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

Abstract

The embodiment of the invention discloses an aircraft power-on system and method, electronic equipment and a storage medium, and relates 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; wherein the wireless power supply module transmitting end converts a first direct current voltage signal output by a 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 mode; the receiving end of the wireless power supply module receives the magnetic field signal and converts the magnetic field signal into a second direct-current voltage signal; and the aircraft power switch module receives the second direct-current voltage signal, switches from an off state to an on state according to the voltage value of the second direct-current voltage signal, and controls the aircraft power supply to supply power to the aircraft. According to the embodiment of the invention, the switching-on and switching-off of the aircraft power supply are controlled in a wireless connection mode, and the safety of switching on the aircraft power supply is effectively improved.

Description

Technical Field

[0001] This application relates to the technical field of aircraft, and more particularly, to an aircraft power-on system, method, electronic device, and storage medium. Background Art

[0002] In recent years, with the development of technology, aircraft have been more and more widely used; when an aircraft is launched, it is necessary to start the power supply on the aircraft to supply power to the aircraft to support the aircraft to complete flight operation requirements.

[0003] Currently, before an aircraft is launched, it is necessary to turn on the power supply on the aircraft; however, since the aircraft usually carries pyrotechnics, the safety of performing the power-on operation on the aircraft at close range is relatively low. And if a cable is used between the ground and the aircraft to control the power-on of the aircraft power supply, it is necessary to disconnect the connection cable between the ground and the aircraft before takeoff, and this method may cause abnormal separation of the cable, thus affecting the launch of the aircraft. Therefore, it is necessary to improve the safety of the aircraft power-on operation. Summary of the Invention

[0004] Embodiments of this application provide an aircraft power-on system, method, electronic device, and storage medium to improve the safety of the aircraft power-on operation.

[0005] According to a first aspect of the embodiments of this application, an aircraft power-on system is provided. The system includes: a ground power supply, a transmitting end of a wireless power supply module, a receiving end of the wireless power supply module, an aircraft power switch module, and an aircraft power supply; Wherein, the transmitting end of the wireless power supply module 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 receiving end of the wireless power supply module in a wireless manner; The receiving end of the wireless power supply module 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, switches from an off state to an on state according to the voltage value of the second DC voltage signal, and controls the aircraft power supply to supply power to the aircraft.

[0006] As an optional implementation manner, the transmitting end of the wireless power supply module includes: a power full-bridge circuit, a first LC resonance circuit, and a first microcontroller; Wherein, 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 resonance circuit; The first LC resonance 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 in the form of electromagnetic waves.

[0007] As an optional implementation manner, the receiving end of the wireless power supply module includes a second LC resonance circuit, a rectifier bridge, and a linear voltage regulator circuit; Wherein, the second LC resonance circuit generates a first AC voltage signal according to 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 stabilizes the third DC voltage signal to obtain a second DC voltage signal.

[0008] As an optional implementation manner, the receiving end of the wireless power supply module further includes a second microcontroller; Wherein, the second microcontroller determines the power value of the second LC resonance circuit according to the first AC voltage signal and the resistance value of the receiving end of the wireless power supply module as a first power value; If the first power value is less than the second power value, a first signal is sent to the transmitting end of the wireless power supply module, and the first signal includes the second power value; wherein, the second power value is the maximum power value allowed to be received by the receiving end of the wireless power supply module; 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 resonance circuit adjusts the intensity of the magnetic field signal output to the receiving end of the wireless power supply module according to the duty cycle after the PWM pulse-width modulation signal is adjusted; The second LC resonance circuit receives the adjusted magnetic field signal, and adjusts the voltage value of the first AC voltage signal according to the intensity of the adjusted magnetic field signal, so as to control the first power value to be the same as the second power value.

[0009] As an optional implementation manner, the aircraft power switch module includes a magnetic latching relay; Wherein, according to the voltage value of the second DC voltage signal, the contacts of the magnetic latching relay are closed, and the state of the aircraft power switch module is switched from the off state to the on state, controlling the aircraft power supply to supply power to the aircraft.

