Aircraft power-on system, method, electronic device, and storage medium

Abstract

Embodiments of the application disclose an aircraft power-on system and method, electronic equipment and a storage medium, and relate to the technical field of aircrafts. The system comprises a ground power supply, a wireless power supply module transmitting end, a wireless power supply module receiving end, an aircraft power supply switch module and an aircraft power supply. The wireless power supply module transmitting end converts a first direct current voltage signal output by the ground power supply into a magnetic field signal, and sends the magnetic field signal to the wireless power supply module receiving end in a wireless manner. The wireless power supply module receiving end receives the magnetic field signal and converts the magnetic field signal into a second direct current voltage signal. The aircraft power supply switch module receives the second direct current voltage signal, switches from an open state to a closed state according to a voltage value of the second direct current voltage signal, and controls the aircraft power supply to supply power to the aircraft. The embodiments of the application control the opening and closing of the aircraft power supply in a wireless connection manner, and effectively improve the safety of opening the aircraft power supply.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more specifically, to an aircraft power supply system, method, electronic device, and storage medium. Background Technology

[0002] In recent years, with the development of science and technology, aircraft have been used more and more widely. When an aircraft is launched, it needs to start the power supply on the aircraft to provide power to support the aircraft in completing flight operations.

[0003] Currently, the power supply to an aircraft needs to be switched on before launch; however, because aircraft typically carry pyrotechnics, close-range power-on operations pose a safety risk. If a cable is used to control the power supply between the ground and the aircraft, this cable must be disconnected before takeoff, which could lead to abnormal cable separation and affect the launch. Therefore, it is necessary to improve the safety of aircraft power-on operations. Summary of the Invention

[0004] This application provides an aircraft power-on system, method, electronic device, and storage medium to improve the safety of aircraft power-on operations.

[0005] According to a first aspect of the embodiments of this application, an aircraft power supply system is provided, the system comprising: a ground power supply, a wireless power supply module transmitter, a wireless power supply module receiver, an aircraft power switch module, and an aircraft power supply; The wireless power supply module transmitter converts the first DC voltage signal output by the ground power supply into a magnetic field signal, and transmits the magnetic field signal wirelessly to the wireless power supply module receiver. The wireless power supply module receiver receives the magnetic field signal and converts the magnetic field signal into a second DC voltage signal; wherein, the voltage value of the second DC voltage signal includes the operating voltage value of the aircraft power switch module; The aircraft power switch module receives the second DC voltage signal and switches from an open state to a closed state according to the voltage value of the second DC voltage signal, thereby controlling the aircraft power supply to supply power to the aircraft.

[0006] As an optional implementation, the wireless power supply module transmitter includes: a power full-bridge circuit, a first LC resonant circuit, and a first microcontroller; The first microcontroller generates a PWM pulse width modulation signal and outputs the PWM pulse width modulation signal to the power full-bridge circuit. The power full-bridge circuit converts the first DC voltage signal into a high-frequency square wave signal according to the PWM pulse width modulation signal, and outputs the high-frequency square wave signal to the first LC resonant circuit. The first LC resonant circuit filters the high-frequency square wave signal to obtain an alternating current. The alternating current generates an induced magnetic field, and the magnetic field signal of the induced magnetic field is sent to the receiving end of the wireless power supply module via electromagnetic waves.

[0007] As an optional implementation, the wireless power supply module receiver includes a second LC resonant circuit, a rectifier bridge, and a linear voltage regulator circuit; The second LC resonant circuit generates a first AC voltage signal based on the magnetic field signal and outputs the first AC current-voltage signal to the rectifier bridge; wherein the voltage value of the first AC voltage signal is the same as the voltage value of the second DC voltage signal. The rectifier bridge converts the first AC voltage signal into a third DC voltage signal and outputs the third DC voltage signal to the linear voltage regulator circuit. The linear voltage regulator circuit regulates the third DC voltage signal to obtain the second DC voltage signal.

[0008] As an optional implementation, the wireless power supply module receiver also includes a second microcontroller; The second microcontroller determines the power value of the second LC resonant circuit based on the first AC voltage signal and the resistance value of the receiving end of the wireless power supply module, and uses this as the first power value. If the first power value is less than the second power value, a first signal is sent to the transmitter of the wireless power supply module, the first signal including the second power value; wherein, the second power value is the maximum power value that the receiver of the wireless power supply module is allowed to receive; The first microcontroller acquires the first signal and adjusts the duty cycle of the PWM pulse width modulation signal output by the power full-bridge circuit according to the second power value; The first LC resonant circuit adjusts the strength of the magnetic field signal output to the receiver of the wireless power supply module according to the duty cycle adjusted by the PWM pulse width modulation signal. The second LC resonant circuit receives the adjusted magnetic field signal and adjusts the voltage value of the first AC voltage signal according to the strength of the adjusted magnetic field signal, thereby controlling the first power value to be the same as the second power value.

[0009] As an optional implementation, the aircraft power switch module includes a magnetic latching relay; Specifically, based on the voltage value of the second DC voltage signal, the contacts of the magnetic latching relay close, the state of the aircraft power switch module changes from open to closed, and the aircraft power supply is controlled to supply power to the aircraft.

[0010] As an optional implementation, the system further includes a flight control computer; the aircraft power switch module further includes a normally closed relay, which is located between the aircraft power supply and the magnetic latching relay; The flight control computer sends a first instruction to the normally closed relay, the first instruction being used to instruct the normally closed relay to switch from a normally closed state to a normally open state. The normally closed relay receives the first instruction and switches from the normally closed state to the normally open state, controlling the aircraft power supply to stop supplying power to the aircraft.

[0011] According to a second aspect of the embodiments of this application, a method for powering on an aircraft is provided. The method is applied to an aircraft power-on system, the system comprising: a ground power supply, a wireless power supply module transmitter, a wireless power supply module receiver, an aircraft power switch module, and an aircraft power supply. The method includes: The wireless power supply module transmitter receives the first DC voltage signal output by the ground power supply and converts the first DC voltage signal into a magnetic field signal. The wireless power supply module receives the magnetic field signal and generates a second DC voltage signal based on the magnetic field signal; wherein, the voltage value of the second DC voltage signal includes the operating voltage value of the aircraft power switch module; The aircraft power switch module receives the second DC voltage signal and switches from an open state to a closed state according to the voltage value of the second DC voltage signal, thereby controlling the aircraft power supply to supply power to the aircraft.

[0012] As an optional implementation, the wireless power supply module receives the magnetic field signal and generates a second DC voltage signal based on the magnetic field signal, including: A first AC voltage signal is generated based on the magnetic field signal; The first AC voltage signal is converted into a third DC voltage signal, and the third DC voltage signal is regulated to obtain the second DC voltage signal.

