Composite wing unmanned aerial vehicle electric field coupling charging device and system

Abstract

The application relates to an electric field coupling charging device and system of a compound wing unmanned plane, the electric field coupling charging device comprises a transmitting device, a receiving device and a shielding device, the transmitting device is arranged on a landing platform, and the receiving device and the shielding device are arranged at the bottom of the fuselage of the compound wing unmanned plane; the transmitting device comprises a first polar plate, a first insulating layer, a second polar plate and a second insulating layer from top to bottom; the receiving device comprises a third insulating layer, a third polar plate, a fourth insulating layer and a fourth polar plate from top to bottom; the first polar plate comprises a plurality of first transmitting units which are uniformly distributed and have the same area, the third polar plate comprises a plurality of second transmitting units which are uniformly distributed and have the same area, and the first transmitting units and the second transmitting units are arranged in a staggered mode; the third insulating layer, the third polar plate and the fourth insulating layer are of the same shape and are all solid planes, and the fourth polar plate is hollow.

Description

Technical Field

[0001] This invention belongs to the field of wireless charging technology for unmanned aerial vehicles (UAVs), specifically relating to an electric field coupling charging device and system for composite-wing UAVs. Background Technology

[0002] Compound-wing drones combine the high maneuverability, long endurance, and long flight range of fixed-wing drones with the vertical takeoff and landing and flexible hovering capabilities of multi-rotor drones. Currently, wireless charging technology in the drone field is mostly designed for multi-rotor drones. Due to the unique shape and landing accuracy issues of compound-wing drones, existing technologies cannot be directly applied to them. Furthermore, the drone's payload directly affects its endurance; therefore, the weight of the receiver should be minimized to meet lightweight requirements when designing the coupling device. Compound-wing drones have large wings, and their landing range is limited to a circular area with a diameter of one meter due to wind speed. Therefore, the designed coupling device should have a wide range of fault tolerance to ensure reliable wireless charging. To shorten the charging time of compound-wing drones, the designed coupling device should have high power transmission capabilities. Compound-wing drones contain precision electronic components; to ensure the safety of the drone equipment, the designed coupling device should have good electromagnetic shielding capabilities to prevent the internal components from being exposed to strong electric fields.

[0003] Existing magnetic field coupling wireless charging technology generates an alternating magnetic field near the magnetic field coupling device. Conductive materials in an alternating magnetic field will generate eddy currents and heat, resulting in additional losses and safety hazards. The magnetic field coupling device uses high-frequency Litz wire wound into coils, and in order to better constrain the magnetic circuit and obtain a larger coupling coefficient, the magnetic field coupling device inevitably uses ferrite materials, which makes it heavy. The alternating magnetic field generated by the coupling device can interfere with drones. Summary of the Invention

[0004] To address the aforementioned problems, the present invention provides an electric field coupling charging device and system for a composite wing unmanned aerial vehicle (UAV). In a first aspect, the electric field coupling charging device includes a transmitting device, a receiving device, and a shielding device. The transmitting device is located on a landing platform, and the receiving device and shielding device are located at the bottom of the composite wing UAV fuselage. The transmitting device, from top to bottom, includes a first electrode plate, a first insulating layer, a second electrode plate, and a second insulating layer. The receiving device, from top to bottom, includes a third insulating layer, a third electrode plate, a fourth insulating layer, and a fourth electrode plate.

[0005] The first electrode plate includes several uniformly distributed first emitting units with the same area, and the third electrode plate includes several uniformly distributed second emitting units with the same area. The first emitting units and the second emitting units are staggered. The third insulating layer, the third electrode plate, and the fourth insulating layer have the same shape and are all solid planes. The fourth electrode plate is hollow.

[0006] Optionally, the first electrode plate, the second electrode plate, the third electrode plate and the fourth electrode plate are all made of conductor materials, and the first insulating layer, the second insulating layer, the third insulating layer and the fourth insulating layer are all made of insulating materials.

[0007] The first electrode plate, the first insulating layer, the second electrode plate, and the second insulating layer are all made of flexible materials, allowing them to be bent and folded for easy transport and carrying. They can be unfolded into a flat surface when in use.

[0008] Optionally, the first electrode plate has a certain thickness and is the uppermost layer of the transmitting device, exhibiting a state that slightly protrudes from the plane of the transmitting device;

[0009] The fourth electrode plate has a certain thickness and is the bottom layer of the receiving device, which protrudes slightly from the bottom surface of the compound wing UAV.

