33 and the support section 34 of the landing gear. The coils on both sides are wound in close contact with the landing gear to reduce the drag when the UAV is flying.

[0030] In this embodiment, the UAV landing gear 31 has an inclined plane below and a vertical plane above, forming a composite side structure of "inclined plane + vertical plane". When winding from the outside to the inside, the coil starts winding from the lower side of the inclined plane and winds clockwise or counterclockwise on the composite plane. After winding a certain number of turns, the coil passes through the landing gear to the other side. When winding from the inside to the outside, the winding directions of the coils on both sides are opposite, and the number of turns is the same as that of the coil on the other side.

[0031] Furthermore, a rectangular gap is left in the middle of the receiving coil 21, and the soft magnet 22 is placed in the rectangular gap with the same thickness as the coil. The lower part of the soft magnet 22 is in contact with the lower part of the rectangular gap of the coil, and the left and right sides of the soft magnet 22 are spaced a certain distance from the left and right sides of the rectangular gap of the coil. The upper part of the soft magnet 22 is spaced a certain distance from the upper part of the rectangular gap of the coil. The coil is set on both sides to improve the coupling coefficient.

[0032] Furthermore, taking the plane where the transmitting device 1 is located as a reference, the plane where the receiving device 2 is located forms an angle of 45°-90° with the plane of the transmitting device 1.

[0033] In this embodiment, the transmitting device 1 transmits electrical energy through the transmitting coil 11 and the receiving coil 21 of the receiving device 2. After the transmitting coil 11 is supplied with high-frequency alternating current, it generates a high-frequency alternating magnetic field. Under the coupling effect of the alternating magnetic field, the receiving coil 21 generates an induced electromotive force due to electromagnetic induction and forms an induced current. The double-sided coil makes the current larger, realizing the wireless transmission of electrical energy from the transmitting end to the receiving end.

[0034] Furthermore, as a preferred embodiment of the present invention, the transmitting device 1 further includes a heat dissipation layer, which is attached to the side of the ferrite 12 away from the transmitting coil. The heat dissipation layer is made of graphene heat sink or aluminum alloy heat sink, and its thickness is 0.5-1mm.

[0035] Example 2 Furthermore, this embodiment of the invention provides a wireless charging coupling system for unmanned aerial vehicles. Based on the structure of embodiment 1, this embodiment also includes the following technical features.

[0036] Specifically, the coupling coil in this embodiment of the invention can use Litz wire as the core conductive material. The Litz wire is made of multiple strands of insulated enameled wire twisted together, which can effectively suppress the skin effect and proximity effect under high frequency transmission, reduce the AC loss of the coil, and improve the energy transmission efficiency. At the same time, the multi-strand twisted structure gives the coil excellent resistance to mechanical fatigue, which can adapt to the vibration and shock during the take-off and landing of the UAV and reduce the risk of wire breakage.

[0037] In this embodiment, the soft magnet and the coil are glued together with double-sided adhesive, which enables rapid assembly of the two and ensures the stability of the structural connection. At the same time, the insulating properties of the double-sided adhesive can prevent electrical contact between the soft magnet and the coil wires, thus improving system safety.

[0038] Example 3 This invention provides a coil winding method for a wireless charging coupling system for unmanned aerial vehicles (UAVs), which is applied to the UAV wireless charging coupling system and includes at least one of the following winding methods: 1) Tight winding: such as Figure 4 , Figure 5 As shown, the coil turns are tightly fitted together, and the winding begins from the first side inside the U-shaped structure of ferrite 12. After the first turn is wound, the second turn is tightly fitted to the first turn in the horizontal direction until the second side of the U-shaped structure of ferrite 12 is reached. The coil spacing is evenly distributed. The lower coil of ferrite 12 can be tightly wound or double-layered. At this time, the distance h1 between the lower end of the coil rectangle and the ferrite is greater than W2 / 2.

[0039] In this embodiment, the coil is wound starting on one side of the ferrite 12 slot. After the first turn is completed, the next turn is close to the first turn until the other side of the ferrite slot is reached. The coil spacing is even, maximizing the number of turns within a limited volume to increase power density and meet the need for rapid power replenishment in a short time. When winding the lower part of the ferrite 12, a tight winding or double-layer winding method can be adopted to adapt to different spaces. At the same time, it can adapt to the small-range precise alignment during the vertical take-off and landing of UAVs, ensuring electromagnetic coupling efficiency. This achieves the technical effect of high power and high reliability charging in a compact space.

