Charging system and charging method for aircraft

Abstract

The invention discloses a charging system and a charging method for an aircraft. The self-adaptive battery equalization module is integrated in the aircraft energy storage module and is matched with the transmitting end resonant coupling module and the energy scheduling control module which are arranged on the ground charging station, so that deep integration of an electric energy transmission link is realized through modular topology reconstruction. Wherein a multi-channel active equalization topology is embedded in the self-adaptive battery equalization module, and a dynamic charge redistribution technology based on a switched capacitor array is adopted to realize single voltage deviation control in a battery pack. According to the system, a bidirectional magnetic resonance coupling technology is added on the basis of a traditional physical contact type charging interface, so that an adaptive charging protocol can be triggered without mechanical alignment after an aircraft lands on a base, cross-air-gap energy transmission is realized through high-frequency inversion and resonance compensation, the energy conversion efficiency of the system and the reliability of the charging process are successfully and remarkably improved, and the charging efficiency is improved. And an all-weather autonomous energy supply solution is provided for mobile platforms such as an unmanned aerial vehicle cluster.

Description

Technical Field

[0001] The present application relates to the field of aircraft charging technology, specifically to a charging system and charging method for aircraft, and is particularly suitable for an autonomous charging base station device and an energy transmission control method for electric vertical take-off and landing aircraft. Background Art

[0002] Currently, the mainstream technologies for autonomously charging drones via base stations fall into three categories. The first is mechanical battery swapping, which uses a robotic arm or rail system to automatically swap batteries, relying on precise mechanical structures for rapid recharging. The second is point-to-point contact charging, where the drone lands on a charging station and precisely connects the drone to the platform through physical contact points. The third is laser charging, which uses a high-energy laser beam emitted from the ground to remotely illuminate the drone's photovoltaic panels, converting light energy directly into electricity. However, each of these technologies faces application bottlenecks.

[0003] 1. Mechanical battery replacement technology has the following shortcomings:

[0004] 1) Low reliability of the mechanical structure: Frequent plugging and unplugging causes wear on the battery clips and guide rails, which can easily lead to safety hazards such as positioning deviation after long-term use;

[0005] 2) Limited environmental adaptability: On uneven terrain, the robot arm used to replace batteries is easily disturbed by vibrations, making it difficult to perform battery replacement operations stably.

[0006] 3) High maintenance complexity: Consumable parts need to be replaced regularly, and the need for coordinated battery replacement among multiple machines requires reliance on complex scheduling algorithms.

[0007] 2. The following deficiencies exist in contact charging technology:

[0008] 1) Docking accuracy requirements are stringent: Relying on high-precision visual / electromagnetic guidance systems, any deviation in the drone’s landing posture can easily lead to charging failure;

[0009] 2) Insufficient contact durability: Oxidative corrosion of metal contacts caused by environmental factors increases contact resistance, leading to energy loss and overheating risks;

[0010] 3) Poor applicability in adverse climates: Rainy and snowy weather can easily lead to contact insulation failure, posing a risk of short circuit or leakage.

[0011] 3. Laser charging technology has the following shortcomings:

[0012] 1) Unstable energy transmission efficiency: Atmospheric turbulence, rain and fog and other environments cause laser scattering and attenuation, and the actual conversion efficiency drops significantly;

[0013] 2) Radiation safety management is complex: High-power lasers must be strictly restricted in their use scenarios, posing a potential risk of accidental injury to personnel or equipment;

[0014] 3) High overall cost: Laser emitters and high-efficiency photovoltaic modules are expensive and require supporting heat dissipation and tracking systems. Summary of the Invention

[0015] To solve the above problems, the present application provides a charging system and a charging method for an aircraft.

