Lightweight magnetic coupling mechanism for unmanned aerial vehicle wireless charging system and parameter optimization method thereof

Abstract

The invention discloses a lightweight magnetic coupling mechanism for a wireless charging system of an unmanned aerial vehicle and a parameter optimization method of the lightweight magnetic coupling mechanism, and the lightweight magnetic coupling mechanism comprises a transmitting end magnetic core, a transmitting coil, a receiving end magnetic core and a receiving coil of the coupling mechanism and optimized parameters of all parts of the coupling mechanism, so that the lower weight of the receiving end and the higher energy transmission effect are realized. In the design of the coupling mechanism, a novel soft magnetic composite material magnetic core is adopted to replace a traditional ferrite magnetic core to be used as a receiving end magnetic core. A similar closed magnetic core structure is designed, a magnetic field path is restrained, and mutual inductance of the coupling mechanism is improved. The structure, size and optimization parameters of a coupling mechanism are designed by considering the demand characteristics of light weight, structural special shape and high performance of the unmanned aerial vehicle, and target optimization is carried out by adopting a simulated annealing particle swarm optimization algorithm. According to the design, the length of the receiving end magnetic core and the receiving coil are optimized, the weight of the airborne side wireless charging device is reduced, the airborne side wireless charging device is suitable for unmanned aerial vehicles with different shapes, additional wind resistance is not increased, and the airborne side wireless charging device has wide applicability and popularization value.

Description

Technical Field

[0001] The present invention relates to the field of wireless power transmission, and in particular to a lightweight magnetic coupling mechanism for a wireless charging system of an unmanned aerial vehicle and a parameter optimization method thereof. Background Art

[0002] Currently, drones have been widely used in various industries, but the problems of battery life and power supply have not been effectively improved. Wireless charging technology can extend the battery life of drones, reduce operational risks, and reduce labor costs, and has broad application prospects. However, due to the special structure of drones and their limited carrying capacity, the lightweight and structural adaptability problems of the magnetic coupling mechanism have been caused. In the design of the magnetic coupling mechanism of drones, the airborne side is required to avoid the use of materials such as ferrite and aluminum plates as much as possible. This requirement reduces the ability to restrain the magnetic field, thereby further increasing the design difficulty of the magnetic coupling mechanism. Designing a lightweight, highly structurally adaptable and high-performance magnetic coupling mechanism is one of the key research issues in drone wireless charging systems.

[0003] At present, in order to solve the problems of lightweight, structural adaptability and high performance of the magnetic coupling mechanism of the wireless charging system of drones, many academic papers and patents have been studied and corresponding solutions have been proposed, such as:

[0004] 1. In the patent with application number 202311451005.1 and titled "Receiver for wireless charging of drones and lightweight processing method thereof", it is proposed that the receiving unit is composed of two parts with the same shape and structure, in which the ferrite core is designed as a cylindrical shape with a hollow center and a receiving coil wrapped around the outside. The size of the core is optimized to reduce the weight of the receiving end and improve system performance. However, the vibration and turbulence of drones during take-off and landing make the hollow ferrite structure easy to break and the magnetic coupling mechanism easy to be damaged.

[0005] 2. In the patent with application number 202311251059.3 and titled "A UAV Wireless Charging Coupling Mechanism and Charging System", it is proposed to design a three-sided transmitting coil structure in the transmitting end of the coupling mechanism. The coils are connected in series, and the receiving coil is a solenoid coil, which is wound on the pin of the drone. This structure does not increase the weight of the receiving end, and the transmitting coil is designed to ensure the coupling coefficient and energy transmission efficiency between the coils. But at the same time, the problem brought by the three-dimensional groove structure of the transmitting coil is that the accuracy of the drone's fixed-point landing is required, and it needs to land in the groove.

[0006] 3. In the patent with the application number 202411652581.7 and the title "A UAV Magnetic Coupling Resonant Wireless Power Transmission System", it is proposed to use a double-D coil at the transmitting end of the coupling mechanism and a U-shaped ferrite magnetic core at the receiving end to guide the magnetic flux. The receiving-end coil is wound around the UAV pin to improve the structural adaptability of the coupling mechanism. And through the PWM phase-shifted closed-loop control method, the output voltage of the inverter module is changed to achieve high-performance transmission. However, this method introduces additional circuits and electronic devices in the circuit, increasing the weight of the receiving end.