[0010] As an alternative embodiment, the system further includes a flight control computer; the aircraft power switch module further includes a normally closed relay, and the normally closed relay 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, and the first instruction is used to instruct the normally closed relay to switch from the normally closed state to the 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 the present application, a method for powering on an aircraft is provided. The method is applied to an aircraft power-on system, and the system includes: a ground power supply, a transmitting end of a wireless power supply module, a receiving end of the wireless power supply module, an aircraft power switch module, and an aircraft power supply; The method includes: The transmitting end of the wireless power supply module 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 receiving end of the wireless power supply module receives the magnetic field signal and generates a second DC voltage signal according to 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 the off state to the on state according to the voltage value of the second DC voltage signal, controlling the aircraft power supply to supply power to the aircraft.

[0012] As an alternative embodiment, the receiving end of the wireless power supply module receives the magnetic field signal and generates a second DC voltage signal according to the magnetic field signal, including: Generating a first AC voltage signal according to the magnetic field signal; Converting the first AC voltage signal into a third DC voltage signal, and stabilizing the voltage of the third DC voltage signal to obtain the second DC voltage signal.

[0013] As an alternative embodiment, the 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, and the first signal includes the second power value, so that the wireless power supply module adjusts the intensity 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 manner, the system further includes a flight control computer; The aircraft power switch module receives the second DC voltage signal, and switches from the off state to the on state according to the voltage value of the second DC voltage signal, controls the aircraft power supply to supply power to the aircraft, and then further includes: The flight control computer sends a first instruction to the aircraft power switch module, and the first instruction is used to instruct the aircraft power switch module to switch from the on state to the off state, and control the aircraft power supply to stop supplying power to the aircraft.

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

[0016] According to the fourth aspect of the embodiments of the present application, a computer-readable storage medium is provided, on which a computer program is stored, and when the computer program is executed by a processor, the method according to any one of the second aspects is implemented.

[0017] The beneficial effects brought by the technical solutions provided by the embodiments of the present application are: In the embodiments of the present application, the transmitting end of the wireless power supply module 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 receiving end of the wireless power supply module in a wireless manner; the receiving end of the wireless power supply module converts the magnetic field signal into a DC voltage signal through 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 the off state to the on state under the action of the DC voltage signal, and controls the aircraft power supply to supply power to the aircraft. The embodiments of the present application realize the remote control of the opening and closing of the aircraft power supply, avoid the risks brought by the close-range opening of the aircraft power supply in the prior art, and effectively improve the safety of the aircraft power-on operation; at the same time, the wireless connection between the aircraft and the ground avoids the abnormal separation of cables affecting the launch of the aircraft in the prior art. Description of the Drawings

[0018] To more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings required for the description of the embodiments of the present application.

[0019] Figure 1 Structural schematic diagram of the power-on system of the aircraft provided for the embodiments of the present application; Figure 2 Structural schematic diagram of the transmitting end of a wireless power supply module provided for the embodiments of the present application; Figure 3 Structural schematic diagram of the receiving end of a wireless power supply module provided for the embodiments of the present application; Figure 4 Structural schematic diagram of an aircraft power switch module, an aircraft power supply, and a flight control computer provided for the embodiments of the present application; Figure 5 Flow schematic diagram of a method for powering on an aircraft provided for the embodiments of the present application; Figure 6 Interaction schematic diagram of a method for powering on an aircraft provided for the embodiments of the present application; Figure 7 Structural schematic diagram of an electronic device provided for the embodiments of the present application. Detailed implementation manners

[0020] The following describes the embodiments of the present application in conjunction with the drawings in the present application. It should be understood that the embodiments described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application, and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0021] Those skilled in the art of the present technology can understand that, unless specifically stated otherwise, the singular forms "a", "an", and "the" used herein may also include the plural forms. It should be further understood that the terms "including" and "comprising" used in the embodiments of the present application mean that the corresponding features can be implemented as the presented features, information, data, steps, operations, elements, and / or components, but do not exclude the implementation of other features, information, data, steps, operations, elements, components, and / or their combinations, etc. supported by the art of the present technology. It should be understood that when we say 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. In addition, the "connection" or "coupling" used herein may include wireless connection or wireless coupling. The term "and / or" 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 implemented as "B", or implemented as "A and B".