[0016] According to a first aspect of the present application, the present application provides a charging system for an aircraft, characterized by comprising a charging base station and an aircraft:

[0017] The charging base station includes a power supply module, an energy scheduling control module and a first resonant coupling module;

[0018] The power supply module is used to provide stable constant voltage DC power;

[0019] The energy scheduling control module is electrically connected to the power supply module and is used to generate an optimal energy distribution strategy according to the load power demand of the aircraft and output DC power with matching power;

[0020] The first resonant coupling module is electrically connected to the energy scheduling control module and is used to convert direct current into high-frequency alternating current through electromagnetic resonance to facilitate wireless transmission;

[0021] The aircraft includes a second resonant coupling module, a contact charging interface, a synchronous boost topology module, a battery energy management module, an adaptive balanced charging module and an energy storage module;

[0022] The second resonant coupling module is used to sense the high-frequency alternating current generated by the first resonant coupling module through resonant coupling when the aircraft approaches the charging base station, and to generate the DC voltage required for the aircraft to perform wireless charging through AC-DC conversion;

[0023] The contact charging interface is used to obtain direct current by physical contact with the power supply module through a Type-C interface electrical connection;

[0024] The synchronous boost topology module is electrically connected to the contact charging interface and is used to perform DC-DC topology boosting of direct current through synchronous rectification technology;

[0025] The battery energy management module is electrically connected to the second resonant coupling module and the synchronous boost topology module, and is used to control the power switch timing of the second resonant coupling module and the synchronous boost topology module to select the power supply channel;

[0026] The adaptive balanced charging module is electrically connected to the battery energy management module, and is used to obtain electric energy from the selected power supply channel and perform balanced charging for the energy storage module.

[0027] According to a second aspect of the present application, the present application provides a charging method for an aircraft, comprising:

[0028] The energy scheduling control step includes sampling the current in the charging base station circuit and predicting the aircraft's load power demand based on the linear relationship between voltage and current. Based on the prediction results, the operating mode is dynamically adjusted to achieve optimal matching of the energy allocation strategy and control the output power to match the DC power.

[0029] The magnetic coupling resonant rectification step includes converting direct current into high-frequency alternating current by electromagnetic resonance, and generating the direct current voltage required for wireless charging of the aircraft by inducing the high-frequency alternating current through resonant coupling and performing AC-DC conversion;

[0030] The contact power supply synchronous boosting step includes the aircraft obtaining direct current from the charging base station through a physical interface, and performing a DC-DC topology boosting of the direct current through synchronous rectification technology;

[0031] Battery energy management steps, including selecting power supply channels for direct current obtained wirelessly and direct current obtained through physical contact;

[0032] The adaptive balanced charging step includes obtaining electric energy from the selected power supply channel and performing balanced charging for the aircraft.

[0033] The beneficial effects of this application are:

[0034] This solution systematically overcomes the technical barriers of traditional charging solutions in terms of mechanical losses, environmental adaptability, and energy efficiency through the organic integration of multi-physics collaborative design and intelligent control technologies. To address the adaptability limitations of mechanical battery swapping systems in complex terrain, an innovative dual-mode architecture combines magnetic resonance wireless power supply with intelligent contact charging. This architecture achieves contactless energy transmission through adaptive electromagnetic field control technology, significantly reducing reliance on precision mechanical structures and effectively avoiding safety hazards caused by contact oxidation and positioning deviation. The energy transmission system deeply integrates high-frequency resonance and synchronous rectification technologies to maintain efficient energy conversion over a wide load range. Combined with active balancing management and intelligent temperature control strategies, a complete energy quality assurance system is established. This solution significantly enhances the sustained operational capabilities of drones in complex scenarios such as field surveys and emergency rescue. By reducing operation and maintenance costs and improving charging reliability, it provides an all-weather, multi-scenario smart energy solution for long-duration missions of industrial-grade unmanned equipment, marking a significant breakthrough in the environmentally adaptive development of autonomous power supply technology for mobile platforms. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 A schematic diagram of the structure of an existing charging system for aircraft;

[0036] Figure 2 This is a schematic structural diagram of a charging system for an aircraft in one embodiment of the present application;

[0037] Figure 3 A flowchart of an existing charging method for aircraft is provided;

[0038] Figure 4 This is a flowchart of a charging method for an aircraft in one embodiment of the present application;

[0039] Figure 5 This is a schematic diagram of the program operation flow of the energy scheduling control module in one embodiment of the present application;

[0040] Figure 6 This is a schematic diagram of the program operation flow of the battery energy management module in one embodiment of the present application;

[0041] Figure 7 This is a schematic structural diagram of an adaptive balanced charging module in one embodiment of the present application;

[0042] Figure 8 This is a physical schematic diagram of a charging system for an aircraft in one embodiment of the present application. DETAILED DESCRIPTION

[0043] The present application will be further described in detail below through specific implementation methods in conjunction with the accompanying drawings.