[0040] 2) Sparse winding: such as Figure 6 As shown, the coil turns are spaced evenly. The winding starts from the first side inside the ferrite 12 U-shaped structure. After the first turn is wound, the second turn is kept at a set interval from the first turn until the second side of the ferrite 12 U-shaped structure is reached. The coil spacing is evenly distributed. At this time, the distance h1 between the lower end of the coil rectangle and the ferrite is greater than W2 / 3.

[0041] In this embodiment, the coil is wound starting on one side of the ferrite 12 slot. After the first turn is completed, the next turn is spaced apart from the first turn, continuing until the other side of the ferrite 12 slot, resulting in a uniform coil spacing. This sparse winding provides excellent heat dissipation, effectively mitigating the risk of heat buildup in high-temperature environments and ensuring long-term reliable operation of the charging system. Furthermore, the sparse structure facilitates cleaning and maintenance, reducing the probability of interference from foreign objects such as dust and moisture. This achieves high stability and ease of maintenance for the charging system even in harsh environments.

[0042] 3) Uneven winding: such as Figures 7-9As shown, the coil has different turn spacing in different areas within the ferrite 12 U-shaped structure. Starting from the first side within the ferrite 12 U-shaped structure, after the first turn is completed, the second turn is spaced apart from the first turn and the spacing between each coil is different until the second side of the ferrite 12 U-shaped structure. The overall distribution of the coil is uneven.

[0043] In this embodiment, the coil is wound starting on one side of the ferrite 12 slot. After the first turn is completed, the next turn has a certain interval from the first turn, and the intervals vary between different coils until the other side of the ferrite 12 slot, resulting in an uneven coil distribution. This non-uniform design allows for targeted adjustment of the magnetic field distribution, compensating for the influence of the housing structure on electromagnetic coupling. This ensures efficient charging even in special receiver positions, while also providing a certain degree of resistance to offset. Furthermore, the magnetic field can be locally strengthened to meet the design requirements of priority charging in specific areas. This achieves precise optimization of the magnetic field distribution and efficient charging in customized scenarios.

[0044] 4) Gradient winding: such as Figure 10 As shown, the coil turn spacing varies in a gradient. The winding starts from the first side inside the ferrite 12 U-shaped structure. After the first turn is wound, the second turn is spaced apart from the first turn. The coil turn spacing is the same in different areas, but the turn spacing is different between different areas, until the second side of the ferrite 12 U-shaped structure.

[0045] In this embodiment, the coil is wound starting on one side within the 12 slots of the ferrite core. After the first turn is completed, the next turn has a certain interval from the first turn. Different regions have the same interval within a region, but different regions have different intervals. This winding method optimizes the spatial distribution of the magnetic field, keeping the magnetic field relatively uniform over a large area. This significantly improves the positional tolerance of the receiver and reduces the requirements for takeoff and landing accuracy. This achieves stable and efficient charging over a large alignment range, adapting to the multi-mission scenario switching needs of compound-wing UAVs.

[0046] 5) Double-layer coil winding: such as Figure 11 As shown, two layers of coils are tightly wound, starting from the first side inside the ferrite 12 U-shaped structure. After the first turn is wound, the second turn is close to the upper part of the first turn, and the third turn is close to the horizontal side of the first turn. The winding continues in sequence until the second side of the ferrite U-shaped structure, and the coils are evenly distributed.

[0047] In this embodiment, the coil is wound starting on one side of the ferrite 12 slot. After the first turn is completed, the second turn is close to the top of the first turn, and the third turn is close to the horizontal side of the first turn, until the other side of the ferrite 12 slot. This uniform coil distribution significantly improves the power transmission capability and electromagnetic coupling stability, meeting the demand for rapid power replenishment at the kilowatt level. At the same time, the double-layer structure has high magnetic field redundancy and can resist strong electromagnetic interference, thereby achieving the technical effect of high-power and high-reliability charging and ensuring the robustness of the system in complex electromagnetic environments.