[0013] As an optional implementation, the conversion of the first AC voltage signal into a third DC voltage signal includes: If the first power value is less than the second power value, a first signal is sent to the wireless power supply module, the first signal including the second power value, so that the wireless power supply module adjusts the strength of the magnetic field signal output to the receiving end of the wireless power supply module; Wherein, the first power value is determined by the voltage value of the first AC voltage signal and the resistance value of the receiving end of the wireless power supply module, and the second power value is the maximum power value that the receiving end of the wireless power supply module is allowed to receive.

[0014] As an optional implementation, the system also includes a flight control computer; The aircraft power switch module receives the second DC voltage signal and switches from an open state to a closed state according to the voltage value of the second DC voltage signal, controlling the aircraft power supply to supply power to the aircraft. The module also includes: The flight control computer sends a first instruction to the aircraft power switch module, the first instruction being used to instruct the aircraft power switch module to switch from a closed state to an open state, thereby controlling the aircraft power supply to stop supplying power to the aircraft.

[0015] According to a third aspect of the present application, an electronic device is provided, comprising: a memory, a processor, and a computer program stored in the memory, wherein the processor executes the computer program to implement the method described in any one of the second aspects.

[0016] According to a fourth aspect of the embodiments of this application, a computer-readable storage medium is provided having a computer program stored thereon that, when executed by a processor, implements the method as described in any one of the second aspects.

[0017] The beneficial effects of the technical solutions provided in this application are: In this embodiment, the wireless power supply module transmitter converts the first DC voltage signal output from the ground power supply into a magnetic field signal and wirelessly transmits the magnetic field signal to the wireless power supply module receiver. The wireless power supply module receiver converts the magnetic field signal into a DC voltage signal via electromagnetic conversion and outputs the DC voltage signal to the aircraft power switch module. The magnetic latching relay of the aircraft power switch module switches from an open state to a closed state under the action of the DC voltage signal, controlling the aircraft power supply to power the aircraft. This embodiment enables remote control of the aircraft power supply to turn on and off, avoiding the risks associated with short-range aircraft power-on in the prior art, and effectively improving the safety of aircraft power-on operation. Simultaneously, the wireless connection between the aircraft and the ground avoids the impact of abnormal cable separation on aircraft transmission seen in the prior art. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments of this application will be briefly introduced below.

[0019] Figure 1 This is a schematic diagram of the structure of the aircraft power supply system provided in the embodiments of this application; Figure 2 This application provides a schematic diagram of the structure of a wireless power supply module transmitter. Figure 3 This is a schematic diagram of the structure of a wireless power supply module receiver provided in an embodiment of this application; Figure 4 A schematic diagram of the structure of an aircraft power switch module, an aircraft power supply, and a flight control computer provided in this application embodiment; Figure 5 A schematic flowchart illustrating an aircraft power-on method provided in this application embodiment; Figure 6 An interactive schematic diagram of an aircraft power-on method provided in an embodiment of this application; Figure 7 This is a schematic diagram of the structure of an electronic device provided in an embodiment of this application. Detailed Implementation

[0020] The embodiments of this application are described below with reference to the accompanying drawings. It should be understood that the embodiments described below with reference to the accompanying drawings are exemplary descriptions for explaining the technical solutions of the embodiments of this application, and do not constitute a limitation on the technical solutions of the embodiments of this application.

[0021] Those skilled in the art will understand that, unless otherwise stated, the singular forms “a,” “an,” and “the” used herein may also include the plural forms. It should be further understood that the terms “comprising” and “including” as used in embodiments of this application mean that the corresponding feature can be implemented as the presented feature, information, data, step, operation, element, and / or component, but do not exclude implementation as other features, information, data, step, operation, element, component, and / or combinations thereof supported by the art. It should be understood that when we say that an element is “connected” or “coupled” to another element, the one element can be directly connected or coupled to the other element, or it can mean that the one element and the other element establish a connection relationship through an intermediate element. Furthermore, “connected” or “coupled” as used herein can include wireless connection or wireless coupling. The term “and / or” as used herein indicates at least one of the items defined by the term; for example, “A and / or B” can be implemented as “A,” or as “B,” or as “A and B.”

[0022] In the embodiments of this application, the terms "module" or "unit" refer to a computer program or part of a computer program that has a predetermined function and works with other related parts to achieve a predetermined goal, and can be implemented wholly or partially using software, hardware (such as processing circuitry or memory), or a combination thereof. Similarly, a processor (or multiple processors or memory) can be used to implement one or more modules or units. Furthermore, each module or unit can be part of an overall module or unit that includes the functionality of that module or unit.

[0023] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.

[0024] In recent years, with the development of technology, aircraft have been used more and more widely. Usually, aircraft carry a power source, and when an aircraft is launched, the power source needs to be activated to supply power to the aircraft in order to support the aircraft in completing its flight operations.

[0025] Currently, before launch, it is necessary to activate the aircraft's power supply at close range; however, since aircraft typically carry pyrotechnics, activating the power supply at close range carries low safety risks. If a cable connection is used between the ground and the aircraft to control the power supply, the cable must be disconnected before takeoff, which could lead to abnormal cable separation and affect the launch. Therefore, it is necessary to improve the safety of aircraft power-on operations.

[0026] The aircraft power supply system, method, electronic equipment, and storage medium provided in this application are intended to solve the above-mentioned technical problems of the prior art.

[0027] The technical solutions of this application and their effects are described below through several exemplary embodiments. It should be noted that the following embodiments can be referenced, borrowed from, or combined with each other. Identical terms, similar features, and similar implementation steps in different embodiments will not be repeated.

[0028] This application provides an aircraft power supply system, which includes: a ground power supply, a wireless power supply module transmitter, a wireless power supply module receiver, an aircraft power switch module, and an aircraft power supply. Among them, the wireless power supply module transmitter converts the first DC voltage signal output by the ground power supply into a magnetic field signal, and sends the magnetic field signal to the wireless power supply module receiver wirelessly. The wireless power supply module receiver receives the magnetic field signal and converts it into a second DC voltage signal; wherein the voltage value of the second DC voltage signal includes the operating voltage value of the aircraft power switch module; The aircraft power switch module receives a second DC voltage signal and switches from an open state to a closed state based on the voltage value of the second DC voltage signal, thereby controlling the aircraft power supply to provide power to the aircraft.

[0029] Specifically, this application provides a schematic diagram of the structure of an aircraft's power supply system; as shown in the following embodiments. Figure 1 As shown, the aircraft power supply system 100 includes: a ground power supply 10, a wireless power supply module transmitter 20, and an aircraft 200; wherein the aircraft 200 includes: a wireless power supply module receiver 30, an aircraft power switch module 40, an aircraft power supply 50, and a flight control computer 60.