[0022] In the embodiments of the present application, the term "module" or "unit" refers to a computer program with a predetermined function or a part of a computer program, which works together with other related parts to achieve a predetermined goal, and can be fully or partially implemented by using software, hardware (such as processing circuits or memories), or a combination thereof. Similarly, one processor (or multiple processors or memories) can be used to implement one or more modules or units. In addition, each module or unit can be a part of the overall module or unit that includes the functions of that module or unit.

[0023] To make the objectives, technical solutions, and advantages of the present application clearer, the following will further describe the embodiments of the present application in detail with reference to the accompanying drawings.

[0024] In recent years, with the development of technology, the application of aircraft has become more and more extensive; generally, an aircraft is equipped with a power supply, and when the aircraft is launched, it is necessary to start the power supply on the aircraft to supply power to the aircraft to support the aircraft to complete flight operation requirements.

[0025] Currently, before the aircraft is launched, it is necessary to turn on the power supply on the aircraft at close range; however, since the aircraft usually carries pyrotechnics, the safety of powering on the aircraft at close range is relatively low. And if a cable is used to connect between the ground and the aircraft to control the power-on of the aircraft power supply, it is necessary to disconnect the cable connecting the ground and the aircraft before the aircraft takes off, and this method may cause abnormal cable separation, thus affecting the launch of the aircraft. Therefore, it is necessary to improve the safety of the aircraft power-on operation.

[0026] The aircraft power-on system, method, electronic device, and storage medium provided by the present application are intended to solve the above technical problems in the prior art.

[0027] The following describes the technical solutions of the embodiments of the present application and the technical effects produced by the technical solutions of the present application through the description of several exemplary embodiments. It should be noted that the following embodiments can refer to, draw on, or combine with each other. For the same terms, similar features, and similar implementation steps in different embodiments, they will not be described repeatedly.

[0028] The embodiments of the present application provide an aircraft power-on system, and the system includes: a ground power supply, a transmitting end of a wireless power supply module, a receiving end of a wireless power supply module, an aircraft power switch module, and an aircraft power supply; Among them, the transmitting end of the wireless power supply module 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 receiving end of the wireless power supply module in a wireless manner; The receiving end of the wireless power supply module receives the magnetic field signal and converts the magnetic field signal into a second DC voltage signal; among them, the voltage value of the second DC voltage signal includes the working voltage value of the aircraft power switch module; The aircraft power switch module receives the second DC voltage signal, switches from the off state to the on state according to the voltage value of the second DC voltage signal, and controls the aircraft power supply to supply power to the aircraft.

[0029] Specifically, the embodiment of the present application provides a structural schematic diagram of an aircraft power-on system; as Figure 1 shown, the aircraft power-on system 100 includes: a ground power supply 10, a wireless power supply module transmitting end 20, and an aircraft 200; wherein the aircraft 200 includes: a wireless power supply module receiving end 30, an aircraft power switch module 40, an aircraft power supply 50, and a flight control computer 60.

[0030] In the embodiment of the present application, the ground power supply 10 is connected to the wireless power supply module transmitting end 20 to provide a first DC voltage signal to the wireless power supply module transmitting end 20. The wireless power supply module transmitting end 20 converts the first DC electrical signal provided by the ground power supply 10 into a magnetic field signal, and sends the magnetic field signal to the wireless power supply module receiving end 30 in a wireless manner, realizing the wireless connection between the aircraft 200 and the ground, and avoiding the technical problem that the aircraft 200 affects the launch due to the failure of cable separation in the prior art. The wireless power supply module receiving end 30 is connected to the aircraft power switch module 40; after receiving the magnetic field signal, the wireless power supply module receiving end 30 converts the magnetic field signal into a second DC voltage signal and outputs the second DC voltage signal to the aircraft power switch module 40. The aircraft power switch module 40 switches from the off state to the on state according to the second DC voltage signal input by the wireless power supply module receiving end 30, and controls the aircraft power supply 50 to supply power to the aircraft 200, realizing the remote control of the aircraft power supply to turn on, and effectively improving the safety of the aircraft power-on operation.