[0007] In summary, the existing methods have problems such as poor structural adaptability, poor lightweight performance, and poor magnetic core performance at the receiving end. Therefore, there is an urgent need for a design method for the magnetic coupling mechanism to solve the problems of lightweight, structural adaptability, and high performance of the magnetic coupling mechanism in the wireless charging system. Summary of the Invention

[0008] In view of this, the present invention provides a lightweight magnetic coupling mechanism for a UAV wireless charging system and its parameter optimization method. The present invention uses a new type of soft magnetic composite material as the receiving-end magnetic core, effectively improving the mutual inductance of the magnetic coupling mechanism. This material has the characteristics of light density and not being easily impacted and broken, avoiding the use of traditional ferrite magnetic cores, which have a large density, a large load on the airborne side, and are fragile under vibration, and are not suitable for use as the airborne-side magnetic core of UAVs. The receiving-end coil uses a lightweight solenoid coil, and the magnetic flux path of the magnetic coupling mechanism is analyzed. The simulated annealing particle swarm optimization algorithm is used to optimize the parameters of the magnetic coupling mechanism, reducing the system weight, increasing the mutual inductance, and reducing the system loss.

[0009] According to the first aspect of the embodiments of the present application, a lightweight magnetic coupling mechanism for a UAV wireless charging system is provided, including: a transmitting end, a transmitting-end compensation capacitor, a receiving end, and a receiving-end compensation capacitor. The receiving end is connected to the receiving-end compensation capacitor, and the transmitting end is connected to the transmitting-end compensation capacitor; the transmitting end includes a transmitting coil and a transmitting-end magnetic core; the receiving end includes a receiving coil and a receiving-end magnetic core;

[0010] Optionally, the transmitting end and the receiving end together form a magnetic coupling mechanism.

[0011] Further, the transmitting-end magnetic core is a ferrite magnetic core with a U-shaped appearance, and the convex part is placed horizontally upward; the receiving-end magnetic core is a cylindrical new type of soft magnetic composite material magnetic core with an inverted U-shaped appearance, and the convex part is downward, and is placed inside the UAV pin; the transmitting-end magnetic core and the receiving-end magnetic core are combined to form a magnetic flux path with a small air gap.

[0012] Further, the transmitting coil is a DD-type planar coil; the receiving coil is a solenoid coil, which is placed horizontally and is located above the transmitting coil.

[0013] Further, the transmitting coil is nested outside the protruding part of the transmitting core; the receiving coil is wound outside the receiving core, and the drone pin is located between the receiving coil and the receiving core.

[0014] Further, the receiving coil can pick up the horizontal magnetic field generated by the transmitting coil, and the similar closed path formed by the transmitting core and the receiving core guides the main magnetic field through the receiving coil.

[0015] Further, the diameter d m of the receiving core is 14 mm, and the maximum value of the length l m is 200 mm.

[0016] Further, the magnetic flux density in the receiving coil is lower than the saturation magnetic flux density of the receiving core.

[0017] According to the second aspect of the embodiments of the present application, a method for optimizing the parameters of a lightweight magnetic coupling mechanism for a drone wireless charging system is provided, including:

[0018] Determine the size range of the magnetic coupling mechanism according to the size and power requirements of the drone, and obtain the capacitance value at resonance by using simulation software;

[0019] Determine the optimization parameters and optimization objectives, and obtain 300 optimization parameters and corresponding target values through simulation by the simulation software as the initial values of the algorithm;

[0020] Adopt the simulated annealing particle swarm algorithm to optimize the parameters of the magnetic coupling mechanism;

[0021] Determine the final parameters according to the importance degree of the optimization objectives from the Pareto front solution set, obtain the values of the transmitting end compensation capacitor and the receiving end compensation capacitor by using the simulation software, simulate and output the transmission efficiency, output power and system loss by using the circuit simulation software, and judge whether the initial requirements of the system are met.

[0022] Further, the optimization parameters for optimizing the parameters of the coupling mechanism are the core length l m , the number of turns N sol of the receiving coil, and the length l sol of the receiving coil.