[0010] In this invention, the first and fourth plates protrude from each other to form a unipolar contact connection that constitutes an energy transfer circuit. When the compound wing UAV lands, it ensures good contact between the first and fourth plates, obtains good power transmission capability, and improves the energy transfer capability of the coupling charging device.

[0011] Optionally, the shielding device is located above the receiving device, and its shape is determined by the shape of the composite-wing UAV, with an area larger than that of the receiving device. Preferably, the shielding device is formed by the carbon fiber fuselage of the composite-wing UAV and connected to the fourth electrode plate.

[0012] This invention only requires installing a receiving device on the underside of the compound-wing UAV's belly. The receiving device conforms to the original shape of the UAV, avoiding any impact on its aerodynamic parameters, while also meeting lightweight requirements. A recessed mounting groove can be provided on the underside of the UAV's belly for installing the receiving device, ensuring good contact between the receiving device and the transmitting device.

[0013] This invention proposes two specific transmitting and receiving devices. The first transmitting device is a checkerboard pattern, and the receiving device is circular. Optionally, the first electrode plate is square and includes several square first transmitting units, which are arranged in a matrix. In both the horizontal and vertical directions, there is a space between two adjacent first transmitting units, and the shape and area of ​​the space are the same as those of the first transmitting units.

[0014] Optionally, the second electrode plate is square and includes several square second transmitting units, which are arranged in a matrix. In both the horizontal and vertical directions, there is a gap between two adjacent second transmitting units, and the shape and area of ​​the gap are the same as those of the second transmitting units.

[0015] The first and second transmitting units are staggered and do not correspond to each other vertically, so as to avoid an excessively large area between the first and second plates, thereby reducing the value of the coupling capacitance C12 between them.

[0016] Optionally, the third insulating layer, the third electrode plate, and the fourth insulating layer are all circular, the fourth electrode plate is annular, the third insulating layer and the fourth insulating layer have the same area, the diameter of the third electrode plate is slightly smaller than the diameter of the third insulating layer, the inner diameter of the fourth electrode plate is slightly larger than the diameter of the third electrode plate, and the outer diameter of the fourth electrode plate is equal to the diameter of the third insulating layer.

[0017] In the second type, both the transmitting and receiving devices are square. Optionally, the first electrode plate is square and includes several strip-shaped first transmitting units, with equal spacing between adjacent first transmitting units, and one end of each first transmitting unit is electrically connected to the other end.

[0018] Optionally, the second electrode plate is square and has an area larger than that of the first electrode plate. The second electrode plate includes several square second transmitting units arranged in sequence. The second transmitting units are parallel to the first transmitting units, and there is a gap between two adjacent second transmitting units. A first transmitting unit is located directly above the gap, which avoids an excessively large facing area between the first and second electrode plates, thereby reducing the value of the coupling capacitance C12 between them. One end of each second transmitting unit is electrically connected to the others, and the other end is also electrically connected to the others.

[0019] The corresponding first and second insulating layers are also square, and their areas are not less than the area of ​​the second electrode plate.

[0020] Optionally, the third insulating layer, the third electrode plate, and the fourth insulating layer are all square, the fourth electrode plate is a square ring, the third insulating layer and the fourth insulating layer have the same area, the area of ​​the third electrode plate is slightly smaller than the area of ​​the third insulating layer, the empty area inside the fourth electrode plate is slightly larger than the area of ​​the third electrode plate, and the outer edge of the fourth electrode plate corresponds to the edge of the third insulating layer.

[0021] Secondly, the electric field coupling charging system for a composite-wing unmanned aerial vehicle (UAV) provided by the present invention includes the aforementioned electric field coupling charging device for a composite-wing UAV, a DC power supply, an inverter circuit, a resonant compensation network, and a rectifier circuit.

[0022] The inverter circuit is an asymmetrical half-bridge structure, the resonant compensation network adopts bilateral LC compensation, including compensation circuit one and compensation circuit two, the rectification stage adopts full-bridge rectification, and the negative terminal of the DC power supply is grounded.

[0023] The shielding device is connected to the ground at the negative terminal of the DC power supply through the inverter circuit, compensation circuit one, the second plate and the fourth plate, so that the shielding device always maintains zero potential, thereby protecting the internal components of the UAV from strong electric field interference.