[0031] In the embodiment of the present application, the ground power supply 10 and the wireless power supply module transmitting end 20 are arranged outside the aircraft 200; the wireless power supply module receiving end 30, the aircraft power switch module 40, the aircraft power supply 50, and the flight control computer 60 are arranged inside the aircraft; wherein, the wireless power supply module transmitting end 20 and the wireless power supply module receiving end 30 are placed opposite to each other; wherein, being placed opposite to each other means that the wireless power supply module transmitting end 20 and the wireless power supply module receiving end 30 maintain the state of geometric center coincidence or maximum overlap of the magnetic field coupling area in space; for example, the planes of the wireless power supply module transmitting end 20 and the wireless power supply module receiving end 30 are parallel and the center points completely coincide.

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

[0033] Furthermore, as Figure 1 shown, in the embodiment of the present 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, and the aircraft power supply 50 supplies power to the aircraft 200, including supplying power to the flight control computer 60.

[0034] In an alternative embodiment, the aircraft further includes other modules, including but not limited to: explosive initiators, servos, servo controllers, etc. ( Figure 1 not shown in the figure); when the aircraft 200 includes the above modules, the aircraft power supply supplying power to the aircraft further includes supplying power to the above modules; those skilled in the art can determine the types and quantities of other modules on the aircraft according to the actual situation.

[0035] In an alternative embodiment, the aircraft power switch module can be a separate module in the aircraft, and can also be arranged inside the flight control computer or other modules; those skilled in the art can set the position of the aircraft power switch module according to the actual situation.

[0036] The embodiment of the present application realizes remote control of the opening and closing of the aircraft power supply, avoids the risks brought by the close-range opening of the aircraft power supply in the prior art, and effectively improves the safety of the power-on operation of the aircraft power supply; at the same time, the wireless connection is used between the aircraft and the ground, avoiding the abnormal separation of cables affecting the launch of the aircraft in the prior art.

[0037] Based on the above embodiments, as an alternative embodiment, the transmitting end of the wireless power supply module includes: a power full-bridge circuit, a first LC resonance circuit, and a first microcontroller; wherein, 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 full - bridge power 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 resonance circuit; The first LC resonance 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 in the form of electromagnetic waves.

[0038] Specifically, an embodiment of the present application provides a schematic structural diagram of the transmitting end of a wireless power - supply module, as Figure 2 shown. The transmitting end 20 of the wireless power - supply module includes: a first micro - controller 201, a full - bridge power circuit 202, and a first LC resonance circuit 203.

[0039] Specifically, in the embodiment of the present application, the full - bridge power circuit 202 is connected to the ground power supply, and the first LC resonance circuit 203 is connected to the receiving end of the wireless power - supply module. Among them, the full - bridge power circuit 202 receives the DC voltage signal sent by the ground power supply; the first micro - controller 201 generates a PWM pulse - width modulation signal and sends the PWM pulse - width modulation signal to the full - bridge power circuit 202, controlling the full - bridge power circuit 202 to generate a high - frequency square - wave signal according to the received DC voltage signal and the PWM pulse - width modulation signal and output the high - frequency square - wave signal to the first LC resonance circuit 203. When the frequency of the high - frequency square - wave signal approaches the natural resonance frequency of the first LC resonance circuit 203, the inductor and capacitor in the first LC resonance circuit 203 resonate, and the energy between the inductor and capacitor is exchanged periodically. After the high - frequency square - wave signal passes through LC resonance, the harmonic components are filtered out to obtain an alternating current, and the waveform of the alternating current is approximately a sine wave. According to Faraday's law of electromagnetic induction, a changing current will generate an induced magnetic field, and the magnetic - field signal of the induced magnetic field is transmitted to the receiving end of the wireless power - supply module in the form of electromagnetic waves.