[0048] Furthermore, this embodiment applies different coil winding methods to the transmitting coil, adapting to various conditions. Through targeted combination designs of multiple coils, precise adaptation across all scenarios is achieved. This embodiment maximizes power density and ensures precise coupling through tight winding, optimizes heat dissipation and maintainability in harsh environments with high temperature and humidity through sparse winding, precisely adjusts the magnetic field distribution through uneven winding, expands the charging alignment range for the composite wing UAV's takeoff and landing through gradient winding, and meets the requirements for power transmission and electromagnetic interference resistance through double-layer coil winding. These measures address the shortcomings of existing technologies in terms of space constraints, environmental adaptability, customized adaptation, alignment tolerance, and high-power reliability, effectively improving the power density, heat dissipation performance, magnetic field adaptability, position tolerance, and anti-interference capability of the composite wing UAV wireless charging system in different scenarios.

[0049] Example 4 Furthermore, the present invention also provides a drone, including a fuselage body, a receiving device in a drone wireless charging coupling system, a fixed-wing lift assembly, and a vertical take-off and landing power assembly, wherein the drone is charged using the drone wireless charging coupling system.

[0050] This embodiment of the wireless charging coupling system is adapted to compound-wing UAVs. The coupling system occupies little space, has a large coupling coefficient, enables efficient energy transfer, and is easy to install without affecting the UAV's flight performance. Wireless charging can be achieved directly through the transmitter in the parking area, without the need for additional wiring, thus improving operational continuity.

[0051] Example 5 The embodiments of the present invention experimentally verify the wireless charging coupling system provided in the above embodiments.

[0052] Figure 12 , Figure 13 These are the receiving device and its compensation capacitor, and the transmitting device and its compensation capacitor, respectively. Figure 14 This is a schematic diagram of the experimental platform; the experimental platform uses a power supply model FTA60-100, a power analyzer model WT1804E, and an electronic load model FT6412A 150V / 120A.

[0053] Test method: A spatial rectangular coordinate system (where the x-axis is along the horizontal left and right direction) is established with the geometric center of the transmitting device as the origin. Points are evenly spaced along the positive and negative x-axis with a step size of 1 cm. The coupling efficiency of the system and the coupling coefficient with the coupling device are measured at each measurement point.

[0054] The experimental data are shown in the table below.

[0055] Table 1. Efficiency of tightly wound coupled systems

[0056] Table 2 Efficiency of Gradient-Wound Coupled Systems

[0057] In conclusion, as follows: Figure 15 , Figure 16 As shown, regardless of whether it is tight winding or gradient winding, the coupling coefficient and energy transmission efficiency reach their peak at the geometric center of the transmitting device (coordinate 0), and gradually decrease as the absolute value of the coordinate increases (the offset distance increases), and drop sharply after the offset is ≥3cm. Tight winding has better energy focusing in the near field, while gradient winding has a wider magnetic field coverage. The coupling and transmission efficiency of both winding methods show a trend of first increasing and then decreasing with the increase of spatial offset distance, with the near field center being the optimal transmission position.

[0058] Gradient-wound coupling devices offer superior mid-to-long-range transmission performance and a wider magnetic field coverage. Tightly wound coupling devices provide more stable transmission efficiency and stronger energy focusing in the near-field offset range. Furthermore, the tightly wound coil structure concentrates magnetic field energy in a small area around the transmission center, maintaining high coupling matching even with small near-field offsets and exhibiting a slower transmission efficiency decay rate. This makes them suitable for applications requiring high near-field positioning accuracy. Fully tight winding is suitable for scenarios with small near-field offsets, high positioning accuracy requirements, and energy-focused transmission needs; gradient winding is suitable for mid-to-long-range offsets, high magnetic field coverage requirements, and scenarios needing to accommodate multiple transmission locations. The choice between the two winding processes can be determined based on the actual spatial location requirements of wireless energy transmission.

[0059] Furthermore, the embodiments of the present invention are verified by simulation based on the above experiments, as shown below.

[0060] like Figure 17 As shown, it illustrates the simulation variation of the coupling coefficient in the X direction for various winding methods.

[0061] The simulation data in the X direction for each winding method are shown in Table 3.

[0062] Table 3 Simulation data in the X direction

[0063] As shown above, the coupling coefficient of the tightly wound structure exhibits the following trend with distance: the upward and downward slopes are the steepest, the high coupling coefficient is maintained only within an extremely narrow distance range, and it is most sensitive to positional deviations. This structure can achieve optimal energy transfer efficiency in static scenarios with fixed positions and high alignment accuracy.

