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

Abstract

The invention relates to a composite wing unmanned aerial vehicle electric field coupling charging device and system, 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 a composite wing unmanned aerial vehicle body; the transmitting device sequentially 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 sequentially 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 manner; the third insulating layer, the third polar plate and the fourth insulating layer are the same in shape and are solid planes, and the fourth polar plate is hollow.

Description

Technical Field

[0001] The present invention belongs to the technical field of wireless charging of unmanned aerial vehicles, and in particular relates to an electric field coupling charging device and system for a composite wing unmanned aerial vehicle. Background Art

[0002] Composite wing UAVs combine the advantages of high maneuverability, long endurance, and long flight distance of fixed-wing UAVs with the advantages of vertical take-off and landing and flexible hovering of multi-rotor UAVs. At present, wireless charging technology in the field of UAVs is mostly aimed at multi-rotor UAVs. Due to the specific shape and landing accuracy of composite wing UAVs, the existing technology cannot be directly applied to composite wing UAVs, and the load of UAVs directly affects their endurance. Therefore, when designing the coupling device, the weight of the receiving side should be reduced as much as possible to meet the lightweight requirements. Composite wing UAVs have large wings. Affected by the wind speed in the environment, the landing range is a circular area with a diameter of one meter. Therefore, the designed coupling device should have a wide range of misalignment tolerance to ensure reliable wireless charging. In order to shorten the charging time of composite wing UAVs, the designed coupling device should have a higher power transmission capacity. There are precision electronic devices inside composite wing UAVs. In order to ensure the safety of UAV equipment, the designed coupling device should have a good electromagnetic shielding capability to prevent the internal devices of the UAV from being exposed to a strong electric field environment.

[0003] With the existing magnetic field coupling wireless charging technology, an alternating magnetic field is generated near the magnetic field coupling device. The conductor material in the alternating magnetic field will generate eddy currents and heat, resulting in additional losses and safety hazards. The magnetic field coupling device is wound into a coil using high-frequency Litz wire, 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 are heavy. The alternating magnetic field generated by the coupling device will interfere with the drone. Summary of the invention

[0004] In view of the above problems, the present invention provides an electric field coupling charging device and system for a composite wing UAV. In a first aspect, 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 composite wing UAV; the transmitting device comprises a first electrode plate, a first insulating layer, a second electrode plate and a second insulating layer from top to bottom; the receiving device comprises a third insulating layer, a third electrode plate, a fourth insulating layer and a fourth electrode plate from top to bottom;

[0005] The first electrode plate includes a plurality of first emitting units that are evenly distributed and have the same area, the third electrode plate includes a plurality of second emitting units that are evenly distributed and have the same area, and 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, and 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 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;

[0007] The first electrode plate, the first insulating layer, the second electrode plate and the second insulating layer are all made of flexible materials, which allow bending and folding, so as to facilitate transportation and carrying, and can be unfolded into a plane when in use.

[0008] Optionally, the first electrode plate has a certain thickness and is the uppermost layer of the emitting device, and is slightly protruding from the plane of the emitting device;

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

[0010] In the present invention, the first electrode plate and the fourth electrode plate are protruded toward each other to form a unipolar contact connection to constitute an energy transmission circuit. When the composite wing UAV lands, the first electrode plate is ensured to be in good contact with the fourth electrode plate, thereby obtaining good power transmission capability and improving the energy transmission capability of the coupled charging device.

[0011] Optionally, the shielding device is arranged above the receiving device, the shape of the shielding device is determined according to the shape of the composite wing UAV, and the area of ​​the shielding device is larger than the area of ​​the receiving device. Preferably, the shielding device is served by the carbon fiber fuselage of the composite wing UAV and is connected to the fourth electrode plate.

[0012] The present invention only needs to install the receiving device on the bottom surface of the belly of the composite wing UAV, and the receiving device conforms to the original shape of the UAV, avoids affecting the aerodynamic parameter index of the UAV, and meets the lightweight requirements. The bottom surface of the UAV belly can be provided with a mounting groove recessed into the body for installing the receiving device to ensure good contact between the receiving device and the transmitting device.

[0013] The present invention proposes the following two specific transmitting devices and receiving devices. The first transmitting device is in a chessboard shape, and the receiving device is in a circular shape. Optionally, the first electrode plate is square and includes a plurality of square first transmitting units, and the plurality of first transmitting units are arranged in a matrix; in the horizontal and vertical directions, there is a vacancy between two adjacent first transmitting units, and the shape and area of ​​the vacancy are the same as those of the first transmitting unit.