[0030] In this embodiment, the ground power supply 10 is connected to the wireless power supply module transmitter 20, providing a first DC voltage signal to the transmitter 20. The wireless power supply module transmitter 20 converts the first DC signal provided by the ground power supply 10 into a magnetic field signal and transmits it wirelessly to the wireless power supply module receiver 30, enabling wireless connection between the aircraft 200 and the ground, thus avoiding the technical problem in the prior art where the aircraft 200's transmission is affected by cable disconnection failure. The wireless power supply module receiver 30 is connected to the aircraft power switch module 40; after receiving the magnetic field signal, the receiver 30 converts it into a second DC voltage signal and outputs it to the aircraft power switch module 40. The aircraft power switch module 40 switches from an open state to a closed state according to the second DC voltage signal input from the wireless power supply module receiver 30, controlling the aircraft power supply 50 to supply power to the aircraft 200, realizing remote control of the aircraft power supply's activation, and effectively improving the safety of the aircraft power-on operation.

[0031] In this embodiment, the ground power supply 10 and the wireless power supply module transmitter 20 are located outside the aircraft 200; the wireless power supply module receiver 30, the aircraft power switch module 40, the aircraft power supply 50, and the flight control computer 60 are located inside the aircraft; wherein, the wireless power supply module transmitter 20 and the wireless power supply module receiver 30 are placed facing each other; wherein, placing them facing each other means that the wireless power supply module transmitter 20 and the wireless power supply module receiver 30 maintain a state in which their geometric centers coincide or their magnetic field coupling regions overlap to the maximum extent; for example, the planes of the wireless power supply module transmitter 20 and the wireless power supply module receiver 30 are parallel and their center points completely coincide.

[0032] It should be noted that the magnetic field coupling coefficient is maximized and energy transmission loss is minimized when the wireless power supply module transmitter 20 and receiver 30 are placed facing each other; the magnetic field coupling coefficient is inversely proportional to the distance. For example, when the distance between the wireless power supply module transmitter 20 and receiver 30 is less than 8mm, the energy transmission efficiency can reach 70%-80%; when the distance between the wireless power supply module transmitter 20 and receiver 30 exceeds 8mm, the energy transmission efficiency decreases significantly; for example, when the distance between the wireless power supply module transmitter 20 and receiver 30 is 10mm, the energy transmission efficiency drops below 60%. Therefore, those skilled in the art can set the distance between the wireless power supply module transmitter 20 and receiver 30 according to the actual situation.

[0033] Furthermore, such as Figure 1 As shown, in this embodiment of the application, the aircraft power switch module 40 is connected to the flight control computer 60, and the aircraft power supply 50 supplies power to the aircraft 200, including the flight control computer. The aircraft power supply 50 supplies power to the aircraft 200, including the flight control computer 60.

[0034] In an optional embodiment, the aircraft also includes other modules, including but not limited to: pyrotechnic detonator, servo motor, servo motor controller, etc. Figure 1 (not shown in the image). When the aircraft 200 includes the above-mentioned modules, the aircraft power supply to the aircraft also includes supplying power to the above-mentioned modules; those skilled in the art can determine the type and quantity of other modules on the aircraft according to the actual situation.

[0035] In an optional embodiment, the aircraft power switch module can be a separate module in the aircraft, or it can be located inside the flight control computer or other modules; those skilled in the art can set the location of the aircraft power switch module according to the actual situation.

[0036] This application embodiment enables remote control of the aircraft's power supply to be turned on and off, avoiding the risks associated with turning on the aircraft's power supply at close range in the prior art, and effectively improving the safety of the aircraft's power-on operation; at the same time, the aircraft is connected to the ground wirelessly, avoiding the impact of abnormal cable separation on the aircraft's launch in the prior art.

[0037] Based on the above embodiments, as an optional embodiment, the wireless power supply module transmitter includes: a power full-bridge circuit, a first LC resonant circuit, and a first microcontroller; The first microcontroller generates a PWM pulse width modulation signal and outputs the PWM pulse width modulation signal to the power full-bridge circuit. The power full-bridge circuit converts the first DC voltage signal into a high-frequency square wave signal according to the PWM pulse width modulation signal, and outputs the high-frequency square wave signal to the first LC resonant circuit. The first LC resonant circuit filters the high-frequency square wave signal to obtain an alternating current. The alternating current generates an induced magnetic field, and the magnetic field signal of the induced magnetic field is sent to the receiver of the wireless power supply module via electromagnetic waves.

[0038] Specifically, this application provides a schematic diagram of the structure of a wireless power supply module transmitter, as shown in the embodiment. Figure 2 As shown, the wireless power supply module transmitter 20 includes: a first microcontroller 201, a power full-bridge circuit 202, and a first LC resonant circuit 203.

[0039] Specifically, in this embodiment, the power full-bridge circuit 202 is connected to the ground power supply, and the first LC resonant circuit 203 is connected to the wireless power supply module receiver. The power full-bridge circuit 202 receives the DC voltage signal sent by the ground power supply. The first microcontroller 201 generates a PWM pulse width modulation signal and sends it to the power full-bridge circuit 202, controlling the full-bridge circuit 202 to generate a high-frequency square wave signal based on the received DC voltage signal and the PWM pulse width modulation signal, and outputs the high-frequency square wave signal to the first LC resonant circuit 203. When the frequency of the high-frequency square wave signal approaches the inherent resonant frequency of the first LC resonant circuit 203, the inductor and capacitor in the first LC resonant circuit 203 resonate, and the energy between the inductor and capacitor periodically exchanges. After the high-frequency square wave signal passes through the LC resonant circuit, the harmonic components are filtered out, resulting in an alternating current. The waveform of the alternating current is approximately sinusoidal. According to Faraday's principle of electromagnetic induction, a changing current generates an induced magnetic field, and the magnetic field signal of the induced magnetic field is transmitted to the wireless power supply module receiver in the form of an electromagnetic wave.

[0040] In some optional embodiments, the ground power supply outputs a 12V DC voltage signal; the first microcontroller generates a PWM pulse width modulation signal with a frequency of 140KHz and outputs the PWM pulse width modulation signal to the full-bridge power circuit, controlling the full-bridge power circuit to generate a 12V high-frequency square wave signal (frequency of 140KHz) based on the 12V DC voltage signal and the 140KHz PWM pulse width modulation signal.

[0041] It should be noted that the PWM pulse width modulation signal includes a preset duty cycle; the duty cycle is used to determine the ratio of the duration of the high level of the PWM pulse width modulation signal within one cycle to the total cycle time. For example, when the preset duty cycle is 15%, the duration of the high level within one cycle accounts for 15% of the total cycle time, and the remaining 85% of the cycle time is the duration of the low level. In this embodiment, the power full-bridge circuit is equipped with a MOSFET. When the PWM pulse width modulation signal is high, the MOSFET is turned on, and the power full-bridge circuit generates a high-level signal; when the PWM pulse width modulation signal is low, the MOSFET is turned off, and the power full-bridge circuit generates a low-level signal; the high-level signal and the low-level signal within one cycle are combined to obtain a square wave signal.