[0024] To avoid exposing the drone to a strong electric field during charging, the coupling charging device prevents eddy currents and heating from occurring inside the conductor, even when conductive materials are present nearby. The drone can autonomously land on the launching device to replenish its power. Once fully charged, it enters standby mode or continues its mission, achieving fully unmanned and automated charging.

[0025] The present invention also provides a method for improving the fault tolerance capability of the coupling charging device, enabling the compound-wing UAV to achieve charging at any position of the launching device while ensuring that the coupling parameters remain stable. The method includes:

[0026] (1) Based on the shapes of the third electrode, the first emitting unit, and the second emitting unit, determine a parameter that can display the area relationship between the third electrode and the first emitting unit, and between the third electrode and the second emitting unit;

[0027] (2) The area of ​​the third plate facing the first plate is S. p1 The area of ​​the third plate facing the second plate is S. p2 In S p1 equals S p2 Then, determine the value of the parameter mentioned in step (1).

[0028] In the aforementioned coupling charging device, the capacitance between the third electrode plate and the first electrode plate is the first capacitor, and the capacitance between the third electrode plate and the second electrode plate is the second capacitor. Unexpectedly, the inventors discovered that the closer the values ​​of the first capacitor and the second capacitor are, the more stable the coupling charging device is, the more stable the coupling parameters are, and the stronger the fault tolerance capability for the third electrode is.

[0029] The ideal parallel plate capacitance is determined by the following formula:

[0030]

[0031] Where C is the capacitance, k is the electrostatic constant of the dielectric between the two plates, S is the area of ​​the two plates facing each other, d is the distance between the two plates, and ε is the dielectric constant of the dielectric between the two plates.

[0032] After the compound-wing UAV lands, the distance between the receiving and transmitting devices remains constant. Therefore, the coupling capacitance C is determined by the area S of the two plates facing each other. For the first and second capacitors to remain stable, the area of ​​the third plate facing the first plate must be equal to the area of ​​the third plate facing the second plate, regardless of the plate's position. The area of ​​the fourth electrode is much smaller than that of the third electrode and does not affect the areas of the third plate facing the first or second plates; therefore, the influence of the fourth electrode is not considered. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of the structure of an electric field coupling charging device for a composite wing unmanned aerial vehicle (UAV) according to Embodiment 1.

[0034] Figure 2 This is a schematic diagram of the compound-wing UAV in Example 1;

[0035] Figure 3 This is a schematic diagram of the electric field coupling charging system for the composite wing UAV in Example 1;

[0036] Figure 4 This is a schematic diagram showing the third electrode plate covering the first and second electrodes plate for different n values ​​in Example 1 (P1 is the first electrode plate and P2 is the second electrode plate in the diagram).

[0037] Figure 5 In Example 1 A schematic diagram showing the third plate covering the first and second plates (P3 in the diagram is the third plate, and r is the radius of the third plate).

[0038] Figure 6 In Example 1 A schematic diagram showing the third electrode plate covering the first and second electrodes.

[0039] Figure 7 In Example 1 A schematic diagram showing the third electrode plate covering the first and second electrodes.

[0040] Figure 8 In Example 1 A schematic diagram showing the third electrode plate covering the first and second electrodes.

[0041] Figure 9 This is a schematic diagram showing the third electrode plate covering the first and second electrodes plate for different n values ​​in Example 2.

[0042] In the attached diagram, 1-transmitting device, 11-first electrode plate, 12-first insulating layer, 13-second electrode plate, 14-second insulating layer, 2-receiving device, 21-third insulating layer, 22-third electrode plate, 23-fourth insulating layer, 24-fourth electrode plate, 3-shielding device, 4-first transmitting unit, 5-second transmitting unit. Detailed Implementation

[0043] Example 1

[0044] This embodiment provides an electric field coupling charging device for a composite-wing unmanned aerial vehicle, such as... Figures 1-2As shown, it includes a transmitter 1, a receiver 2, and a shielding device 3. The transmitter 1 is located on the landing platform, and the receiver 2 and the shielding device 3 are located at the bottom of the fuselage of the composite wing UAV. The transmitter 1 includes, from top to bottom, a first electrode plate 11, a first insulating layer 12, a second electrode plate 13, and a second insulating layer 14. The receiver 2 includes, from top to bottom, a third insulating layer 21, a third electrode plate 22, a fourth insulating layer 23, and a fourth electrode plate 24.