[0044] The present application provides a charging system for an aircraft, characterized by comprising a charging base station and an aircraft.

[0045] Please refer to Figure 2 The present application discloses a charging system for aircraft, which includes a power supply module 21, an energy scheduling control module 22, a first resonant coupling module 23, a second resonant coupling module 24, a battery energy management module 25, a contact charging interface 26, a synchronous boost topology module 27, an adaptive balanced charging module 28, and an energy storage module 29, which are described below.

[0046] The charging base station includes a power supply module 21 , an energy scheduling control module 22 and a first resonant coupling module 23 .

[0047] The energy scheduling control module 22 is electrically connected to the power supply module 21 and is used to generate an optimal energy allocation strategy based on the aircraft's load power requirements and output DC power to match the power. For example, the energy scheduling control module 22 and the power supply module 21 are electrically connected using a 12V DC power supply. A sampling resistor is connected in series with the power supply line to convert current into voltage. A high-frequency ADC captures voltage data in real time, dynamically calculating the load power and energy requirements using Ohm's law to generate an optimal energy allocation strategy and output DC power to match the power requirements.

[0048] The first resonant coupling module 23 is electrically connected to the energy scheduling control module 22 and is configured to convert direct current (DC) power into high-frequency alternating current (AC) power via electromagnetic resonance for wireless transmission. For example, the first resonant coupling module 23 is located in a charging base station within an aircraft charging system and is electrically connected to the energy scheduling control module 22. It converts DC power into high-frequency AC power, driving the transmitting coil into a resonant state, and converting the DC power into high-frequency AC power via electromagnetic resonance for wireless transmission.

[0049] The aircraft includes a second resonant coupling module 24 , a contact charging interface 26 , a synchronous boost topology module 27 , a battery energy management module 25 , an adaptive balanced charging module 28 and an energy storage module 29 .

[0050] The second resonant coupling module 24 is used to sense the high-frequency AC power generated by the first resonant coupling module 23 when the aircraft approaches the charging base station through resonant coupling, and to generate the DC voltage required for the aircraft to perform wireless charging through AC-DC conversion. For example, the second resonant coupling module 24 is located at the drone end of the aircraft charging system. When the aircraft approaches the charging base station, it senses the high-frequency AC power generated by the first resonant coupling module 23 through resonant coupling, and to generate the DC voltage required for the aircraft to perform wireless charging through AC-DC conversion. The transmission efficiency is 80-85%.

[0051] The contact charging interface 26 is used to obtain 5V / 3A DC power through physical contact with the power supply module 21 using a Type-C interface electrical connection.

[0052] The synchronous boost module 27 is connected to the contactless charging port 26 and is used to boost the DC power supply using synchronous rectification technology. For example, the synchronous boost module 27 uses a 5V / 3A DC power input. Based on the synchronous rectification Boost architecture, high-frequency PWM control and MOSFET complementary drive technology are used to boost the DC power supply using a DC-DC topology, achieving an energy conversion efficiency of 90-94%.

[0053] The battery energy management module 25 is electrically connected to the second resonant coupling module 24 and the synchronous boost topology module 27, and is used to control the power switching timing of the second resonant coupling module 24 and the synchronous boost topology module 27 to select the power supply channel. For example, the battery energy management module 25 uses the MCU chip's multiple synchronous ADC channels for parallel analog-to-digital conversion sampling to monitor and compare the input voltage and current parameters of the contact-type power supply synchronous boost module and the magnetic coupling resonant rectifier module in real time. Based on the power calculation results, the intelligent switching logic is triggered to dynamically switch to the optimal power supply channel with higher charging efficiency.