[0042] It should also be noted that in the embodiments of this application, the frequency and duty cycle of the high-frequency square wave signal are the same as those of the PWM pulse width modulation signal; when the frequency and duty cycle of the PWM pulse width modulation signal change, the frequency and duty cycle of the high-frequency square wave signal will also change accordingly.

[0043] In this embodiment, the first microcontroller generates a PWM pulse width modulation signal and outputs it to the power full-bridge circuit, controlling the power full-bridge circuit to convert the DC voltage signal into a high-frequency square wave signal; the LC resonant circuit filters the high-frequency square wave signal to obtain an alternating current; the alternating current generates an induced magnetic field in the transmitting coil, and the magnetic field signal of the induced magnetic field is sent to the receiving end of the wireless power supply module by means of electromagnetic waves, realizing the wireless transmission of electrical energy.

[0044] Based on the above embodiments, as an optional embodiment, the wireless power supply module receiver includes a second LC resonant circuit, a rectifier bridge, and a linear voltage regulator circuit; The second LC resonant circuit generates a first AC voltage signal based on the magnetic field signal and outputs the first AC current-voltage signal to the rectifier bridge; wherein the voltage value of the first AC voltage signal is the same as the voltage value of the second DC voltage signal. The rectifier bridge converts the first AC voltage signal into a third DC voltage signal, and outputs the third DC voltage signal to the linear voltage regulator circuit; The linear voltage regulator circuit regulates the third DC voltage signal to obtain the second DC voltage signal.

[0045] Specifically, this application provides a schematic diagram of the structure of a wireless power supply module receiver, as shown in the embodiment. Figure 3 As shown, the wireless power supply module receiver 30 includes: a second microcontroller 301, a second LC resonant circuit 302, a rectifier bridge 303, and a linear voltage regulator circuit 304.

[0046] Specifically, in this embodiment, the wireless power supply module receiver 30 is disposed inside the aircraft, and the wireless power supply module transmitter is disposed outside the aircraft. The first LC resonant circuit of the wireless power supply module transmitter transmits the magnetic field signal to the second LC resonant circuit 302 of the wireless power supply module receiver 30 in the form of electromagnetic waves. The second LC resonant circuit 302 includes a capacitor and an inductor. When the magnetic field signal acts on the second LC resonant circuit 302, an induced electromotive force is generated in the inductor, and a current is formed by charging and discharging in the capacitor. When the capacitor discharges, the current flows through the inductor, and the inductor stores magnetic field energy. When the current decreases... The inductor generates a reverse electromotive force, continuing to charge the capacitor, but with opposite polarity, forming a first AC voltage signal. This first AC voltage signal is output to the rectifier bridge 303. The rectifier bridge 303 converts the received first AC voltage signal into a third DC voltage signal and outputs the third DC voltage signal to the linear voltage regulator circuit 304. The linear voltage regulator circuit 304 is a circuit device that stabilizes the output voltage by adjusting the internal resistance or current. The linear voltage regulator circuit 304 regulates the third DC voltage signal to obtain a second DC voltage signal, which is then output to the aircraft power switch module. It should be noted that, in this embodiment, the second DC voltage signal is the operating voltage of the aircraft power switch module, controlling the switching state of the aircraft power switch module.

[0047] In this embodiment, the second LC resonant circuit, rectifier bridge, and linear voltage regulator circuit of the wireless power supply module receiver work together to efficiently and stably convert the magnetic field signal into a DC voltage signal, providing a reliable power supply for the aircraft power switch module.

[0048] Based on the above embodiments, as an optional embodiment, the wireless power supply module receiver also includes a second microcontroller; The second microcontroller determines the power value of the second LC resonant circuit based on the first AC voltage signal and the resistance value of the wireless power supply module receiver, and uses it as the first power value. If the first power value is less than the second power value, a first signal is sent to the transmitter of the wireless power supply module. The first signal includes the second power value. The second power value is the maximum power value that the receiver of the wireless power supply module is allowed to receive. The first microcontroller acquires the first signal and adjusts the duty cycle of the PWM pulse width modulation signal output by the power full-bridge circuit according to the second power value; The first LC resonant circuit adjusts the strength of the magnetic field signal output to the receiver of the wireless power supply module based on the duty cycle adjusted by the PWM pulse width modulation signal. The second LC resonant circuit receives the adjusted magnetic field signal and adjusts the voltage value of the first AC voltage signal according to the strength of the adjusted magnetic field signal, so as to control the first power value to be the same as the second power value.

[0049] Specifically, in this embodiment, the second microcontroller determines the power value transmitted from the wireless power supply module transmitter as the first power value based on the voltage value of the first AC voltage signal and the equivalent resistance value of the wireless power supply module coil. When the first power value is less than the maximum power value allowed to be received by the wireless power supply module receiver, the wireless power supply module receiver sends a first signal to the wireless power supply module transmitter, wherein the first signal includes the maximum power value allowed to be received by the wireless power supply module receiver. After receiving the first signal, the wireless power supply module transmitter adjusts the duty cycle of the PWM pulse width modulation signal according to the maximum power value allowed to be received by the wireless power supply module receiver, thereby adjusting the power value transmitted from the wireless power supply module transmitter to the wireless power supply module receiver.

[0050] The following is a specific example to illustrate this.

[0051] Example 1: Initially, the first microcontroller of the wireless power supply module transmitter is set to a PWM pulse width modulation signal frequency of 140kHz and a duty cycle of 15%. The DC voltage signal from the ground power supply is 12V, and the equivalent resistance of the coil at the wireless power supply module transmitter is... Under these conditions, the voltage output by the transmitter coil of the wireless power supply module is: At this time, the power of the wireless power supply module transmitter is: Ignoring the electromagnetic conversion process at the transmitter of the wireless power supply module and the energy loss during the propagation of the magnetic field signal in the air, the power received by the receiver of the wireless power supply module is approximately 5W. Assuming the maximum power allowed to be received by the receiver is 15W, this maximum allowed power (e.g., 15W) is fed back to the transmitter. After receiving the maximum power demand of 15W, the first microcontroller at the transmitter adjusts the duty cycle of the PWM signal to three times its original value (i.e., setting it to 45%), since 15W is three times 5W. This increases the conduction time of the MOSFETs in the full-bridge power circuit. At this point, the output power of the transmitter is... The power received by the wireless power supply module is the same as the maximum power that the receiver can receive. Assuming that the equivalent resistance of the coil at the receiver end of the wireless power supply module is the same as that at the transmitter end of the wireless power supply module, both are 4.35Ω, when the receiver end of the wireless power supply module receives 15W of energy, it outputs a 12V DC voltage signal after passing through the rectifier bridge and the linear voltage regulator circuit.