[0045] The first electrode plate 11 includes 18 uniformly distributed first launching units 4 with the same area, and the third electrode plate 22 includes 18 uniformly distributed second launching units 5 with the same area. The first launching units 4 and the second launching units 5 are staggered. The third insulating layer 21, the third electrode plate 22, and the fourth insulating layer 23 have the same shape and are all solid circles. The fourth electrode plate 24 is a hollow annulus. The number of first and second launching units can be appropriately increased or decreased according to the size of the compound wing UAV and the size of the platform or plane carrying the launching device.

[0046] The first electrode plate 11, the second electrode plate 13, the third electrode plate 22 and the fourth electrode plate 24 are all made of conductive materials, and the first insulating layer 12, the second insulating layer 14, the third insulating layer 21 and the fourth insulating layer 23 are all made of insulating materials; the first electrode plate 11, the first insulating layer 12, the second electrode plate 13 and the second insulating layer 14 are all made of flexible materials.

[0047] The first electrode plate 11 has a certain thickness and is the uppermost layer of the transmitting device, exhibiting a state that slightly protrudes from the plane of the transmitting device;

[0048] The fourth electrode plate 24 has a certain thickness and is the bottom layer of the receiving device, protruding slightly from the bottom surface of the compound wing UAV. The thickness of the first electrode plate is 0.1-1mm, and the thickness of the fourth electrode plate is 0.1-1mm.

[0049] The shielding device 3 is located above the receiving device 2. The shielding device 3 is made of the carbon fiber fuselage of the composite wing UAV and is connected to the fourth pole plate 24.

[0050] Both the first electrode plate 11 and the first transmitting unit 4 are square, and the 18 first transmitting units 4 are arranged in a matrix. In the horizontal and vertical directions, there is a space between two adjacent first transmitting units 4, and the shape and area of ​​the space are the same as those of the first transmitting unit 4.

[0051] Both the second electrode plate 13 and the second transmitting unit 5 are square, and the 18 second transmitting units 5 are arranged in a matrix. In both the horizontal and vertical directions, there is a gap between each pair of adjacent second transmitting units 5, and the shape and area of ​​the gap are the same as those of the second transmitting units 5. One end of each second transmitting unit is electrically connected to the others, and the other end is also electrically connected to the others.

[0052] The third insulating layer 21 and the fourth insulating layer 23 have the same area. The diameter of the third electrode plate 22 is slightly smaller than the diameter of the third insulating layer 21. The inner diameter of the fourth electrode plate 24 is slightly larger than the diameter of the third electrode plate 22. The outer diameter of the fourth electrode plate 24 is equal to the diameter of the third insulating layer 21.

[0053] The electric field coupling charging system for the composite wing UAV in this embodiment, such as Figure 3 As shown, it includes the aforementioned electric field coupling charging device for a composite-wing UAV, a DC power supply, an inverter circuit, a resonant compensation network, and a rectifier circuit.

[0054] The inverter circuit is an asymmetrical half-bridge structure, the resonant compensation network adopts bilateral LC compensation, including compensation circuit one and compensation circuit two, the rectifier circuit adopts full-bridge rectification, and the negative terminal of the DC power supply is grounded.

[0055] The shielding device is connected to the ground at the negative terminal of the DC power supply through the inverter circuit, compensation circuit one, the second plate and the fourth plate, so that the shielding device always maintains zero potential, thereby protecting the internal components of the UAV from strong electric field interference.

[0056] The input terminal of the inverter circuit is connected to a DC power supply, and the output terminal of the inverter circuit is connected to a compensation circuit. The first output terminal of the compensation circuit is connected to a first plate, and the second output terminal is connected to a second plate. A first insulating layer is provided between the first plate and the second plate.

[0057] The third electrode plate is connected to the first input terminal of the compensation circuit two. The fourth electrode plate and the shielding device are both connected to the second input terminal of the compensation circuit two. A fourth insulating layer is provided between the third electrode plate and the fourth electrode plate. A third insulating layer is provided between the third electrode plate and the shielding device. The output terminal of the compensation circuit two is connected to the input terminal of the rectifier circuit. The output terminal of the rectifier circuit is connected to the load.