[0023] Further, the optimization objectives for optimizing the parameters of the coupling mechanism are the receiving end weight m, the system figure of merit FOM, and the core loss P core .

[0024] Further, the core loss P core includes the core loss of the receiving coil and the core loss of the transmitting coil.

[0025] Further, the optimization result of the simulated annealing particle swarm algorithm for the magnetic coupling mechanism is that the number of turns N of the receiving coil sol is 31 turns, the length l of the magnetic core m is 118 mm, and the length l of the receiving coil sol is 2139 mm.

[0026] The beneficial effects of the present invention are as follows:

[0027] The present invention proposes to improve the transmission efficiency of the system and reduce the weight of the receiving end by using a soft magnetic composite material magnetic core and designing a magnetic coupling mechanism and optimizing its parameters. This solution does not add additional electronic devices and effectively reduces the load on the airborne side. The solenoid coil is used on the airborne side, which not only has a light weight, small wind resistance, but also has a low installation difficulty and good structural adaptability to the UAV. The present invention uses the simulated annealing particle swarm algorithm to optimize the parameters of the magnetic coupling mechanism, and finds the final solution among the three optimization objectives of magnetic core loss, receiving end weight and system efficiency, providing a complete set of lightweight design and optimization solutions for the magnetic coupling mechanism. Description of the Drawings

[0028] Figure 1 is the structural diagram of the magnetic coupling mechanism with a novel soft magnetic material magnetic core of the present invention;

[0029] Figure 2 is the structural diagram of the magnetic cores at the transmitting end and the receiving end of the magnetic coupling mechanism of the present invention;

[0030] Figure 3 is the structure and parameter diagram of the airborne side receiving end of the magnetic coupling mechanism with a novel soft magnetic material magnetic core of the present invention;

[0031] Figure 4 is the structural diagram of the transmitting end of the magnetic coupling mechanism of the present invention;

[0032] Figure 5 is the magnetic flux path diagram of the magnetic coupling mechanism with a novel soft magnetic material magnetic core of the present invention;

[0033] Figure 6 is the schematic diagram of the magnetic flux density distribution of the magnetic coupling mechanism with a novel soft magnetic material magnetic core of the present invention;

[0034] Figure 7 is the schematic diagram of the equivalent circuit of the S-S resonant compensation topology network of the present invention;

[0035] Figure 8 is the schematic diagram of the relationship between the magnetic flux density and the magnetic core loss of the soft magnetic composite material magnetic core of the present invention;

[0036] Figure 9 is the flow chart of the simulated annealing particle swarm algorithm for optimizing the parameters of the magnetic coupling mechanism of the present invention;

[0037] Figure 10This is a schematic diagram of the hardware circuit connection of the system of the present invention.

[0038] In the figure: the pin 1 of the drone, the transmitting core 2, the transmitting coil 3, the receiving core 4, and the receiving coil 5. Specific embodiments

[0039] To make the above objects, features, and advantages of the present invention more obvious and understandable, the following will describe in detail the specific embodiments of the present invention with reference to the accompanying drawings of the specification. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative work shall fall within the protection scope of the present invention.

[0040] A lightweight magnetic coupling mechanism for a drone wireless charging system provided by the present invention is as shown in the appendix Figure 1 and includes a transmitting coil 3, a transmitting core 2, a receiving coil 5, and a receiving core 4. This structure uses the magnetic coupling resonance method for wireless power transmission and calculates the compensation capacitance using an S-S type compensation circuit. The transmitting coil 3 is connected to the transmitting end compensation capacitor, and the receiving coil 5 is connected to the receiving end capacitor. The transmitting core 4 is a new type of nanocrystalline soft magnetic composite material, with a cylindrical shape like an inverted U, and the protruding part is downward. The transmitting core 2 is PC40 ferrite, with a shape similar to a U, and the protruding part is placed horizontally upward. As can be seen from the appendix Figure 2 , the front view of the core structure is a similar closed core structure, and the air gap between the two cores is small, which can greatly reduce magnetic field leakage. This core structure guides the magnetic flux path, reduces the gap between the cores at the receiving end and the transmitting end, and ensures that most of the magnetic flux passes through the magnetic coupling mechanism coil via the core.