[0040] In some alternative embodiments, the ground power supply outputs a 12V DC voltage signal; the first micro - controller 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 (with a frequency of 140KHz) according to 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; wherein, 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 period to the entire period time. For example, when the preset duty cycle is 15%, the duration of the high level within one period accounts for 15% of the entire period time, and the remaining 85% of the period time is the duration of the low level. In the embodiments of the present application, the power full-bridge circuit is provided with MOS transistors. When the PWM pulse width modulation signal is at a high level, the MOS transistors are turned on, and the power full-bridge circuit generates a high-level signal; when the PWM pulse width modulation signal is at a low level, the MOS transistors are turned off, and the power full-bridge circuit generates a low-level signal; combining the high-level signal and the low-level signal within one period results in a square wave signal.

[0042] It should also be noted that in the embodiments of the present 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 the embodiments of the present application, 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 resonance 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 in the form of electromagnetic waves, realizing wireless power transmission.

[0044] Based on the above embodiments, as an optional embodiment, the receiving end of the wireless power supply module includes a second LC resonance circuit, a rectifier bridge, and a linear voltage regulator circuit; wherein, the second LC resonance circuit generates a first alternating voltage signal according to the magnetic field signal and outputs the first alternating current voltage signal to the rectifier bridge; wherein, the voltage value of the first alternating voltage signal is the same as the voltage value of the second DC voltage signal; The rectifier bridge converts the first alternating 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 stabilizes the third DC voltage signal to obtain a second DC voltage signal.

[0045] Specifically, the embodiments of the present application provide a structural schematic diagram of the receiving end of the wireless power supply module, as Figure 3 shown, the receiving end 30 of the wireless power supply module includes: a second microcontroller 301, a second LC resonance circuit 302, a rectifier bridge 303, and a linear voltage regulator circuit 304.

[0046] Specifically, in the embodiments of the present application, the receiving end 30 of the wireless power supply module is arranged inside the aircraft, and the transmitting end of the wireless power supply module is arranged outside the aircraft. The first LC resonance circuit of the transmitting end of the wireless power supply module transmits the magnetic field signal to the second LC resonance circuit 302 of the receiving end 30 of the wireless power supply module in the form of electromagnetic waves. Among them, the second LC resonance circuit 302 is provided with a capacitor and an inductor. When the magnetic field signal acts on the second LC resonance circuit 302, an induced electromotive force will be generated in the inductor, and at the same time, charge and discharge will occur in the capacitor to form a current. When the capacitor discharges, the current flows through the inductor, and the inductor stores magnetic field energy. When the current decreases, the inductor will generate a reverse electromotive force to continue charging the capacitor, but with the opposite polarity, forming a first AC voltage signal, and outputting the first AC voltage signal 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 realizes stable output voltage by adjusting the resistance or current inside the circuit. The linear voltage regulator circuit 304 stabilizes the third DC voltage signal to obtain a second DC voltage signal, and outputs the second DC voltage signal to the aircraft power switch module. It should be noted that in the embodiments of the present application, the second DC voltage signal is the operating voltage of the aircraft power switch module, which controls the on-off state of the aircraft power switch module.