[0014] Optionally, the second electrode plate is square and includes a plurality of square second emitting units, and the plurality of second emitting units are arranged in a matrix; in the horizontal and vertical directions, there is a vacancy between two adjacent second emitting units, and the shape and area of ​​the vacancy are the same as those of the second emitting unit;

[0015] The first transmitting unit and the second transmitting unit are staggered and do not correspond to each other vertically, so as to avoid an excessively large facing area between the first electrode plate and the second electrode plate, thereby reducing the value of the coupling capacitor C12 therebetween.

[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] The second type of transmitting device and receiving device are both square. Optionally, the first electrode plate is square and includes a plurality of first strip-shaped transmitting units, the spacing between two adjacent first transmitting units is equal, and one end of each first transmitting unit is electrically connected to each other, and the other end is also electrically connected to each other.

[0018] Optionally, the second plate is square and has an area greater than that of the first plate; the second plate includes a plurality of square second emitting units arranged in sequence, the second emitting units are parallel to the first emitting units, there is a gap between two adjacent second emitting units, and a first emitting unit corresponds to the gap directly above, so as to avoid an excessively large facing area between the first plate and the second plate, thereby reducing the value of the coupling capacitance C12 between the two. One end of each second emitting unit is electrically connected to each other, and the other end is also electrically connected to each other.

[0019] The corresponding first insulating layer and second insulating layer 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 vacant 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] In a second aspect, the electric field coupling charging system for a composite wing UAV provided by the present invention comprises the above-mentioned 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 asymmetric half-bridge structure. The resonant compensation network adopts bilateral LC compensation, including compensation circuit 1 and compensation circuit 2. The rectification link adopts full-bridge rectification, and the negative end of the DC power supply is grounded.

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

[0024] The drone is prevented from being exposed to a strong electric field when charging. Even if there is a conductor material near the coupling charging device, eddy current heating will not be generated inside the conductor. The drone can recharge its energy by landing on the launch device autonomously. After the energy is recharged, it will enter a standby state or continue to perform its mission. The charging process is unmanned and automated.

[0025] The present invention also provides a method for improving the misalignment tolerance of the coupling charging device, so that the composite wing UAV can be charged when landing at any position of the launching device, and the coupling parameters are ensured to remain stable. The method includes:

[0026] (1) determining a parameter that can show the area size relationship between the third electrode and the first emitting unit, and between the third electrode and the second emitting unit according to the shapes of the third electrode, the first emitting unit, and the second emitting unit;

[0027] (2) The area facing the third plate and the first plate is S p1 , the area facing the third plate and the second plate is S p2 , in S p1 Equal to S p2 When , determine the value of the parameter described in step (1).

[0028] In the coupling charging device, the capacitance between the third electrode plate and the first electrode plate is the first capacitance, and the capacitance between the third electrode plate and the second electrode plate is the second capacitance. The inventor unexpectedly discovered that the closer the values ​​of the first capacitance and the second capacitance are, the more stable the coupling charging device is, the more stable the coupling parameters are, and the stronger the tolerance to misalignment of the third electrode is.

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

[0030]

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

[0032] After the composite wing UAV lands, the distance between the receiving device and the transmitting device remains unchanged, and the coupling capacitance C is determined by the area S of the two plates facing each other. If the first capacitance and the second capacitance are to remain stable, it is required that when the third plate is in different positions, the area of ​​the third plate facing the first plate is equal to the area of ​​the third plate facing the second plate. The area of ​​the fourth electrode is much smaller than that of the third electrode, and does not affect the area of ​​the third plate facing the first plate or the area of ​​the third plate facing the second plate. Therefore, the influence of the fourth electrode is not considered. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a schematic structural diagram of an electric field coupling charging device for a composite wing UAV according to Example 1;

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

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

[0036] Figure 4 Schematic diagram of the third electrode plate covering the first electrode plate and the second electrode plate when different n values ​​are in Example 1 (P 1 is the first plate, P 2 is the second electrode);

[0037] Figure 5 For Example 1 Schematic diagram of the third electrode plate covering the first electrode plate and the second electrode plate (P in the figure) 3 is the third electrode plate, r is the radius of the third electrode plate);

[0038] Figure 6 For Example 1 A schematic diagram showing that the third electrode plate covers the first electrode plate and the second electrode plate;

[0039] Figure 7 For Example 1 A schematic diagram showing that the third electrode plate covers the first electrode plate and the second electrode plate;

[0040] Figure 8 For Example 1 A schematic diagram showing that the third electrode plate covers the first electrode plate and the second electrode plate;

[0041] Fig. 9 Schematic diagram of the third electrode plate covering the first electrode plate and the second electrode plate when the n value is different in Example 2.