[0054] The adaptive balanced charging module 28 is electrically connected to the battery energy management module 25 and is used to obtain power from the selected power supply channel and balance charge the energy storage module 29. Figure 7 As shown in the structural diagram, the energy storage module 71 is used to store electrical energy and provide energy reserves for the system. The voltage monitoring circuit 72 is used to monitor the voltage of the energy storage module 71 and feedback the electrical energy status of the energy storage module 71. The MOSFET switch array 73 is turned on and off according to the control signal output by the voltage monitoring circuit 72 to regulate the energy charging and discharging path. The power supply 74 is electrically connected to the MOSFET switch array 73 to access external electrical energy and replenish energy for the system. The load module 75 is electrically connected to the MOSFET switch array 73 to consume electrical energy and perform the work tasks required by the equipment. By deploying multiple voltage detection circuits 72 to dynamically detect the terminal voltage of each energy storage module 71, actively and evenly drive the MOSFET switch array 73, and combine the battery SOC and SOH data to control the charge and discharge path of the energy storage module 71, energy balance between multiple battery modules is achieved.

[0055] In a specific embodiment, the energy scheduling control module 22 samples the current in the circuit and predicts the load power demand of the aircraft based on the linear relationship between current and voltage. The operating mode is dynamically adjusted according to the prediction result to achieve optimal matching of the energy allocation strategy. The linear relationship between current and voltage is expressed as follows:

[0056] V OUT =G×I SENSE ×R SENSE

[0057] Among them, V OUT is the output voltage, G is the gain factor, I SENSE is the sampling current, R SENSE is the sampling resistor value. SENSE The low-resistance precision resistor and the gain coefficient G generated by the voltage amplifier circuit convert the current value I SENSE Converted into a continuous analog voltage value V that matches the ADC range OUT , and use this to calculate the aircraft's load power.

[0058] In a specific embodiment, the synchronous boost topology module 27 is specifically coupled with the contact charging interface 26 based on the synchronous rectification Boost architecture, and performs a DC-DC boost conversion topology through high-frequency PWM control and MOSFET complementary drive technology, and the voltage gain satisfies:

[0059]

[0060] Among them, V o is the output voltage, V in is the input voltage, and D is the PWM duty cycle. The formula shows that the voltage gain is nonlinearly positively correlated with the duty cycle, and the boost multiple can be dynamically controlled by adjusting D. In this embodiment, the input voltage V in is 5V, the duty cycle D is 0.603, and the output voltage V o The voltage is 12.6V, achieving stable boost, and the boost conversion topology efficiency is 90-94%.

[0061] In a specific embodiment, the battery energy management module 25 specifically implements periodic capture and monitoring of the input / output voltage through the synchronous multi-channel sampling results of the MCU chip, and implements rapid coordination of the switching timing of the second resonant coupling module and the synchronous boost topology module through a preset adaptive control strategy; wherein the synchronous multi-channel sampling results are expressed by the formula:

[0062]

[0063] Among them, the resolution of ADC is N bits, and the reference voltage is V ref , the input analog voltage is V in The converted digital result is Digital_voltage. The formula shows the linear relationship between input and output voltage in synchronous multi-channel sampling. in With reference voltage V ref Compare, calculate their proportions and then map them to the digital range. In this embodiment, the reference voltage V ref The voltage is 3.3V, and the resolution N of the ADC is 12 bits, which meets the monitoring requirements of the battery energy management module 25 for millivolt-level voltage changes.

[0064] In a specific embodiment, the adaptive balanced charging module 28 specifically adopts an active balanced topology to drive the MOSFET switch array and realizes balanced control of the energy storage module 29 based on a preset SOC dynamic balance model; in this embodiment, the energy storage module 29 includes 3 batteries, and the state of charge SOC of the i-th battery is i (t) from the initial state SOC i (t) and the time-varying equilibrium current I bal,i(τ) are jointly determined and expressed as:

[0065]

[0066] Among them, C i is the rated capacity of the i-th battery, I bal,i (τ) is the balancing current at time τ, where a positive value indicates charging and a negative value indicates discharging.

[0067] The adaptive balanced charging module 28 can adjust the balanced current of each battery circuit in real time to make the SOC of all batteries i Satisfying SOC1=SOC2=…···=SOC n .

[0068] Accordingly, this application also proposes a charging method for aircraft, such as Figure 4 As shown, it includes the following steps.

[0069] S41. Energy scheduling control steps include sampling the current in the charging base station circuit, predicting the aircraft's load power demand based on the linear relationship between voltage and current, and dynamically adjusting the operating mode based on the predicted results to achieve optimal matching of the energy allocation strategy and control the output of DC power to match the power. For example, the MCU chip's high-frequency ADC captures voltage in real time, dynamically calculates current characteristics based on the series sampling resistor, predicts the aircraft's load power demand, and dynamically adjusts the operating mode based on the predicted results using a PID algorithm to achieve optimal matching of the energy allocation strategy and output DC power to match the power.