[0058] The method for improving the fault tolerance capability of the coupling charging device in this embodiment includes:

[0059] (1) The diameter of the third plate is d, the side length of the first transmitting unit and the second transmitting unit are the same and a, and the parameter n is defined as d / a;

[0060] (2) The area of ​​the third plate facing the first plate is S. p1 The area of ​​the third plate facing the second plate is S. p2 In S p1 equals S p2 Then, determine the value of the parameter mentioned in step (1).

[0061] like Figure 4As shown, as n increases, new emission units will be covered by the third plate. Five critical values ​​are marked, and n is divided into four segments.

[0062] like Figure 5 As shown, When S1 is the approximate area of ​​the first emitting unit in the upper left corner covered by the third electrode P3, and S3 is the approximate area of ​​the second emitting unit directly above the third electrode P3, S1 and S3 are determined by the following formula:

[0063]

[0064] Where r is the radius of the third electrode;

[0065] S p1 and S p2 Determined by the following formula:

[0066]

[0067] When S p1 =S p2 When n is calculated, n = 1.735.

[0068] like Figure 6 As shown, When S1 is the approximate area of ​​the first emitting unit covered by the third electrode P3 in the upper left corner, and S2 is the approximate area of ​​the first emitting unit covered by the third electrode P3 in the upper right corner, S1 and S2 are determined by the following formula:

[0069]

[0070] S p1 and S p2 Determined by the following formula:

[0071]

[0072] When S p1 =S p2 When n is calculated, n = 3.125.

[0073] like Figure 7 As shown, When S1 is the area of ​​the first emitting unit covered by the third electrode P3 in the upper left corner, S2 is the approximate area of ​​the first emitting unit covered by the third electrode P3 directly above it, and S3 is the approximate area of ​​the second emitting unit covered by the third electrode P3 in the upper left corner. S1, S2, and S3 are determined by the following formula:

[0074]

[0075] Where r is the radius of the third electrode;

[0076] S p1 and S p2 Determined by the following formula:

[0077]

[0078] When S p1 =S p2 When n is calculated, there is no solution.

[0079] like Figure 8 As shown, When S1 is the approximate area of ​​the first transmitting unit covered by the third electrode P3 in the upper left corner, S2 is the approximate area of ​​the first transmitting unit covered by the third electrode P3 directly above it, and S3 is the approximate area of ​​the second transmitting unit covered by the third electrode P3 in the upper left corner. S1, S2, and S3 are determined by the following formula:

[0080]

[0081] Where r is the radius of the third electrode;

[0082] S p1 and S p2 Determined by the following formula:

[0083]

[0084] When S p1 =S p2 When n is calculated, n = 4.657.

[0085] The coupling charging devices corresponding to the three cases from which the value of n can be obtained are modeled and simulated in Maxwell 11 software, and the coupling capacitance between the first plate and the second plate is defined as C. 12 The coupling capacitance between the third plate and the first plate is C. M The coupling capacitance between the third plate and the first plate is C. 23 During the simulation, the value of the same capacitor will fluctuate to some extent. This fluctuation is represented by the rate of change. The rates of change for the three capacitors mentioned above are A... 12 A M and A 23 The more stable the coupling parameters of the coupling charging device, the smaller the rate of change. The rate of change A is determined by the following formula:

[0086]

[0087] Among them, C max and C min These represent the maximum and minimum values ​​of the same capacitor, respectively.

[0088] Table 1. Data on capacitance change rate under different n values.

[0089]

[0090] The coupling charging device provided in this embodiment, in Within this range, the dimensional design of the third, first, and second electrodes was studied, and this range can meet the practical applications of most compound-wing UAVs. For different ranges of n, suitable n values ​​can be obtained, as shown in the table above. At that time, C M and C 23 The rate of change is large, the coupling parameters are unstable, and the fault tolerance capability is low; At that time, the rate of change of each capacitor is less than 10%, and the fault tolerance capability is within an acceptable range; At that time, the rate of change of each capacitor was within 5%, the coupling parameters were stable, and the fault tolerance capability was high.

[0091] Example 2

[0092] This embodiment of the electric field coupling charging device and system for a composite wing UAV is the same as that in embodiment 1, except that it makes full use of the space under the fuselage. The receiving device is designed to be rectangular, and the transmitting device is also rectangular. The first electrode plate is rectangular and includes five strip-shaped first transmitting units. The spacing between two adjacent first transmitting units is equal. One end of each first transmitting unit is electrically connected to the other end.