[0042] In the accompanying drawings, 1-transmitting device, 11-first pole plate, 12-first insulating layer, 13-second pole plate, 14-second insulating layer, 2-receiving device, 21-third insulating layer, 22-third pole plate, 23-fourth insulating layer, 24-fourth pole plate, 3-shielding device, 4-first transmitting unit, 5-second transmitting unit. DETAILED DESCRIPTION

[0043] Example 1

[0044] A composite wing UAV electric field coupling charging device of this embodiment, such as Figure 1-Figure 2As shown, it includes a transmitting device 1, a receiving device 2 and a shielding device 3, the transmitting device 1 is arranged on the landing platform, and the receiving device 2 and the shielding device 3 are arranged at the bottom of the fuselage of the composite wing UAV; the transmitting device 1 includes a first electrode 11, a first insulating layer 12, a second electrode 13 and a second insulating layer 14 from top to bottom; the receiving device 2 includes a third insulating layer 21, a third electrode 22, a fourth insulating layer 23 and a fourth electrode 24 from top to bottom;

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

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

[0047] The first electrode plate 11 has a certain thickness and is the uppermost layer of the launch device, and is slightly protruding from the plane of the launch device;

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

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

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

[0051] The second electrode plate 13 and the second emitting unit 5 are both square, and the 18 second emitting units 5 are arranged in a matrix; in the horizontal and vertical directions, there is an empty space between two adjacent second emitting units 5, and the shape and area of ​​the empty space are the same as those of the second emitting unit 5. One end of each second emitting unit is electrically connected to each other, and the other end is also electrically connected to each other.

[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 , and 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 of the composite wing UAV of this embodiment is as follows: Figure 3 As shown, it includes the above-mentioned composite wing UAV electric field coupling charging device, DC power supply, inverter circuit, resonant compensation network and rectifier circuit,

[0054] The inverter circuit is an asymmetric half-bridge structure, the resonant compensation network adopts bilateral LC compensation, including compensation circuit 1 and compensation circuit 2, the rectifier circuit adopts full-bridge rectification, and the negative end of the DC power supply is grounded;

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

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

[0057] The third electrode plate is connected to the first input end of the compensation circuit 2, the fourth electrode plate and the shielding device are both connected to the second input end of the compensation circuit 2, 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 end of the compensation circuit 2 is connected to the input end of the rectifier circuit, and the output end of the rectifier circuit is connected to the load.

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

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

[0060] (2) The area facing the third plate and the first plate is S p1 , the area facing the third plate and the second plate is S p2 , in S p1 Equal to S p2 When , determine the value of the parameter described in step (1).

[0061] like Figure 4As shown, as n increases, new emission units will be covered by the third plate, 5 critical values ​​are marked, and n is divided into 4 segments.

[0062] like Figure 5 As shown, When S 1 The third electrode P 3 The approximate area of ​​the first emitting unit covering the upper left corner, S 3 The third electrode P 3 The approximate area of ​​the second transmitting unit directly above, S 1 and S 3 Determined by the following formula:

[0063]

[0064] Wherein, 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 , we calculate n=1.735.

[0068] like Figure 6 As shown, When S 1 The third electrode P 3 The approximate area of ​​the first emitting unit covering the upper left, S 2 The third electrode P 3 The approximate area of ​​the first emitting unit directly above the cover, S 1 and S 2 Determined by the following formula:

[0069]

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

[0071]

[0072] When S p1 =S p2 , we calculate n=3.125.

[0073] like Figure 7 As shown, When S 1 The third electrode P 3The area of ​​the first transmitting unit covering the upper left corner, S 2 The third electrode P 3 The approximate area of ​​the first emitting unit directly above the cover, S 3 The third electrode P 3 The approximate area of ​​the second emission unit covering the upper left, S 1 , S 2 and S 3 Determined by the following formula:

[0074]

[0075] Wherein, 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 , the calculation shows that n has no solution.

[0079] like Figure 8 As shown, When S 1 The third electrode P 3 The approximate area of ​​the first emitting unit covering the upper left, S 2 The third electrode P 3 The approximate area of ​​the first emitting unit directly above the cover, S 3 The third electrode P 3 The approximate area of ​​the second emission unit covering the upper left, S 1 , S 2 and S 3 Determined by the following formula:

[0080]

[0081] Wherein, 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 , we calculated n = 4.657.