[0047] In the embodiments of the present application, the second LC resonance circuit, the rectifier bridge, and the linear voltage regulator circuit of the receiving end of the wireless power supply module cooperate 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] On the basis of the above embodiments, as an optional embodiment, the receiving end of the wireless power supply module further includes a second microcontroller; Among them, the second microcontroller determines the power value of the second LC resonance circuit according to the first AC voltage signal and the resistance value of the receiving end of the wireless power supply module as the first power value; If the first power value is less than the second power value, a first signal is sent to the transmitting end of the wireless power supply module. The first signal includes the second power value. Among them, the second power value is the maximum power value that the receiving end of the wireless power supply module allows to receive; The first microcontroller obtains 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 resonance circuit adjusts the intensity of the magnetic field signal output to the receiving end of the wireless power supply module according to the adjusted duty cycle of 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 intensity 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 the embodiment of the present application, the second microcontroller determines the power value transmitted from the transmitting end of the wireless power supply module as the first power value according to the voltage value of the first AC voltage signal and the equivalent resistance value of the coil of the wireless power supply module; when the first power value is less than the maximum power value allowed to be received by the receiving end of the wireless power supply module, the receiving end of the wireless power supply module sends a first signal to the transmitting end of the wireless power supply module, where the first signal includes the maximum power value allowed to be received by the receiving end of the wireless power supply module; after receiving the first signal, the transmitting end of the wireless power supply module adjusts the duty cycle of the PWM pulse width modulation signal according to the maximum power value allowed to be received by the receiving end of the wireless power supply module, so as to adjust the power value transmitted from the transmitting end of the wireless power module to the receiving end of the wireless power supply module.

[0050] The following is illustrated by a specific example.

[0051] Example 1: Initially, the first microcontroller at the transmitting end of the wireless power supply module sets the frequency of the PWM pulse width modulation signal to 140 kHz, the duty cycle to 15%, the voltage value of the DC voltage signal of the ground power supply to 12 V, and the equivalent resistance of the coil at the transmitting end of the wireless power supply module is . Under this condition, the voltage output by the coil at the transmitting end of the wireless power supply module is: , at this time, the power at the transmitting end of the wireless power supply module is: ; without considering the electromagnetic conversion process at the transmitting end 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 receiving end of the wireless power supply module is approximately equal to 5 W. Assuming that the maximum power value allowed to be received by the receiving end of the wireless power supply module is 15 W, the maximum power allowed to be received by the receiving end of the wireless power supply module (such as 15 W) is fed back to the transmitting end of the wireless power supply module. After receiving the maximum power requirement of 15 W, the first microcontroller at the transmitting end of the wireless power supply module, since 15 W is three times that of 5 W; therefore, the duty cycle of the PWM pulse width modulation signal is adjusted to 3 times the original, that is: the duty cycle of the PWM pulse width modulation signal is set to 45%; in this way, the conduction time of the MOS tube in the power full-bridge circuit is increased. At this time, the output power of the transmitting end of the wireless power supply module is , which is the same as the maximum power allowed to be received by the receiving end of the wireless power supply module. Assuming that the equivalent resistance of the coil at the receiving end of the wireless power supply module is the same as that of the coil at the transmitting end of the wireless power supply module, both being 4.35 Ω, when the receiving end of the wireless power supply module receives 15 W of energy, a 12 V DC voltage signal is output after passing through the rectifier bridge and the linear voltage regulator circuit.

[0052] It should be noted that, in addition to the second LC resonance circuit, the receiving end of the wireless power supply module further includes a rectifier bridge and a linear voltage regulator circuit; wherein, 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 to output a stable 12V DC voltage signal, so as to control the switching state of the aircraft power switch module.

[0053] In the embodiment of the present application, the receiving end of the wireless power supply module sends the maximum power value that it allows to receive to the transmitting end of the wireless power supply module, so that the wireless power supply module can dynamically adjust the duty cycle of the PWM pulse width modulation signal according to the actual requirements of the receiving end of the wireless power supply module, ensuring that the power received by the receiving end of the wireless power supply module is the same as the maximum power it allows to receive, and 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; Wherein, according to the voltage value of the second DC voltage signal, the contacts of the magnetic latching relay are closed, and the state of the aircraft power switch module is switched from the off state to the on state, controlling the aircraft power supply to supply power to the aircraft.

[0055] Specifically, the embodiment of the present application provides a schematic structural diagram of an aircraft power switch module, an aircraft power supply, and a flight control computer; as Figure 4 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 of the flight control computer; wherein, the magnetic latching relay 402 is respectively connected to the receiving end 30 of the wireless power supply module and the diode 601; the normally closed relay 401 is respectively connected to the aircraft power supply 50, the magnetic latching relay 402, and the internal circuit 602 of the flight control computer.