[0052] It should be noted that, in addition to the second LC resonant circuit, the wireless power supply module receiver also includes a rectifier bridge and a linear voltage regulator circuit. The rectifier bridge is used to convert the AC voltage signal output by the second microcontroller into a DC voltage signal, and the linear voltage regulator circuit is used to regulate the DC voltage signal and output a stable 12V DC voltage signal, thereby controlling the switching state of the aircraft power switch module.

[0053] In this embodiment, the wireless power supply module receiver sends its maximum allowable power value to the wireless power supply module transmitter, enabling the wireless power supply module to dynamically adjust the duty cycle of the PWM pulse width modulation signal according to the actual needs of the wireless power supply module receiver, ensuring that the power received by the wireless power supply module receiver is the same as its maximum allowable power, thereby improving the overall efficiency of the wireless power supply system.

[0054] Based on the above embodiments, as an optional embodiment, the aircraft power switch module includes a magnetic latching relay; Specifically, based on the voltage value of the second DC voltage signal, the contacts of the magnetic latching relay close, and the state of the aircraft power switch module changes from the open state to the closed state, controlling the aircraft power supply to supply power to the aircraft.

[0055] Specifically, this application provides a structural schematic diagram of an aircraft power switch module, an aircraft power supply, and a flight control computer; as shown in the following embodiments. Figure 4 As shown, the aircraft power switch module 40 includes a normally closed relay 401 and a magnetic latching relay 402; the flight control computer 60 includes a diode 601 and an internal circuit 602; wherein, the magnetic latching relay 402 is connected to the wireless power supply module receiver 30 and the diode 601 respectively; the normally closed relay 401 is connected to the aircraft power supply 50, the magnetic latching relay 402 and the internal circuit 602 of the flight control computer respectively.

[0056] In this embodiment, the magnetic latching relay 402 uses the magnetic force of a permanent magnet to maintain its switching state, rather than relying on a continuous current. When a brief pulse current is applied externally through the coil, the magnetic system inside the magnetic latching relay 402 changes, thereby switching the state of the contacts.

[0057] A resistor is provided between the wireless power supply module receiver 30 and the magnetic latching relay 402. The output terminal 30 of the wireless power supply module generates current through the resistor. When the current acts on the magnetic latching relay 402, the magnetic system inside the magnetic latching relay 402 will change, thereby switching the state of the contacts. Once the state switching is completed, even if the current in the coil disappears, the magnetic latching relay 402 can continue to retain the current switching state.

[0058] Specifically, in this embodiment, the preset switching state of the magnetic latching relay 402 is the open state. When current is applied to the magnetic latching relay 402, the switching state of the magnetic latching relay 402 switches from the open state to the closed state.

[0059] Specifically, in this embodiment, the normally closed relay 401 and the magnetic latching relay 402 are connected in series, and the initial switching state of the normally closed relay 401 is the closed state. Therefore, when the switching state of the magnetic latching relay 402 changes from the open state to the closed state, the switching state of the aircraft power switch module 40 also changes from the open state to the closed state. At this time, the aircraft power supply 50 can supply power to the aircraft through the aircraft power switch module 40, including supplying power to the flight control computer 60.

[0060] In some alternative embodiments, the aircraft also includes other modules, including but not limited to: pyrotechnic detonators, servo motors, servo motor controllers, etc.; the aircraft power supply provides power to the aircraft and also provides power to the aforementioned modules.

[0061] In this embodiment of the application, in the aircraft power switch module, a magnetic latching relay is used to control the on and off of the power supply. By inputting current to the magnetic latching relay, the contacts of the magnetic latching relay are controlled to switch from the open state to the closed state. Moreover, the contacts of the magnetic latching relay are locked by the spring in the closed state, so they can remain in the energized state even after the power is cut off. This has high stability and reliability, and controls the aircraft power supply to continuously and stably supply power to the aircraft.

[0062] Based on the above embodiments, as an optional embodiment, the system further includes a flight control computer; the aircraft power switch module further includes a normally closed relay, which is located between the aircraft power supply and the magnetic latching relay; The flight control computer sends a first command to the normally closed relay, which instructs the normally closed relay to switch from the normally closed state to the normally open state. When the normally closed relay receives the first command, it switches from the normally closed state to the normally open state, controlling the aircraft power supply to stop supplying power to the aircraft.

[0063] like Figure 4 As shown, the internal circuit 602 of the flight control computer includes a CPU and / or control circuit, which can generate command signals. When it is necessary to stop the aircraft power supply 50 to supply power to the aircraft, the internal circuit 602 of the flight control computer sends a first command to the normally closed relay 401. The first command is used to indicate that the switching state of the normally closed relay is switched from the normally closed state to the normally open state.

[0064] Specifically, the normally closed relay 401 consists of a coil, an iron core, an armature, contacts, and a spring. The coil, usually made of insulated wire, is the key component for generating the magnetic field. The iron core enhances the magnetic field generated by the coil. The armature can move under the influence of the magnetic field, causing the contacts to close or open. The contacts are divided into normally closed contacts and normally open contacts. The normally closed contacts are closed when the relay is not energized and open when energized, while the normally open contacts are open. The spring is used to restore the armature to its initial position when the relay is de-energized.

[0065] Specifically, in this embodiment, when the relay coil of the normally closed relay 401 is not energized, no current flows through the coil, and therefore no magnetic field is generated; under the action of the spring, the armature remains in the initial position, at which time the normally closed contact is closed, the normally closed relay is in the normally closed state, and current and voltage signals can pass through the normally closed relay. It can be understood that in this embodiment, the initial switching state of the normally closed relay 401 is the closed state.

[0066] Specifically, when the flight control computer's internal circuit 602 sends a first command to the normally closed relay 401, the coil of the normally closed relay 401 is energized. Current flows through the coil, and according to the principle of electromagnetic induction, a magnetic field is generated around the coil. This magnetic field attracts the armature, overcoming the spring's reaction force, causing the armature to move. The armature then moves the contacts, opening the normally closed contacts. The normally closed relay is now in the normally open state, preventing current and voltage signals from passing through it. This can be understood as follows: after the flight control computer's internal circuit 602 sends the first command to the normally closed relay 401, the switching state of the normally closed relay 401 changes from closed to open. Since the normally closed relay 401 and the magnetically latched relay 402 are connected in series, when the normally closed relay 401 is in the open state, the switching state of the aircraft power switch module 40 changes from closed to open, and the aircraft power supply 50 stops supplying power to the aircraft.