[0064] The coupling coefficient of the sparse winding structure exhibits the following trend with distance: the lowest peak value, but the flattest curve, resulting in the widest effective coupling distance range, and maintaining coupling capability even under large positional offsets. This structure has the highest tolerance for positional deviations and is suitable for scenarios with low alignment accuracy and large positional fluctuations.

[0065] The coupling coefficient of the gradient-wound structure exhibits the following trend with distance: the peak value is at a moderate level, the overall slope of the curve is moderate, the effective coupling range is wider than that of a tightly coupled structure, and it has good tolerance for positional deviations. This structure achieves a good balance between coupling efficiency and positional adaptability, making it suitable for scenarios with moderate positional fluctuations.

[0066] The coupling coefficient of the non-uniform winding structure exhibits the following trend with distance: it enters the effective coupling region earliest among the five structures, and its descent phase is relatively gentle. This structure can establish effective coupling earlier in scenarios with large distance variations, adapting to dynamically changing initial position scenarios.

[0067] The coupling coefficient of the double-layer winding structure exhibits the following trend with distance: the peak value is close to that of the tightly wound structure, and the high coupling coefficient range shows a relatively gentle plateau period, with a slightly wider effective coupling range than the tightly wound structure. This structure combines high transmission efficiency with a certain degree of positional fault tolerance, making it suitable for scenarios requiring high coupling efficiency while allowing for small-range positional fluctuations.

[0068] like Figure 18 As shown, it illustrates the simulation variation of the coupling coefficient in the Y direction for various winding methods.

[0069] The simulation data in the Y direction for each winding method are shown in Table 4.

[0070] Table 4 Simulation data in the Y direction

[0071] As can be seen from the above, for tightly wound structures, the coupling coefficient is symmetrically distributed with the offset, reaches the highest peak at 0 offset, and the value decays rapidly after deviating from the center. The downward trend in the positive and negative offset directions is steep, and the whole structure is extremely sensitive to positional offset.

[0072] Sparse winding structure: The coupling coefficient also shows a symmetrical single-peak trend, with the peak value being significantly lower than that of the compact type. The curve changes gently across the entire offset range, the decay rate is slow, and the overall value is low with small fluctuations.

[0073] Gradient winding structure: The coupling coefficient decreases symmetrically and steadily with the offset, with the peak value between the dense and sparse types. The attenuation rate is uniform and there are no drastic changes. The overall change pattern is smooth and regular.

[0074] Non-uniform winding structure: The coupling coefficient shows a symmetrical low amplitude variation trend. Among the five structures, the overall value is the lowest, the variation with offset is the smallest, the curve is the flattest, and the offset sensitivity is the weakest.

[0075] Double-layer winding structure: The coupling coefficient shows a symmetrical trend, with the peak value second only to the tightly coupled structure. The attenuation rate is slower than that of the tightly coupled type. It can still maintain a relatively higher coupling coefficient under large offset. The overall trend combines high peak value with relatively good offset adaptability.

[0076] like Figure 19 As shown, it illustrates the simulation variation of the coupling coefficient in the Z direction for various winding methods.

[0077] The simulation data in the Z direction for each winding method are shown in Table 5.

[0078] Table 5 Simulation data in the Z direction

[0079] As shown above, the tightly wound structure has the highest coupling coefficient and the largest peak value among all structures when the offset is small. However, it also has the fastest decay rate, falling behind quickly with even a slightly larger offset, but it has an advantage under extremely small offsets.

[0080] Sparse winding structure: The coupling coefficient at the center position is relatively low, but the descent speed is the slowest and the curve is the flattest. It has the highest retention rate and the strongest anti-offset capability under large offset, making it the optimal choice for large offset conditions.

[0081] Gradient winding structure: The coupling coefficient remains stable and decreases linearly throughout the entire process, without drastic jumps or sharp drops, and the mid-section performance is stable. Its advantages are the most regular transmission characteristics and the least fluctuation, with no prominent peaks, but also no obvious weaknesses, resulting in strong stability.

[0082] Non-uniform winding structure: The overall coupling coefficient is relatively low, but the changes are gentle and the fluctuations are small, and the various indicators are relatively balanced.

[0083] Double-layer winding structure: The center peak value is high and the decay rate is slow, which can maintain a high coupling coefficient within a small to medium offset range.

[0084] Furthermore, Figures 20-24 The simulation cloud map of magnetic induction intensity for various winding methods is shown.