[0041] The transmitting end structure of the magnetic coupling mechanism is as shown in the appendix Figure 3 and includes a transmitting coil 3 and a transmitting core 2. The transmitting coil is a DD-type planar coil, nested outside the protruding part of the transmitting core to reduce magnetic leakage and generate a more uniform magnetic field. The appendix Figure 4 shows the receiving end structure of the magnetic coupling mechanism. The receiving end includes a receiving coil 5 and a receiving core 4. The receiving core 4 is placed inside the pin 1 of the drone. The receiving coil 5 is a solenoid coil, placed horizontally, wound outside the pin 1 of the drone, and the drone pin 1 is in the middle between the receiving coil 5 and the receiving core 4. In the figure, l m is the length of the core of the new material, d m is the diameter of the drone pin, d sol is the inner diameter of the solenoid coil, and l sol is the length of the solenoid coil. The receiving end structure of the present invention is beneficial to reducing wind resistance, without adding additional devices, thereby reducing the overall weight of the device.

[0042] AppendixFigure 5 It shows the magnetic field distribution of the coupling structure. The current directions in the two sets of coils of the magnetic coupling resonator transmitting coil 3 are opposite. The current in the left coil is in the clockwise direction, and the current direction in the right coil is in the counterclockwise direction. The magnetic fields generated by the two rectangular coils form a closed magnetic field. A large number of horizontal magnetic fluxes are formed above the transmitting coil. The receiving coil 5 picks up the horizontal magnetic field generated by the transmitting coil for receiving the horizontal magnetic field, thereby generating an alternating current. Due to the good magnetic permeability of the ferrite and the new soft magnetic composite material, the magnetic core of the magnetic coupling mechanism guides the circulation path of the magnetic flux, forming a closed magnetic circuit between the transmitting coil and the receiving coil. The magnetic field distribution of the coupling mechanism can be obtained through ANSYS Maxwell simulation, as shown in the appendix Figure 6 As shown. The magnetic flux density of this type of closed coupling structure shows the characteristic of being stronger along the magnetic core path, with less magnetic field diverging into the surrounding air, and the magnetic field being concentrated in the coupling structure. In the present invention, the maximum value of the magnetic flux density is inside the magnetic core, with a value of 30 mT, and the magnetic field intensity at a distance of 45 cm from the magnetic core at the receiving end is 26 μT.

[0043] The parameter settings of the magnetic coupling mechanism are shown in Table 1.

[0044]

[0045] The magnetic coupling mechanism adopts an S-S type compensation circuit, which has less parasitic resistance loss and the power factor is not affected by the load resistance. The topological circuit of the coupling structure of the wireless charging system is as shown in Figure 7 As shown, R p and R r are the equivalent resistances at the transmitting end and the receiving end respectively, R l is the equivalent resistance at the port of the rectifier circuit, including the load equivalent resistance and the equivalent internal resistance of the rectifier circuit. U p and U r are the AC input voltage and the AC output voltage of the coupling mechanism respectively, C p and C r are the compensation capacitors, L p and L r are the self-inductances of the transmitting coil and the receiving coil respectively, and M pr is the mutual inductance between the transmitting coil and the receiving coil.

[0046] According to Kirchhoff's voltage law, the mesh equations of the circuit are listed.

[0047]

[0048] The compensation capacitors C p and C r are set according to the system resonance conditions.

[0049]

[0050] System transmission efficiency

[0051]

[0052] A lightweight magnetic coupling structure parameter optimization method for an unmanned aerial vehicle wireless charging system provided by the present invention adopts a simulated annealing particle swarm optimization algorithm. Analyzing the parameter data of the coupling mechanism shows that the characteristics of the coupling mechanism are restricted by multiple parameters, and its optimization goal is multi-objective, which is a non-linear, multi-modal and high-dimensional problem. Therefore, a particle algorithm is adopted as the optimization algorithm in this paper, and on this basis, the simulated annealing algorithm is introduced to improve the problem that the inertia weight is too small at the beginning and too large in the later stage of the PSO algorithm.

[0053] Assume that the target temperature of the simulated annealing algorithm (SA) is T, and the temperature is updated using the set annealing rate after each operation. α is the annealing rate, and when T(x1) drops to the specified temperature, the operation stops. The inertia weight of the PSO algorithm is controlled by the SA algorithm, and the inertia weight is cooled down once after each iteration.