[0070] S42, a magnetic coupling resonant rectification step, including converting direct current into high-frequency alternating current by electromagnetic resonance, and inducing the high-frequency alternating current by resonant coupling and converting the AC / DC into a DC voltage required for wireless charging of the aircraft;

[0071] S43, contact power supply synchronous boosting step, includes the aircraft obtaining 5V / 3A DC power from the charging base station through a physical interface, and performing DC-DC topology boosting of the DC power through synchronous rectification technology.

[0072] S44, the battery energy management step, includes selecting a power supply channel for the wirelessly acquired DC power and the physical contact DC power. For example, the MCU chip performs analog-to-digital conversion sampling, monitors and compares the input voltage and current parameters of the synchronous boost topology module 27 and the second resonant coupling module 24 in real time, and selects a power supply channel for the wirelessly acquired DC power and the physical contact DC power.

[0073] S45, the adaptive balanced charging step, includes obtaining power from the selected power supply channel and performing balanced charging for the aircraft. For example, the system obtains power from the selected power supply channel, dynamically detects the terminal voltage of each energy storage unit, actively and evenly drives the MOSFET array, controls the charge and discharge paths of the energy storage module 29, achieves energy balance among multiple battery modules, and performs balanced charging for the aircraft.

[0074] In a specific embodiment, in the energy scheduling control step S41, the predicted load power demand of the aircraft is obtained in real time based on the linear relationship between the sampled current and voltage using the STM32F411CEU6 chip of the ARM-M4 architecture, and a closed-loop control signal is generated using a dynamic impedance matching algorithm and expressed as follows:

[0075]

[0076] Among them, u(t) is the output control quantity, K p is the proportional coefficient, K i is the integral coefficient, K d is the differential coefficient, e(t) is the error at the current moment; and, based on the closed-loop control signal, the resonant network parameters are dynamically adjusted to achieve adaptive power output of DC power that matches the power. In this embodiment, the energy scheduling control step S41 predicts the load power reference value based on the sampling, and calculates the difference between the load power reference value and the actual output power to obtain the error e(t) at the current moment, and calculates the error through the proportional term K p e(t) reflects the current power deviation, the integral term Cumulative historical error and differential term The error change trend is predicted and a closed-loop control signal u(t) is output to dynamically adjust the resonant network parameters so that the actual output power matches the predicted load power demand.

[0077] In a specific embodiment, in the magnetic coupling resonant rectification step S42, LLC resonant rectification technology is specifically used to perform AC-DC conversion on the high-frequency AC power received by the magnetic resonance coupling.

[0078] For example, in a specific implementation, in the battery energy management step S44, the STM32F411CEU6 chip is specifically used as the MCU chip, which can use the 12-bit ADC to perform analog-to-digital conversion sampling to obtain synchronous multi-channel sampling results, and generate parameter comparison results by comparing the voltage and current parameters of the DC power obtained wirelessly with the DC power voltage and current parameters obtained by physical contact, and dynamically switch the power supply channel based on the parameter comparison results.

[0079] In a specific embodiment, in the adaptive balanced charging step S45 , the voltage of each battery cell is dynamically detected to actively balance the MOSFET array, and the charging and discharging paths of each battery cell are controlled to achieve balanced charging energy.

[0080] The program design content involved in the energy scheduling control module 22 and the battery energy management module 25 is analyzed in detail below.

[0081] Figure 5 The figure shows a schematic diagram of the program operation flow of the energy scheduling control module 22. After providing a 12V DC power supply to enable power supply in step 51, when the external switch is pressed in step 52, the MCU program performs the initialization operation in step 53 and performs digital-to-analog sampling of the switch circuit in step 54. If the switch remains pressed at this time, the locked power supply mechanism is triggered, and the process proceeds to step 55 to obtain the magnetic coupling resonant current characteristic value. After that, the current-voltage analog-to-digital sampling program in step 56 is executed. Then, in step 57, the load power is measured and adjusted. Finally, in step 58, the magnetic coupling resonance is dynamically controlled.