[0093] The second electrode plate is rectangular and has an area larger than that of the first electrode plate. The second electrode plate includes six rectangular second transmitting units arranged in sequence. The second transmitting units are parallel to the first transmitting units, and there is a gap between two adjacent second transmitting units. A first transmitting unit is located directly above the gap.

[0094] The corresponding first and second insulating layers are also square, and their areas are not less than the area of ​​the second electrode plate.

[0095] The third insulating layer, the third electrode plate, and the fourth insulating layer are all rectangular, and the fourth electrode plate is a rectangular ring. The third and fourth insulating layers have the same area, the area of ​​the third electrode plate is slightly smaller than the area of ​​the third insulating layer, and the empty area inside the fourth electrode plate is slightly larger than the area of ​​the third electrode plate. The outer edge of the fourth electrode plate corresponds to the edge of the third insulating layer.

[0096] The method for improving the fault tolerance capability of the coupling charging device in this embodiment is as follows: Figure 9 As shown, it includes:

[0097] (1) The width of the second transmitting unit is L1, the width of the first transmitting unit is L2, the length of the third electrode plate is L3, and the width is W;

[0098] (2) The area of ​​the third plate facing the first plate is S. p1 The area of ​​the third plate facing the second plate is S. p2 In S p1 equals S p2 Then, determine the values ​​of W and L3 in step (1).

[0099] The first electrode plate is identical in the horizontal direction, and the second electrode plate is identical in the horizontal direction. In the vertical direction, the first and second electrode plates are arranged in an array, and the periodic distance of their repeating structure is L1+L2. If the length direction of the third electrode plate is parallel to the first electrode plate, and the width of the third electrode plate is W=L1+L2, then the third electrode plate will always cover one first transmitting unit and one second transmitting unit. This design is beneficial to the stability of the coupling device parameters.

[0100] Assuming L3 = n × W, investigate the effect of the value of n on the fault tolerance capability of the coupling device. When n takes different values, such as... Figure 9 As shown, the corresponding SP1 and SP2 cases are different, and will be discussed separately.

[0101] Let n * ≤n <n * +1, where n* is a positive integer. Assume the third plate moves vertically downwards from the top edge of the first plate, with a distance of y. Figure 9 As shown in the first two third electrodes, SP1 is determined by the following formula:

[0102]

[0103] SP2 is determined by the following formula:

[0104]

[0105] The range of n is:

[0106]

[0107] As can be seen from the above formula, when n is within the range of values ​​mentioned above, the third plate faces the area S directly when it enters and exits the first plate. P1 S P2 Both are functions related to y, meaning that in this case, the coupling capacitance of the coupling device changes with the position of the receiving plate.

[0108] When n = n*, such as Figure 9 The third electrode in the diagram is shown, directly opposite area S. P1 S P2 It is independent of y, as shown in the following formula:

[0109] S P1 =WL1n *

[0110] S P2 =WL2n *

[0111] Therefore, the optimal size of the third electrode plate is L3 = n × W, W = L1 + L2. When n is a positive integer, the fault tolerance capability of the coupling device is optimal. For example, n is 2, 3, 4, etc., depending on the actual needs of the coupling charging device and the compound wing UAV.

[0112] The length units in the above embodiments are all in mm, and the area units are all in mm. 2 .