[0054] T(x1) = αT(x2) (6)

[0055] ω(2) = αω(1) (7)

[0056] 1. Set the objective function:

[0057] 1) System figure of merit FOM

[0058] FOM is used to evaluate the performance of the system. Improving the system figure of merit (FOM) can improve the transmission efficiency of the system. The FOM expression of the wireless charging coupling mechanism is:

[0059]

[0060] The system frequency is 85 kHz, M pr is the mutual inductance of the coupling mechanism, which is greatly affected by the structure of the coupling mechanism and is greatly affected by the structure and parameters of the receiving core and the receiving coil.

[0061] 2) Receiver weight

[0062] The weight of the receiver is mainly generated by the core and the coil, including the core weight and the coil weight. Reducing the core length and the number of coil turns is beneficial to reducing the total mass of the receiver.

[0063] 3) System loss

[0064] It is necessary to reduce the core loss and device loss. The core loss of the new soft magnetic composite material is obtained through testing, as shown in the appendix Figure 8As shown. The device loss is related to the input and output currents of the system. Reducing the system current can reduce the device loss. The core loss is related to the system frequency and current. Select a parameter solution with a smaller system circuit and a smaller core loss that meets the conditions in the optimization results.

[0065] The objective function of the system is as follows:

[0066]

[0067] 2. Set the optimization variables

[0068] Design the core length l m , the number of turns N of the solenoid coil sol , the length l of the solenoid coil sol are the optimization variables, as shown in the following formula:

[0069] X = [x1, x2, x3] = [l m , N sol , l sol (10)

[0070] The optimization of the system parameters is restricted by the constraint conditions. The constraint conditions of the magnetic coupling mechanism are shown in Table 2.

[0071]

[0072] The application of the simulated annealing particle swarm optimization algorithm to the parameter optimization problem of the magnetic coupling mechanism designed in the present invention. The optimization process flow chart is as Figure 9 shown. After the algorithm optimization, a Pareto front solution set is obtained. According to the importance degree of the optimization objectives of the present invention, on the premise that the output power is higher than 100W, the output efficiency of the system is improved, and lightweight is the most important factor in the optimization. Select a suitable solution from the Pareto front solution set to obtain the optimization result. The optimized core length is 118mm, and the number of turns of the coil is 31 turns.

[0073] Perform circuit simulation on the above coupling mechanism and parameters, and build a hardware circuit. Figure 10 is the circuit diagram of the wireless charging system. In the system resonance compensation topology circuit, U in is a DC voltage source. The DC voltage source is connected to the transmitting part of the coupling mechanism through a full-bridge inverter circuit composed of 4 MOSFETS and 4 diodes. The coupling mechanism is composed of a series compensation circuit, a primary circuit, and a secondary circuit. C p and C r constitute the S-S compensation capacitor. L p , L r are the self-inductances of the primary circuit and the secondary circuit respectively. M prIt is the mutual inductance between the primary coil and the secondary coil. Energy is transferred from the transmitting coil of the coupling mechanism to the receiving coil. After passing through the receiving-end compensation circuit, an alternating current is generated, and the current I r After passing through the rectification circuit formed by 4 rectifier diodes, it supplies power to the equivalent load R o The capacitor C at the transmitting end in and the capacitor C at the receiving end o can stabilize the voltage in the corresponding structure and improve the stability of the system. Experiments were carried out using this circuit. The system parameters and some experimental results are shown in Table 3. The output power of the system is 185.01W, meeting the required output requirement of 100W. The load of the magnetic coupling mechanism is 15Ω, within the equivalent load range of the UAV battery, and the weight of the receiving end is only 68.33g.

[0074] Table 3: Parameters of the 85kHz system hardware experimental platform and some experimental results

[0075]

[0076] Table 4 shows the comparison results of the key data before and after the optimization of the coupling mechanism. It can be seen from the table that the device loss and core loss are significantly reduced, and the system efficiency is increased from 79.5% to 83%. The input current and output current after optimization are reduced, which is beneficial to reducing the device loss and core loss.

[0077] Table 4: Comparison of parameter values before and after the optimization of the coupling mechanism

[0078]

[0079] The present invention adopts a new type of soft magnetic composite material, which is applied to the receiving end to improve the system coupling ability. A coupling mechanism structure suitable for nested cores is designed, and the simulated annealing particle swarm algorithm is used to optimize multiple optimization objectives, thereby obtaining a set of coupling mechanism system design and optimization methods and lightweight solutions.