[0085] The coupling charging devices corresponding to the three situations in which the n value 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 a certain extent, and the fluctuation is represented by the rate of change. The rates of change of the above three capacitors are A 12 , A M and A 23 The more stable the coupling parameters of the coupling charging device are, the smaller the rate of change is. The rate of change A is determined by the following formula:

[0086]

[0087] Among them, C max and C min are the maximum and minimum values ​​of the same capacitance respectively.

[0088] Table 1 Capacitance change rate data table under different n

[0089]

[0090] The coupling charging device provided in this embodiment has The size design of the third electrode, the first electrode and the second electrode is studied within the range of , which can meet the practical application of most composite wing UAVs. For different value ranges of n, the appropriate n value can be obtained. As can be seen from the above table, When C M and C 23 The rate of change is large, the coupling parameters are unstable, and the misalignment tolerance is low; When , the change rate of each capacitor is less than 10%, and the misalignment tolerance is within an acceptable range; When , the change rate of each capacitance is within 5%, the coupling parameters are stable, and the misalignment tolerance is high.

[0091] Example 2

[0092] A composite wing UAV electric field coupling charging device and system of the present embodiment is the same as that of embodiment 1, except that the belly space is fully utilized, the receiving device is designed to be rectangular, the transmitting device is correspondingly also rectangular, the first electrode plate is rectangular, and includes 5 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 each other, and the other end is also electrically connected to each other.

[0093] The second electrode plate is rectangular and has an area larger than that of the first electrode plate; the second electrode plate includes 6 rectangular second emitting units arranged in sequence, the second emitting units are parallel to the first emitting units, there is a gap between two adjacent second emitting units, and a first emitting unit corresponds to the space directly above the gap.

[0094] The corresponding first insulating layer and second insulating layer 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, the fourth electrode plate is a rectangular 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 vacant 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.

[0096] The method of improving the misalignment tolerance capability of the coupling charging device in this embodiment is as follows: Fig. 9 As shown, including:

[0097] (1) The width of the second transmitting unit is L 1 , the width of the first transmitting unit is L 2 , the length of the third plate is L 3 , width is W;

[0098] (2) The area facing the third plate and the first plate is S p1 , the area facing the third plate and the second plate is S p2 , in S p1 Equal to S p2 When determining W and L in step (1) 3 The numerical value of .

[0099] The first electrode plate itself is completely identical in the horizontal direction, and the second electrode plate itself is completely identical in the horizontal direction. In the vertical direction, the first electrode plate and the second electrode plate are both arranged in an array, and the periodic distance of the repeated structure is L. 1 +L 2 , if the length direction of the third electrode plate is parallel to the first electrode plate, the width of the third electrode plate W = L 1 +L 2 , the third electrode plate always covers a first transmitting unit and a second transmitting unit. Such a design is conducive to the stability of the coupling device parameters.

[0100] Assume L 3 =n×W, explore the effect of n on the misalignment tolerance of the coupling device. When n takes different values, such as Fig. 9 As shown, the corresponding SP 1 , SP 2 Each situation is different and should be discussed separately.

[0101] Assume n * ≤n <n * +1, where n* is a positive integer. Assume that the third electrode starts from the upper edge of the first electrode and moves downward in the vertical direction, and the moving distance is y, such as Fig. 9 The first two third electrodes are shown in the figure, then SP 1 Determined by the following formula:

[0102]

[0103] SP 2 Determined by the following formula:

[0104]

[0105] The selection range of n is:

[0106]

[0107] From the above formula, it can be seen that when n is within the above range, the third plate faces an area S when crossing into and out of the first plate. P1 , S P2 They are all functions related to y, that is, in this case, the coupling capacitance value of the coupling device changes with the change of the position of the receiving plate.

[0108] When n = n*, Fig. 9 As shown in the third electrode, the area S P1 , S P2 It is independent of y, as shown below:

[0109] S P1 =WL 1 n *

[0110] S P2 =WL 2 n *

[0111] Therefore, the optimal size of the third plate is L 3 =n×W, W=L 1 +L 2 When n is a positive integer, the coupling device has the best tolerance to misalignment. For example, n is 2, 3, 4, etc., depending on the actual needs of the coupling charging device and the composite wing UAV.