[0085] The coupling device provided in this embodiment of the invention uses Litz wire as the core conductive component. The Litz wire adopts a multi-strand enameled wire stranded structure, which has excellent resistance to mechanical fatigue and electromagnetic aging, and can significantly reduce the risk of single-strand wire breakage failure. Under the condition that the Litz wire does not break, the device can maintain long-term stable operation. Its service life and reliability are directly related to the mechanical integrity of the Litz wire, and it can achieve long-term reliable operation with a lifespan comparable to that of the Litz wire, and has the potential for stable adaptation in multiple scenarios.

[0086] This invention addresses the technical problems of existing technologies by disclosing a wireless charging coupling system for drones that is adaptable to various scenarios, has high transmission efficiency, and low loss, along with a coil winding method and the drone itself. Multiple coil winding methods can further expand the application of this coupling system. The receiving device is mounted on the drone's landing gear and includes a receiving coil and a soft magnet. The transmitting device includes a transmitting coil and a ferrite core. The transmitting device is coupled to the receiving coil via the transmitting coil. Optimized ferrite layout significantly reduces magnetic leakage, and the use of high-permeability materials significantly reduces hysteresis and eddy current losses, improving the stability and lifespan of the energy conversion. This coupling system has a small footprint, a large coupling coefficient, achieves efficient energy transmission, and is easy to install without affecting drone flight performance. For different scenarios, the winding method can be modified to better suit them, effectively improving the power density, heat dissipation performance, magnetic field adaptability, position tolerance, and anti-interference capability of the drone wireless charging system in various scenarios. Multiple coil winding methods can further expand the application of this coupling device.

[0087] Furthermore, this invention integrates the receiving coil with the landing gear, eliminating the need for additional space on the drone and reducing flight drag due to its close fit, resulting in strong spatial adaptability. Gradient winding and optimized magnetic field coverage with U-shaped ferrite ensure high coupling efficiency even with minimal drone landing position deviation. By switching winding methods, it can adapt to different usage requirements such as rapid power replenishment, outdoor inspection, and precise takeoff and landing, making it suitable for core scenarios of composite-wing drones, such as aerial surveying and inspection. This invention achieves precise adaptation across all scenarios through targeted combination designs of various coils; tight winding maximizes power density and ensures precise coupling, sparse winding optimizes heat dissipation and maintainability in harsh environments with high temperature and humidity, uneven winding precisely adjusts the magnetic field distribution, gradient winding expands the charging alignment range for composite-wing drone takeoff and landing, and double-layer coil winding meets power transmission and electromagnetic interference resistance requirements. These features address the shortcomings of existing technologies in terms of space constraints, environmental adaptability, customized adaptation, alignment tolerance, and high-power reliability, effectively improving the power density, heat dissipation performance, magnetic field adaptability, position tolerance, and anti-interference capabilities of the composite-wing drone wireless charging system in different scenarios. The optimized ferrite layout significantly reduces magnetic leakage. Combined with the application of high permeability materials, it significantly reduces hysteresis and eddy current losses, thereby improving the stability and lifespan of the device's energy conversion.

[0088] In the description of this invention, it should be understood that terms such as “length”, “width”, “upper”, “lower”, “front”, “rear”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inner”, and “outer” indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0089] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0090] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A wireless charging coupling system for unmanned aerial vehicles (UAVs), comprising a transmitting device and a receiving device, wherein the transmitting device includes a transmitting coil and the receiving device includes a receiving coil, characterized in that, It also includes a landing gear, the receiving device is mounted on the landing gear, and the transmitting device is located in the parking area; The transmitting device includes a ferrite, the ferrite includes a connecting part and a stepped symmetrical protruding structure extending outward from the end of the connecting part, the ferrite is U-shaped in general, and the transmitting coil is vertically wound in the U-shaped structure of the ferrite; The receiving device includes a soft magnet, the receiving coil is wound on both sides of the landing device, a rectangular gap is provided in the middle of the receiving coil, the soft magnet is disposed in the rectangular gap, and the lower part of the soft magnet is attached to the lower part of the rectangular gap.

2. The wireless charging coupling system for unmanned aerial vehicles according to claim 1, characterized in that, The landing gear includes a landing gear, which includes a horizontal support section, a Y-shaped transition connection section, and a strut section.

3. The wireless charging coupling system for unmanned aerial vehicles according to claim 2, characterized in that, The width of the Y-shaped transition connection section is W1, the width of the coverage area of ​​the transmitting coil is W2, W2 > W1; and the distance between the transmitting coil and the ferrite is h1, h1 > W2 / 3 - W2 / 2.