[0080] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that the technical solutions of the present invention can be modified or equivalently replaced without departing from the purpose and scope of the technical solutions of the present invention, and they should all be covered within the scope of the claims of the present invention.

Claims

1. A lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle, characterized in that: include: A transmitting end, a transmitting end compensation capacitor, a receiving end, a receiving end compensation capacitor; the receiving end is connected to the receiving end compensation capacitor, and the transmitting end is connected to the transmitting end compensation capacitor; the transmitting end includes a transmitting coil and a transmitting end magnetic core; the receiving end includes a receiving coil and a receiving end magnetic core.

2. The lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle according to claim 1, characterized in that: The transmitting end and the receiving end together form a magnetic coupling mechanism.

3. The lightweight magnetic coupling mechanism for the wireless charging system of an unmanned aerial vehicle according to claim 2, characterized in that: The transmitting end magnetic core is a ferrite magnetic core with a U-shaped shape, and the protruding part is placed horizontally with the protrusion facing upward; the receiving end magnetic core is a cylindrical new soft magnetic composite material magnetic core with a shape similar to an inverted U-shape, and the protruding part is placed downward inside the drone pin; the transmitting end magnetic core and the receiving end magnetic core are combined to form a magnetic flux path with a small air gap.

4. The lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle according to claim 2, characterized in that: The transmitting coil is a DD-type planar coil; the receiving coil is a solenoid coil, which is placed horizontally and located above the transmitting coil.

5. The lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle according to claim 4, characterized in that: The transmitting coil is nested outside the protruding part of the transmitting end magnetic core; the receiving coil is wound outside the receiving end magnetic core, and the drone pin is located between the receiving coil and the receiving end magnetic core.

6. The lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle according to claim 4, characterized in that: The receiving coil can pick up the horizontal magnetic field generated by the transmitting coil, and the quasi-closed path formed by the transmitting end magnetic core and the receiving end magnetic core guides the main magnetic field to pass through the receiving coil.

7. The lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle according to claim 1, characterized in that: The receiving end magnetic core diameter d m The inner diameter of the receiving coil is 14 mm. sol is 20mm.

8. The lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle according to claim 1, characterized in that: The magnetic flux density in the receiving coil is lower than the saturation magnetic flux density of the receiving end magnetic core, and the saturation magnetic flux density of the receiving end magnetic core is greater than 0.4 T at room temperature and below 100 kHz.

9. A method for optimizing parameters of a lightweight magnetic coupling mechanism for a wireless charging system of an unmanned aerial vehicle, characterized in that: include: Determine the size range of the magnetic coupling mechanism based on the size and power requirements of the drone, and use simulation software to obtain the capacitance value at resonance; Determine the optimization parameters and optimization targets, and obtain 300 optimization parameters and corresponding target values ​​through simulation software as the initial values ​​of the algorithm; The simulated annealing particle swarm algorithm is used to optimize the parameters of the magnetic coupling mechanism; The final parameters are determined from the Pareto front solution set according to the importance of the optimization target. The values ​​of the transmitter compensation capacitor and the receiver compensation capacitor are obtained through simulation software. The transmission efficiency, output power and system loss are simulated and output using circuit simulation software to determine whether the initial system requirements are met.

10. The lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle according to claim 9, characterized in that: The optimization parameter of the coupling mechanism optimization parameter is the core length l m 、N turns of the receiving coil sol , receiving end coil length l sol .

11. The lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle according to claim 9, characterized in that: The optimization objectives of the coupling mechanism optimization parameters are the receiving end weight m, the system factor FOM, and the system loss P core .

12. The lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle according to claim 11, characterized in that: The system loss P core Includes device loss, core loss and coil loss.

13. The lightweight magnetic coupling mechanism for a wireless charging system for an unmanned aerial vehicle according to claim 9, characterized in that: The optimization result of the simulated annealing particle swarm algorithm for the magnetic coupling mechanism is: the number of turns of the receiving end coil N sol 31 turns, core length l m is 118mm, the receiving end coil length l sol It is 2139mm.

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