[0067] In this embodiment, the internal circuit of the flight control computer sends a first command to the normally closed relay, thereby controlling the switching state of the normally closed relay to switch from normally closed to normally open, which significantly improves the safety of the aircraft's power supply under extreme conditions.

[0068] Figure 5 This application provides a flowchart illustrating a method for powering on an aircraft. The method is applied to an aircraft power-on system, which includes: a ground power supply, a wireless power supply module transmitter, a wireless power supply module receiver, an aircraft power switch module, and an aircraft power supply. Figure 5 As shown, the method includes: S501, the wireless power supply module transmitter receives the first DC voltage signal output by the ground power supply and converts the first DC voltage signal into a magnetic field signal.

[0069] In this embodiment, the wireless power supply module transmitter converts the first DC voltage signal into an AC voltage signal using a PWM pulse width modulation signal and inputs the AC voltage signal into an LC resonant circuit. When the frequency of the AC voltage signal is close to the natural frequency of the LC resonant circuit, the inductor and capacitor in the LC resonant circuit resonate and obtain an AC current. According to Faraday's principle of electromagnetic induction, the changing current will generate an induced magnetic field, and the magnetic field signal of the induced magnetic field will be transmitted to the wireless power supply module receiver in the form of electromagnetic waves.

[0070] S502, the wireless power supply module receives the magnetic field signal and generates a second DC voltage signal based on the magnetic field signal; wherein, the voltage value of the second DC voltage signal includes the operating voltage value of the aircraft power switch module.

[0071] Specifically, in this embodiment of the application, the receiving end of the wireless power supply module is responsible for receiving the magnetic field signal emitted by the transmitting end of the wireless power supply module. The receiving end of the wireless power supply module contains coils that can sense changes in the magnetic field. When the magnetic field signal passes through these coils, an induced electromotive force is generated in the coils. The magnitude of the induced electromotive force is proportional to the rate of change of the magnetic field signal. Therefore, the magnitude of the induced electromotive force (AC voltage signal) can be optimized by adjusting parameters such as the relative position and frequency between the transmitting end and the receiving end.

[0072] Specifically, the wireless power supply module receiver converts the sensed AC voltage signal into a DC voltage signal through a rectifier bridge. It should be noted that the rectifier bridge converts the AC voltage signal into a DC voltage signal while maintaining the magnitude and direction of the DC voltage signal. After the rectifier bridge outputs the DC voltage signal, a filter circuit is typically used to remove high-frequency harmonics and noise from the rectified DC voltage signal, making the DC voltage signal smoother and more stable. After the filter circuit, a linear regulator circuit is usually installed. The linear regulator circuit can adjust the magnitude of the output DC voltage signal as needed to ensure that it meets the operating voltage requirements of the aircraft power switching module. It should be noted that the linear regulator circuit in this embodiment includes, but is not limited to, linear regulators, switching regulators, etc., and those skilled in the art can determine the appropriate type based on the specific circumstances.

[0073] Specifically, after rectification, filtering, and voltage regulation, the wireless power supply module receiver finally outputs a stable second DC voltage signal. The voltage value of the second DC voltage signal includes the operating voltage value of the aircraft power switch module and can be directly used to drive the aircraft power switch module.

[0074] S503, the aircraft power switch module receives the second DC voltage signal and switches from the open state to the closed state according to the voltage value of the second DC voltage signal, controlling the aircraft power supply to supply power to the aircraft.

[0075] In this embodiment, the aircraft power switch module receives a second DC voltage signal from the receiver of the wireless power supply module. If the detected voltage value reaches or exceeds a preset operating voltage threshold, the aircraft power switch module will switch from an open state to a closed state, controlling the aircraft power supply to supply power to the aircraft.

[0076] In some alternative embodiments, the power switch module may also include safety mechanisms such as overcurrent protection and overvoltage protection to ensure the safe operation of the aircraft power supply during power supply.

[0077] This application embodiment utilizes wireless power supply technology to remotely control the power-on process of the aircraft, improving the convenience and flexibility of operation. At the same time, the design of the wireless power supply module and the aircraft power switch module ensures the safety and reliability of power transmission and control, avoiding safety hazards caused by poor electrical connections or misoperation.

[0078] Based on the above embodiments, as an optional embodiment, the wireless power supply module receives a magnetic field signal and generates a second DC voltage signal based on the magnetic field signal, including: Based on the magnetic field signal, a first AC voltage signal is generated; The first AC voltage signal is converted into a third DC voltage signal, and the third DC voltage signal is regulated to obtain a second DC voltage signal.

[0079] In this embodiment, the receiving end of the wireless power supply module receives the magnetic field signal generated by the transmitting end through an induction coil. This magnetic field signal is a changing magnetic field, which will induce an electromotive force in the receiving end coil, thereby generating an AC voltage signal. Since the electronic equipment on the aircraft uses DC voltage, this embodiment converts the AC voltage signal into a DC voltage signal through a rectifier circuit. However, the DC voltage signal still has large fluctuations. In order to ensure that the output DC voltage is stable and reliable, this embodiment uses a linear voltage regulator circuit to regulate the rectified DC voltage to eliminate fluctuations in the DC voltage and output a stable DC voltage signal.

[0080] In this embodiment, the wireless power supply module receiver senses a magnetic field signal, converts it from AC to DC, and then regulates it to generate a stable DC voltage signal, thereby safely and reliably controlling the switching state of the aircraft power switch module.

[0081] Based on the above embodiments, as an optional embodiment, converting the first AC voltage signal into a third DC voltage signal includes: If the first power value is less than the second power value, a first signal is sent to the wireless power supply module. The first signal includes the second power value, so that the wireless power supply module adjusts the strength of the magnetic field signal output to the wireless power supply module receiver. The first power value is determined by the voltage value of the first AC voltage signal and the resistance value of the wireless power supply module receiver, and the second power value is the maximum power value that the wireless power supply module receiver is allowed to receive.

[0082] Specifically, in this embodiment, the second microcontroller calculates a first power value based on the voltage value of the first AC voltage signal and the resistance value of the wireless power supply module receiver; the calculated first power value is compared with the maximum power value that the wireless power supply module receiver is allowed to receive; if the first power value is less than the maximum power value that the wireless power supply module receiver is allowed to receive, then the second microcontroller sends a first message to the wireless power supply module transmitter; the wireless power supply module transmitter adjusts the strength of the output magnetic field signal according to the first message, so that the wireless power supply module receiver can operate at its maximum power.

[0083] In this embodiment, the receiving end of the wireless power supply module monitors the received power and sends first information to the transmitting end of the wireless power supply module when necessary, ensuring that the transmitting end of the wireless power supply module adjusts the duty cycle of the PWM pulse width modulation signal so that the power received by the receiving end of the wireless power supply module is equal to the maximum power value that it can receive. This power management and adjustment mechanism is an important component of the aircraft power supply system and is crucial to the stable and efficient operation of the aircraft power supply system.