[0082] Figure 6 The program execution flow diagram of the battery energy management module 25 is shown. When the external switch is pressed in step 62, the energy storage module in step 61 is executed to supply energy to the system. The MCU program performs the initialization operation in step 63 and performs analog-to-digital sampling of the switch circuit in step 64. If the switch remains pressed at this time, the locked power supply mechanism is triggered. In steps 65, 66, and 67, dynamic analog-to-digital conversion sampling of the energy storage module channel, contact charging channel, and resonant coupling channel is performed respectively. The analog-to-digital sampling of the power supply channel is shown in step 68. The MCU then makes a channel switching decision in step 69, and dynamically switches to the optimal power supply channel based on the parameter comparison results in step 610. Finally, the balanced charging task is performed in step 611.

[0083] This application proposes a wireless charging base station device and charging method for aircraft. By constructing a dual-mode energy supply collaborative architecture and a dynamic decision-making algorithm, system feedback parameters are calculated in real time through digital-to-analog conversion, achieving coordinated optimization of energy transmission efficiency and system reliability. Furthermore, a bidirectional active balancing network and multi-dimensional compensation strategy are integrated into the charging circuit, surpassing the balancing accuracy limitations of traditional battery management systems.

[0084] For existing aircraft base station technology, one embodiment uses a robotic arm or guide rail system to automatically replace batteries, relying on precise mechanical structures to achieve rapid energy replenishment. However, there are obvious problems such as reliance on precise mechanical structures, easy wear of interfaces, and high maintenance costs, and the adaptability is significantly reduced in unstructured terrain.

[0085] In another embodiment, Figure 3 In the charging method of the existing charging base station for aircraft shown, the power supply interface enabling step 31 can adopt a contact power supply method, or adopt laser charging technology, through the battery energy management step 32, and perform an adaptive balanced charging step 33.

[0086] However, in practical applications, this technology has obvious shortcomings, such as Figure 1 The following is a schematic diagram of the structure of a conventional charging base station device for aircraft. The power supply module 11 is responsible for providing electrical energy input. The battery energy management module 12 is responsible for receiving electrical energy from the power supply module, monitoring the battery status, and regulating basic energy distribution. The adaptive balancing charging module 13 specifically employs an active balancing topology to drive the MOSFET switch array and balance charge the energy storage module 14. The energy storage module 14 is used to store electrical energy, relying on the stable input from the adaptive balancing charging module 13 to accumulate energy. However, due to environmental and physical factors, energy transmission between the power supply module 11 and the battery energy management module 12 can be significantly disrupted. The metal contacts of contact charging are easily oxidized and short-circuited in rain and snow, while laser charging can experience energy attenuation of over 60% in extreme weather conditions such as heavy fog. Both require millimeter-level positioning accuracy, and strong winds can easily cause docking deviation, leading to charging interruption. Both pose significant safety and reliability issues, limiting charging efficiency and application scenarios.

[0087] The present application relates to a wireless charging base station device and charging method for aircraft. After the power supply module 21 is connected, the energy scheduling control module 22 monitors the charging needs of the aircraft in real time, calculates the load impedance, and dynamically coordinates the switching of contact and wireless charging channels. When the aircraft approaches the base station, the first resonant coupling module 23 transmits energy to the second resonant coupling module 24 in the form of electromagnetic waves. At the same time, the synchronous boost topology module 27 can also be used to boost the low-voltage input of the contact interface 26. For the above two energy supply channels, the battery energy management module 25 continuously compares the voltage and current parameters of the two inputs and automatically selects the optimal power supply mode. Finally, the adaptive balanced charging module 28 ensures the charging balance of multiple groups of batteries by dynamically adjusting the charging and discharging paths.

[0088] Due to the dual-mode energy supply collaborative architecture and dynamic decision-making algorithm that combines contact energy supply and magnetic coupling energy supply, the synergistic effect is fully utilized, and the system-level energy transmission efficiency of more than 80% can be maintained under adverse conditions such as rain, snow, and strong winds. At the same time, the safety risk of the charging process is reduced by more than 60% compared with traditional solutions, significantly improving the all-weather reliable operation capability in complex environments.