Claims

1. A method for improving the fault-tolerant capability of an electric field-coupled charging device for a compound-wing unmanned aerial vehicle, characterized in that, include: (1) Based on the shapes of the third electrode, the first emitting unit, and the second emitting unit, determine a parameter that can display the area relationship between the third electrode and the first emitting unit, and between the third electrode and the second emitting unit; (2) The area of ​​the third plate facing the first plate is S. p1 The area of ​​the third plate facing the second plate is S. p2 In S p1 equals S p2 When, determine the value of the parameter mentioned in step (1); The electric field coupling charging device for the composite wing UAV includes a transmitting device, a receiving device, and a shielding device. The transmitting device is located on the landing platform, and the receiving device and the shielding device are located at the bottom of the composite wing UAV fuselage. The transmitting device includes, from top to bottom, a first electrode plate, a first insulating layer, a second electrode plate, and a second insulating layer. The receiving device includes, from top to bottom, a third insulating layer, a third electrode plate, a fourth insulating layer, and a fourth electrode plate. The first electrode plate includes several uniformly distributed first emitting units with the same area, and the third electrode plate includes several uniformly distributed second emitting units with the same area. The first emitting units and the second emitting units are staggered. The third insulating layer, the third electrode plate, and the fourth insulating layer have the same shape and are all solid planes. The fourth electrode plate is hollow. The first electrode plate is square and includes several square first transmitting units, which are arranged in a matrix. In both the horizontal and vertical directions, there is a gap between two adjacent first transmitting units, and the shape and area of ​​the gap are the same as those of the first transmitting units. The second electrode plate is square and includes several square second transmitting units, which are arranged in a matrix. In both the horizontal and vertical directions, there is a gap between two adjacent second transmitting units, and the shape and area of ​​the gap are the same as those of the second transmitting units. The first transmitting unit and the second transmitting unit are staggered and do not correspond to each other vertically. The third electrode plate is circular; In step (1), the parameter is n, and n = d / a, where the diameter of the third electrode plate is d, and the side lengths of the first transmitting unit and the second transmitting unit are the same and are a; In step (2), as n increases, new transmitting units will be covered by the third electrode plate, dividing n into 4 segments; when And S p1 =S p2 When n=1.735, we get n=1.735; when n=1.735, we get n=1.

735. And S p1 =S p2 When n=3.125; when And S p1 =S p2 When n has no solution; when And S p1 =S p2 At that time, we get n=4.657; The coupling capacitance between the first plate and the second plate is C. 12 The coupling capacitance between the third plate and the second plate is C. M The coupling capacitance between the third plate and the first plate is C. 23 Each of the above coupling capacitors will vary under different n values, C 12 C 23 C M The rates of change are respectively A 12 A M and A 23 The rate of change of the coupling capacitance is the proportion of the difference between the maximum and minimum values ​​of the coupling capacitance in the maximum value of the coupling capacitance. For a coupling capacitor, compare the rate of change under different n values; select an n value that ensures the rate of change of each coupling capacitor is no greater than 5% as the final value of the parameter, so that the coupling parameter is stable and the fault tolerance capability is improved.

2. The method for fault-tolerant bit capability according to claim 1, characterized in that, The first electrode plate, the second electrode plate, the third electrode plate, and the fourth electrode plate are all made of conductive materials, and the first insulating layer, the second insulating layer, the third insulating layer, and the fourth insulating layer are all made of insulating materials; the first electrode plate, the first insulating layer, the second electrode plate, and the second insulating layer are all made of flexible materials.

3. The method for fault-tolerant bit capability according to claim 2, characterized in that, The first electrode plate has a certain thickness and is the uppermost layer of the transmitting device, exhibiting a state that slightly protrudes from the plane of the transmitting device; The fourth electrode plate has a certain thickness and is the bottom layer of the receiving device, which protrudes slightly from the bottom surface of the compound wing UAV.

4. The method for fault-tolerant bit capability according to claim 1, characterized in that, The shielding device is located above the receiving device, and the area of ​​the shielding device is larger than the area of ​​the receiving device.

5. The method for fault-tolerant bit capability according to claim 3, characterized in that, Both the third and fourth insulating layers are circular, and the fourth electrode plate is annular. The third and fourth insulating layers have the same area. The diameter of the third electrode plate is slightly smaller than that of the third insulating layer, the inner diameter of the fourth electrode plate is slightly larger than that of the third electrode plate, and the outer diameter of the fourth electrode plate is equal to that of the third insulating layer.

6. A field-coupled charging system for a composite-wing unmanned aerial vehicle, characterized in that, Includes the method for improving the fault tolerance capability of the electric field coupling charging device for compound wing unmanned aerial vehicles as described in any one of claims 1-5, a DC power supply, an inverter circuit, a resonant compensation network, and a rectifier circuit; The inverter circuit is an asymmetrical half-bridge structure, the resonant compensation network adopts bilateral LC compensation, including compensation circuit one and compensation circuit two, the rectification stage adopts full-bridge rectification, and the negative terminal of the DC power supply is grounded. The shielding device is connected to the ground at the negative terminal of the DC power supply through the inverter circuit, compensation circuit one, the second plate and the fourth plate, so that the shielding device always maintains zero potential, thereby protecting the internal components of the UAV from strong electric field interference.

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