[0084] Based on the above embodiments, as an optional embodiment, the system further includes a flight control computer; The aircraft power switch module receives a second DC voltage signal and switches from an open state to a closed state based on the voltage value of the second DC voltage signal, controlling the aircraft power supply to supply power to the aircraft. This also includes: The flight control computer sends a first command to the aircraft power switch module. The first command is used to instruct the aircraft power switch module to switch from a closed state to an open state, thereby controlling the aircraft power supply to stop supplying power to the aircraft.

[0085] In this embodiment, the aircraft power switch module receives a second DC voltage signal. When the voltage value reaches or exceeds its operating voltage threshold, the switching state of the aircraft power switch module changes from an open state to a closed state, allowing the aircraft power supply to provide power to the aircraft. Furthermore, when it is necessary to stop supplying power to the aircraft, the flight control computer sends a first instruction to the aircraft power switch module. The first instruction instructs the aircraft power switch module to change from a closed state to an open state, thereby cutting off the power supply to the aircraft.

[0086] In some optional embodiments, the aircraft power switch module includes a normally closed relay. The initial switching state of the normally closed relay is normally closed, at which time the switching state of the aircraft power switch module is closed. When the aircraft needs to stop power supply or perform maintenance in an emergency, the flight control computer sends a first instruction to the normally closed relay. The first instruction is used to instruct the normally closed relay to switch its switching state from normally closed to normally open, so that current and voltage cannot pass through the normally closed relay, thereby controlling the aircraft power supply to stop supplying power to the aircraft.

[0087] In this embodiment, when the aircraft needs to urgently stop power supply or perform maintenance, the flight control computer can quickly send commands to achieve precise control of the aircraft's power switch module. It can flexibly control the on / off of the aircraft's power supply according to the actual operating status and needs of the aircraft to meet different flight missions and maintenance requirements. At the same time, the entire power supply and power-off process can be completed automatically by the flight control computer, reducing manual intervention and improving the automation level of the aircraft's power-on system.

[0088] To facilitate a more intuitive and comprehensive understanding by those skilled in the art of the interaction process between various execution entities in the ground-based telemetry, tracking, and command system of this application, this application provides an interactive schematic diagram of an aircraft power-on method, as shown below. Figure 6 As shown, it includes the following steps: Step 601: The ground power supply sends a first DC voltage signal to the wireless power supply module; Step 602: The wireless power supply module transmitter converts the first DC voltage signal into a magnetic field signal; Step 603: The transmitter of the wireless power supply module sends a magnetic field signal to the receiver of the wireless power supply module; Step 604: The receiving end of the wireless power supply module sends the first information to the transmitting end of the wireless power supply module; Step 604: The wireless power supply module receiver sends the adjusted magnetic field signal; Step 606: The wireless power supply module receiver converts the magnetic field signal into a second DC voltage signal; Step 607: The wireless power supply module transmitter sends a second DC voltage signal to the aircraft power switch module; Step 608: The switching state of the aircraft power switch module is switched from the open state to the closed state, controlling the aircraft power supply to supply power to the aircraft; Step 609: The flight control computer sends the first command to the aircraft power switch module; Step 610: The aircraft power switch module switches the switch state from closed to open according to the first instruction, controlling the aircraft power supply to stop supplying power to the aircraft.

[0089] This application's embodiments enable remote control of the aircraft's power supply to be turned on and off, avoiding the risks associated with short-range power-on operations in existing technologies and effectively improving the safety of power-on operations. Furthermore, the aircraft is wirelessly connected to the ground, avoiding the impact of abnormal cable disconnection on aircraft launch, which is common in existing technologies.

[0090] Figure 7 This is a schematic diagram of the structure of an electronic device provided in an embodiment of this application, such as... Figure 7 As shown, the electronic device 4000 includes a processor 4001 and a memory 4003. The processor 4001 and the memory 4003 are connected, for example, via a bus 4002. Optionally, the electronic device 4000 may further include a transceiver 4004, which can be used for data interaction between the electronic device and other electronic devices, such as sending and / or receiving data. It should be noted that in practical applications, the transceiver 4004 is not limited to one type, and the structure of the electronic device 4000 does not constitute a limitation on the embodiments of this application.

[0091] Processor 4001 may be a CPU (Central Processing Unit), a general-purpose processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array), or other programmable logic devices, transistor logic devices, hardware components, or any combination thereof. It can implement or execute the various exemplary logic blocks, modules, and circuits described in conjunction with the disclosure of this application. Processor 4001 may also be a combination that implements computational functions, such as including one or more microprocessor combinations, a combination of a DSP and a microprocessor, etc.

[0092] Bus 4002 may include a pathway for transmitting information between the aforementioned components. Bus 4002 may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus, etc. Bus 4002 can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 7 The bus is represented by a single thick line, but this does not mean that there is only one bus or one type of bus.

[0093] The memory 4003 may be ROM (Read Only Memory) or other types of static storage devices capable of storing static information and instructions, RAM (Random Access Memory) or other types of dynamic storage devices capable of storing information and instructions, or EEPROM (Electrically Erasable Programmable Read Only Memory), CD-ROM (Compact Disc Read Only Memory) or other optical disc storage, optical disc storage (including compressed optical discs, laser discs, optical discs, digital universal optical discs, Blu-ray discs, etc.), magnetic disk storage media, other magnetic storage devices, or any other medium capable of carrying or storing computer programs and capable of being read by a computer, without limitation herein.

[0094] The memory 4003 is used to store computer programs that execute the embodiments of this application, and the execution is controlled by the processor 4001. The processor 4001 is used to execute the computer programs stored in the memory 4003 to implement the steps shown in the foregoing method embodiments.

[0095] The electronic device package may include, but is not limited to, mobile terminals such as mobile phones, laptops, digital radio receivers, PDAs (personal digital assistants), PADs (tablet computers), PMPs (portable multimedia players), and in-vehicle terminals (such as in-vehicle navigation terminals), as well as fixed terminals such as digital TVs and desktop computers. Figure 7 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of use of the embodiments disclosed herein.

[0096] This application provides a computer-readable storage medium storing a computer program. When the computer program is executed by a processor, it can implement the steps and corresponding content of the aforementioned method embodiments.

[0097] It should be noted that the computer-readable medium described in this disclosure can be a computer-readable signal medium, a computer-readable medium, or any combination thereof. A computer-readable storage medium can be, for example,—but not limited to—an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of a computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof. In this disclosure, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. In this disclosure, a computer-readable signal medium can include a data signal propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such propagated data signals can take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium can be any computer-readable medium other than a computer-readable storage medium, which can send, propagate, or transmit a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on the computer-readable medium can be transmitted using any suitable medium, including but not limited to: wires, optical fibers, RF (radio frequency), etc., or any suitable combination thereof.