[0089] Figure 8What is shown is a physical schematic diagram of a charging system for an aircraft in one embodiment of the present application. The battery charging management module 81 is used to control the charging process of the lithium battery pack 82 to ensure safe and efficient charging and maintain a stable battery state. The lithium battery pack 82 is used to store electrical energy to provide power support for aircraft flight and equipment operation. The magnetically coupled wireless power receiving module 83 generates high-frequency alternating current through resonant coupling induction wireless charging base station device 84, and generates the DC voltage required for the aircraft to perform wireless charging through AC-DC conversion. The aircraft motor 85 converts electrical energy into mechanical energy, drives the aircraft rotor to rotate, and realizes the flight function. The aircraft control core 86 is used to integrate flight data, run control algorithms, and command the various components of the aircraft to work together to ensure stable flight. The aircraft tripod 87 is used to provide take-off and landing support, protect the aircraft body, and enhance the stability of ground placement.

[0090] In one embodiment, the aircraft control core 86 precisely controls the aircraft motor 85 to control the drone's landing, allowing the aircraft's footrest 87 to touch down smoothly. After landing, the wireless charging base station 84 is activated, and the magnetically coupled wireless power receiving module 83 establishes a magnetic coupling link with the wireless charging base station 84. The battery charging management module 81 coordinates and directs power to the lithium battery pack 82, initiating the wireless charging process and reserving energy for the next flight.

[0091] In summary, this application can significantly reduce the reliance of aircraft base stations on high-precision positioning under traditional charging technology, break through the limitations of significantly reduced charging efficiency and safety hazards in adverse weather conditions such as rain, snow, and fog, and enable the system to maintain stable charging in complex environments such as strong winds. By intelligently switching between contact and wireless charging modes, it automatically matches the needs of different scenarios, avoiding the oxidation risk of physical contact and reducing environmental interference in wireless transmission, ultimately increasing the overall charging efficiency to more than 80%, while significantly reducing the incidence of safety issues such as short circuits and power outages. In addition, battery balancing technology further solves the problem of uneven charging of multiple groups of batteries, significantly extending the battery life of the device. This solution allows aircraft to charge safely and efficiently even in extreme conditions such as rain, snow, and strong winds, providing reliable support for the all-weather operation of unmanned equipment.

[0092] The above content is a further detailed description of the present application in conjunction with specific implementation methods, and the specific implementation of the present application cannot be considered to be limited to these descriptions. For ordinary technicians in the technical field to which the present application belongs, several simple deductions or substitutions can be made without departing from the inventive concept of the present application.

Claims

1. A charging system for aircraft, characterized in that: Including charging base stations and aircraft; The charging base station includes a power supply module, an energy scheduling control module and a first resonant coupling module; The power supply module is used to provide stable constant voltage DC power; The energy scheduling control module is electrically connected to the power supply module, and is used to generate an optimal energy allocation strategy according to the load power demand of the aircraft and output DC power with matching power; The first resonant coupling module is electrically connected to the energy scheduling control module and is used to convert direct current into high-frequency alternating current through electromagnetic resonance to facilitate wireless transmission; The aircraft includes a second resonant coupling module, a contact charging interface, a synchronous boost topology module, a battery energy management module, an adaptive balanced charging module and an energy storage module; The second resonant coupling module is used to sense the high-frequency alternating current generated by the first resonant coupling module through resonant coupling when the aircraft approaches the charging base station, and to generate the DC voltage required for the aircraft to perform wireless charging through AC-DC conversion; The contact charging interface is used to obtain direct current by physical contact with the power supply module through a Type-C interface electrical connection; The synchronous boost topology module is electrically connected to the contact charging interface and is used to perform DC-DC topology boosting of direct current through synchronous rectification technology; The battery energy management module is electrically connected to the second resonant coupling module and the synchronous boost topology module, and is used to control the power switch timing of the second resonant coupling module and the synchronous boost topology module to select the power supply channel; The adaptive balanced charging module is electrically connected to the battery energy management module, and is configured to obtain electrical energy from a selected power supply channel and perform balanced charging for the energy storage module.

2. The charging system according to claim 1, wherein: The energy scheduling control module specifically samples the current in the circuit and predicts the load power demand of the aircraft based on the linear relationship between current and voltage. The operating mode is dynamically adjusted according to the prediction result to achieve optimal matching of the energy distribution strategy. The linear relationship between current and voltage is expressed by the formula: In OUT =G×i SENSE ×r SENSE Among them, V OUT is the output voltage, G is the gain factor, I SENSE is the sampling current, r SENSE is the sampling resistor value.