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

Claims

1. An electric field coupling charging device for a composite wing UAV, characterized in that: It includes a transmitting device, a receiving device and a shielding device, wherein 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 composite wing UAV; the transmitting device includes a first electrode plate, a first insulating layer, a second electrode plate and a second insulating layer from top to bottom; the receiving device includes a third insulating layer, a third electrode plate, a fourth insulating layer and a fourth electrode plate from top to bottom; The first electrode plate includes a plurality of first emitting units that are evenly distributed and have the same area, the third electrode plate includes a plurality of second emitting units that are evenly distributed and have the same area, and 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, and the fourth electrode plate is hollow.

2. The electric field coupling charging device for composite wing UAV according to claim 1 is characterized in that: The materials of the first electrode plate, the second electrode plate, the third electrode plate and the fourth electrode plate are all conductive materials, and the materials of the first insulating layer, the second insulating layer, the third insulating layer and the fourth insulating layer are all insulating materials; the first electrode plate, the first insulating layer, the second electrode plate and the second insulating layer are all flexible materials.

3. The electric field coupling charging device for composite wing UAV according to claim 2 is characterized in that: The first electrode plate has a certain thickness and is the uppermost layer of the launch device, and is slightly protruding from the plane of the launch device; The fourth electrode plate has a certain thickness and is the lowest layer of the receiving device, and is slightly protruding from the bottom surface of the composite wing UAV.

4. The electric field coupling charging device for composite wing UAV according to claim 1 is characterized in that: The shielding device is arranged above the receiving device, and the area of ​​the shielding device is larger than the area of ​​the receiving device.

5. The electric field coupling charging device for composite wing UAV according to claim 3 is characterized in that: The first electrode plate is square and includes a plurality of square first emitting units, which are arranged in a matrix; in the horizontal and vertical directions, there is a vacancy between two adjacent first emitting units, and the shape and area of ​​the vacancy are the same as those of the first emitting units; The second electrode plate is square and includes a plurality of square second emitting units, which are arranged in a matrix. In the horizontal and vertical directions, there is a vacancy between two adjacent second emitting units, and the shape and area of ​​the vacancy are the same as those of the second emitting unit. The first emitting unit and the second emitting unit are staggered and do not correspond to each other up and down.

6. The electric field coupling charging device for composite wing UAV according to claim 5 is characterized in that: 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.

7. The electric field coupling charging device for composite wing UAV according to claim 3 is characterized in that: The first electrode plate is square and includes a plurality of first emitting units in a strip shape, the distance between two adjacent first emitting units is equal, one end of each first emitting unit is electrically connected to each other, and the other end is also electrically connected to each other; The second electrode plate is square and has an area greater than that of the first electrode plate; the second electrode plate includes a plurality of square second emitting units arranged in sequence, the second emitting units are parallel to the first emitting units, there is a gap between two adjacent second emitting units, and a first emitting unit corresponds directly above the gap; one end of each second emitting unit is electrically connected to each other, and the other end is also electrically connected to each other.

8. The electric field coupling charging device for composite wing UAV according to claim 7 is characterized in that: The third insulating layer, the third electrode plate and the fourth insulating layer are all square in shape, the fourth electrode plate is in the shape of 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 that of the third insulating layer, the vacant area inside the fourth electrode plate is slightly larger than that of the third electrode plate, and the outer edge of the fourth electrode plate corresponds to the edge of the third insulating layer.

9. A composite wing UAV electric field coupling charging system, characterized in that: It comprises the electric field coupling charging device of the composite wing UAV according to any one of claims 1 to 8, a DC power supply, an inverter circuit, a resonant compensation network and a rectifier circuit; The inverter circuit is an asymmetric half-bridge structure. The resonant compensation network adopts bilateral LC compensation, including compensation circuit 1 and compensation circuit 2. The rectification link adopts full-bridge rectification, and the negative end of the DC power supply is grounded. The shielding device is connected to the ground at the negative end of the DC power supply through the inverter circuit, the first compensation circuit, the second electrode plate and the fourth electrode plate, so that the shielding device always maintains zero potential, thereby protecting the internal devices of the drone from strong electric field interference.

10. A method for improving the misalignment tolerance of the coupling charging device according to any one of claims 1 to 8, characterized in that: include: (1) determining a parameter that can show the area size relationship between the third electrode and the first emitting unit, and between the third electrode and the second emitting unit according to the shapes of the third electrode, the first emitting unit, and the second emitting unit; (2) The area facing the third plate and the first plate is S p1 , the area facing the third plate and the second plate is S p2 , in S p1 Equal to S p2 When , determine the value of the parameter described in step (1).

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