[0098] This application also provides a computer program product, including a computer program that, when executed by a processor, can implement the steps and corresponding content of the aforementioned method embodiments. Compared with the prior art, it can achieve: The terms "first," "second," "third," "fourth," "1," "2," etc. (if present) in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this application described herein can be implemented in a sequence other than that shown in the illustrations or text descriptions.

[0099] It should be understood that although arrows indicate various operation steps in the flowcharts of this application's embodiments, the order in which these steps are implemented is not limited to the order indicated by the arrows. Unless explicitly stated herein, in some implementation scenarios of this application's embodiments, the implementation steps in each flowchart can be executed in other orders as required. Furthermore, some or all steps in each flowchart may include multiple sub-steps or multiple stages based on the actual implementation scenario. Some or all of these sub-steps or stages can be executed at the same time, and each sub-step or stage can also be executed at different times. In scenarios where execution times differ, the execution order of these sub-steps or stages can be flexibly configured according to requirements, and this application's embodiments do not limit this.

[0100] The above are only optional implementation methods for some implementation scenarios of this application. It should be noted that for those skilled in the art, other similar implementation methods based on the technical concept of this application, without departing from the technical concept of this application, also fall within the protection scope of the embodiments of this application.

Claims

1. An aircraft power supply system, characterized in that, The system includes: a ground power supply, a wireless power supply module transmitter, a wireless power supply module receiver, an aircraft power switch module, an aircraft power supply, and a flight control computer; the aircraft power switch module includes a magnetic latching relay and a normally closed relay, the normally closed relay being located between the aircraft power supply and the magnetic latching relay, and the initial switching state of the normally closed relay being closed; the wireless power supply module transmitter includes a first LC resonant circuit; the wireless power supply module receiver includes a second LC resonant circuit, a rectifier bridge, and a linear voltage regulator circuit; The wireless power supply module transmitter converts the first DC voltage signal output by the ground power supply into a magnetic field signal, and transmits the magnetic field signal wirelessly to the wireless power supply module receiver. The second LC resonant circuit generates a first AC voltage signal based on the magnetic field signal and outputs the first AC current-voltage signal to the rectifier bridge; wherein the voltage value of the first AC voltage signal is the same as the voltage value of the second DC voltage signal; the rectifier bridge converts the first AC voltage signal into a third DC voltage signal and outputs the third DC voltage signal to the linear voltage regulator circuit; the linear voltage regulator circuit regulates the third DC voltage signal to obtain a second DC voltage signal; wherein the voltage value of the second DC voltage signal includes the operating voltage value of the aircraft power switch module; When the voltage value of the second DC voltage signal is detected to reach or exceed the preset operating voltage threshold, the contacts of the magnetic latching relay close, the state of the aircraft power switch module changes from the open state to the closed state, and the aircraft power supply is controlled to supply power to the aircraft. The flight control computer sends a first instruction to the normally closed relay, the first instruction being used to instruct the normally closed relay to switch from a normally closed state to a normally open state; the normally closed relay receives the first instruction, switches from a normally closed state to a normally open state, and controls the aircraft power supply to stop supplying power to the aircraft.

2. The aircraft power supply system according to claim 1, characterized in that, The wireless power supply module transmitter also includes: a power full-bridge circuit and a first microcontroller; The first microcontroller generates a PWM pulse width modulation signal and outputs the PWM pulse width modulation signal to the power full-bridge circuit. The power full-bridge circuit converts the first DC voltage signal into a high-frequency square wave signal according to the PWM pulse width modulation signal, and outputs the high-frequency square wave signal to the first LC resonant circuit. The first LC resonant circuit filters the high-frequency square wave signal to obtain an alternating current. The alternating current generates an induced magnetic field, and the magnetic field signal of the induced magnetic field is sent to the receiving end of the wireless power supply module via electromagnetic waves.

3. The aircraft power supply system according to claim 2, characterized in that, The wireless power supply module receiver also includes a second microcontroller; The second microcontroller determines the power value of the second LC resonant circuit based on the first AC voltage signal and the resistance value of the receiving end of the wireless power supply module, and uses this as the first power value. If the first power value is less than the second power value, a first signal is sent to the transmitter of the wireless power supply module, the first signal including the second power value; wherein, the second power value is the maximum power value that the receiver of the wireless power supply module is allowed to receive; The first microcontroller acquires the first signal and adjusts the duty cycle of the PWM pulse width modulation signal output by the power full-bridge circuit according to the second power value; The first LC resonant circuit adjusts the strength of the magnetic field signal output to the receiver of the wireless power supply module according to the duty cycle adjusted by the PWM pulse width modulation signal. The second LC resonant circuit receives the adjusted magnetic field signal and adjusts the voltage value of the first AC voltage signal according to the strength of the adjusted magnetic field signal, thereby controlling the first power value to be the same as the second power value.

4. A method for powering on an aircraft, characterized in that, The method is applied to an aircraft power supply system, which includes: a ground power supply, a wireless power supply module transmitter, a wireless power supply module receiver, an aircraft power switch module, an aircraft power supply, and a flight control computer; the aircraft power switch module includes a magnetic latching relay and a normally closed relay, the normally closed relay being located between the aircraft power supply and the magnetic latching relay, and the initial switching state of the normally closed relay being closed; the method includes: The wireless power supply module transmitter receives the first DC voltage signal output by the ground power supply and converts the first DC voltage signal into a magnetic field signal. Based on the magnetic field signal, a first AC voltage signal is generated; if the first power value is less than the second power value, a first signal is sent to the wireless power supply module, the first signal including the second power value, so that the wireless power supply module adjusts the strength of the magnetic field signal output to the receiving end of the wireless power supply module. Wherein, the first power value is determined by the voltage value of the first AC voltage signal and the resistance value of the receiving end of the wireless power supply module, and the second power value is the maximum power value that the receiving end of the wireless power supply module is allowed to receive; the third DC voltage signal is regulated to obtain the second DC voltage signal; wherein, the voltage value of the second DC voltage signal includes the operating voltage value of the aircraft power switch module; When the voltage value of the second DC voltage signal is detected to reach or exceed the preset operating voltage threshold, the contacts of the magnetic latching relay close, the state of the aircraft power switch module changes from the open state to the closed state, and the aircraft power supply is controlled to supply power to the aircraft. The flight control computer sends a first instruction to the normally closed relay, the first instruction being used to instruct the normally closed relay to switch from a closed state to an open state, thereby controlling the aircraft power supply to stop supplying power to the aircraft.

5. An electronic device comprising a memory, a processor, and a computer program stored in the memory, characterized in that, The processor executes the computer program to implement the method of claim 4.

6. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the method of claim 4.

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