4. The wireless charging coupling system for unmanned aerial vehicles according to claim 2, characterized in that, The receiving coil is wound around the Y-shaped transition connection section and the strut section of the landing gear, and fits against the composite side of the inclined and vertical surfaces of the landing gear. The coil is wound from the outside to the inside starting from the lower side of the inclined surface. After winding a set number of turns clockwise or counterclockwise on the composite surface, it passes through the landing gear to the other side and is wound from the inside to the outside. The winding directions of the coils on both sides are opposite and the number of turns is the same.

5. A wireless charging coupling system for unmanned aerial vehicles according to claim 4, characterized in that, The plane of the receiving device forms an angle of 45°-90° with the plane of the transmitting device.

6. The wireless charging coupling system for unmanned aerial vehicles according to claim 1, characterized in that, The ferrite connection section is rectangular. The ferrite has a horizontal rectangle as its core and two ends with a symmetrical "double-step" protruding structure. A U-shaped groove is provided in the middle. The transmitting coil is vertically wound in the U-shaped groove. The side view of the transmitting coil is rectangular.

7. The wireless charging coupling system for unmanned aerial vehicles according to claim 1, characterized in that, The transmitting device also includes a heat dissipation layer, which is attached to the side of the ferrite away from the transmitting coil. The heat dissipation layer is made of graphene heat sink or aluminum alloy heat sink, and its thickness is 0.5-1mm.

8. A method for winding a coil in a wireless charging coupling system for unmanned aerial vehicles, characterized in that, Its application in the UAV wireless charging coupling system as described in any one of claims 2-7 includes at least one of the following winding methods: 1) Tight winding: The coil turns are tightly fitted together. The winding starts from the first side inside the ferrite U-shaped structure. After the first turn is completed, the second turn is tightly fitted to the first turn in the horizontal direction until the second side of the ferrite U-shaped structure is reached. The coil spacing is evenly distributed. The lower coil of the ferrite can be tightly wound or double-layered. At this time, the distance h1 between the lower end of the coil rectangle and the ferrite is greater than W2 / 2. 2) Sparse winding: The coil turns are left with uniform gaps. The winding starts from the first side inside the ferrite U-shaped structure. After the first turn is completed, the second turn is kept at a set interval from the first turn until the second side of the ferrite U-shaped structure is reached. The coil spacing is uniform. At this time, the distance h1 between the lower end of the coil rectangle and the ferrite is greater than W2 / 3. 3) Uneven winding: The coil has different turn spacing in different areas within the ferrite U-shaped structure. Starting from the first side of the ferrite U-shaped structure, after the first turn is completed, the second turn is spaced apart from the first turn and the spacing between each coil is different until the second side of the ferrite U-shaped structure. The overall distribution of the coil is uneven. 4) Gradient winding: The coil turn spacing changes in a gradient. The winding starts from the first side inside the ferrite U-shaped structure. After the first turn is completed, the second turn is spaced apart from the first turn. The coil turn spacing is the same in different areas, and the turn spacing is different between different areas, until the second side of the ferrite U-shaped structure is reached. 5) Double-layer coil winding: Two layers of coils are tightly wound, starting from the first side inside the ferrite U-shaped structure. After the first turn is wound, the second turn is close to the upper part of the first turn, and the third turn is close to the horizontal side of the first turn. The winding continues until the second side of the ferrite U-shaped structure is reached, and the coils are evenly distributed.

9. The coil winding method for a wireless charging coupling system for unmanned aerial vehicles according to claim 8, characterized in that, The coil winding method is applied to the transmitting coil; The transmitting device transmits electrical energy through coupling between the transmitting coil and the receiving coil of the receiving device. When high-frequency alternating current is applied to the transmitting coil, a high-frequency alternating magnetic field is generated. Under the coupling effect of the alternating magnetic field, the receiving coil generates an induced electromotive force and forms an induced current, thereby realizing the wireless transmission of electrical energy from the transmitting end to the receiving end.

10. A drone, comprising a main fuselage, characterized in that, It also includes a receiving device in the drone wireless charging coupling system as described in any one of claims 1-7, as well as a fixed-wing lift assembly and a vertical take-off and landing power assembly, wherein the drone is charged using the drone wireless charging coupling system as described in any one of claims 1-7.

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