3. The charging system according to claim 1, wherein: The synchronous boost topology module is specifically coupled with the contact charging interface based on a synchronous rectification Boost architecture, and implements a DC-DC boost conversion topology through high-frequency PWM control and MOSFET complementary drive technology, and the voltage gain satisfies: Among them, v o is the output voltage, v in is the input voltage and D is the PWM duty cycle.

4. The charging system according to claim 1, wherein: The battery energy management module specifically implements periodic capture and monitoring of the input / output voltage through the synchronous multi-channel sampling results of the MCU chip, and implements rapid coordination of the switching timing of the second resonant coupling module and the synchronous boost topology module through a preset adaptive control strategy; wherein the synchronous multi-channel sampling results are expressed by the formula: Among them, the resolution of ADC is N bits, and the reference voltage is v ref , the input analog voltage is V in , the converted digital result is Digital_voltage.

5. The charging system according to claim 1, wherein: The adaptive balanced charging module specifically adopts an active balanced topology to drive the MOSFET switch array and realizes balanced control of the energy storage module based on a preset SOC dynamic balance model; the energy storage module includes multiple batteries, and the state of charge SOC of the i-th battery is i (t) From the initial state SOC i (t) and the time-varying equilibrium current I bal,i (τ) are jointly determined and expressed as: The adaptive balanced charging module can adjust the balanced current of each battery circuit in real time to make the SOC of all batteries i Satisfying SOC1=SOC2=…···=SOC n .

6. A charging method for an aircraft, characterized in that: include: The energy scheduling control step includes sampling the current in the charging base station circuit and predicting the aircraft's load power demand based on the linear relationship between voltage and current. Based on the prediction results, the operating mode is dynamically adjusted to achieve optimal matching of the energy allocation strategy and control the output power to match the DC power. The magnetic coupling resonant rectification step includes converting direct current into high-frequency alternating current by electromagnetic resonance, and generating the direct current voltage required for wireless charging of the aircraft by inducing the high-frequency alternating current through resonant coupling and performing AC-DC conversion; The contact power supply synchronous boosting step includes the aircraft obtaining direct current from the charging base station through a physical interface, and performing a DC-DC topology boosting of the direct current through synchronous rectification technology; Battery energy management steps, including selecting power supply channels for direct current obtained wirelessly and direct current obtained through physical contact; The adaptive balanced charging step includes obtaining electric energy from the selected power supply channel and performing balanced charging for the aircraft.

7. The charging method for an aircraft according to claim 6, characterized in that: The energy scheduling control step specifically includes obtaining a predicted load power demand of the aircraft in real time based on the linear relationship between the sampled current and voltage using the STM32F411CEU6 chip of the ARM-M4 architecture, generating a closed-loop control signal using a dynamic impedance matching algorithm, and expressing it as follows: Among them, u(t) is the output control quantity, K p is the proportional coefficient, K i is the integral coefficient, K d is the differential coefficient, e(t) is the error at the current moment; Furthermore, the parameters of the resonant network are dynamically adjusted based on the closed-loop control signal to achieve adaptive power output of direct current with matched power.

8. The charging method for an aircraft according to claim 6, characterized in that: In the magnetic coupling resonant rectification step, LLC resonant rectification technology is specifically used to perform AC-DC conversion on the high-frequency AC power received by the magnetic resonance coupling.

9. The charging method for an aircraft according to claim 6, characterized in that: In the battery energy management step, the STM32F411CEU6 chip is specifically used as the MCU chip, which can use a 12-bit ADC to perform analog-to-digital conversion sampling to obtain synchronous multi-channel sampling results, generate parameter comparison results by comparing the voltage and current parameters of the DC power obtained wirelessly with the DC power voltage and current parameters obtained by physical contact, and dynamically switch the power supply channel based on the parameter comparison results.

10. The charging method for aircraft according to claim 6, characterized in that: In the adaptive balanced charging step, the voltage of each battery cell is dynamically detected to actively balance the MOSFET array, and the charging and discharging paths of each battery cell are controlled to achieve balanced charging energy.

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