[0056] In the embodiment of the present application, 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 to maintain. When a short pulse current is applied externally through the coil, the magnetic system inside the magnetic latching relay 402 will change, thereby switching the state of the contacts.

[0057] A resistor is provided between the receiving end 30 of the wireless power supply module and the magnetic latching relay 402. The receiving end 30 of the wireless power supply module generates a current through this resistor. When this 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 maintain the current switching state.

[0058] Specifically, in the embodiments of the present application, the preset switch state of the magnetic latching relay 402 is the open state. When a current acts on the magnetic latching relay 402, the switch state of the magnetic latching relay 402 changes from the open state to the closed state.

[0059] Specifically, in the embodiments of the present application, the normally closed relay 401 and the magnetic latching relay 402 are connected in series, and the initial switch state of the normally closed relay 401 is the closed state; therefore, when the switch state of the magnetic latching relay 402 changes from the open state to the closed state, the switch 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 further includes some other modules, including but not limited to: squib initiator, servo, servo controller, etc.; the aircraft power supply supplies power to the aircraft, and also includes supplying power to the above modules.

[0061] In the embodiments of the present application, in the aircraft power switch module, the magnetic latching relay is used to control the on and off of the power supply. By inputting a current to the magnetic latching relay, the contacts of the magnetic latching relay are controlled to change from the open state to the closed state; and the contacts of the magnetic latching relay are locked by a spring in the closed state, and can still maintain the suction state even after power-off, having high stability and reliability, and controlling the aircraft power supply to continuously and stably supply power to the aircraft.

[0062] Based on the above embodiments, as an alternative embodiment, the system further includes a flight control computer; the aircraft power switch module further includes a normally closed relay, and the normally closed relay 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, and the first instruction is used to instruct the normally closed relay to change from the normally closed state to the normally open state; The normally closed relay receives the first instruction and changes from the normally closed state to the normally open state, controlling the aircraft power supply to stop supplying power to the aircraft.

[0063] As Figure 4 shown, the internal circuit 602 of the flight control computer includes a CPU and / or a control circuit, and can generate an instruction signal; when it is necessary to stop the aircraft power supply 50 from supplying power to the aircraft, the internal circuit 602 of the flight control computer sends a first instruction to the normally closed relay 401, and the first instruction is used to instruct the switch state of the normally closed relay to change 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. Among them, the coil is usually wound with insulated wire and is the key part for generating a magnetic field. The iron core is used to enhance the magnetic field generated by the coil. The armature can move under the action of the magnetic field, driving the closing or opening of the contacts. The contacts are divided into normally closed contacts and normally open contacts. The normally closed contacts are in the closed state when the relay is not powered on and open after being powered on, while the normally open contacts are the opposite. The spring is used to restore the armature to the initial position when the relay is powered off.

[0065] Specifically, in the embodiment of the present application, when the relay coil of the normally closed relay 401 is not powered on, there is no current flowing through the coil, so no magnetic field is generated. Under the action of the spring, the armature remains in the initial position. At this time, the normally closed contacts are closed, and the normally closed relay is in the normally closed state. Current signals and voltage signals can pass through the normally closed relay. It can be understood that in the embodiment of the present application, the initial switch state of the normally closed relay 401 is the closed state.

[0066] Specifically, when the internal circuit 602 of the flight control computer sends a first instruction to the normally closed relay 401, the coil of the normally closed relay 401 is powered on, and current passes through the coil. According to the principle of electromagnetic induction, a magnetic field is generated around the coil. The magnetic field generates an attractive force on the armature, overcoming the reaction force of the spring, causing the armature to move. The armature drives the contacts to act, and the normally closed contacts open. The normally closed relay is in the normally open state, and current signals and voltage signals cannot pass through the normally closed relay. It can be understood that when the internal circuit 602 of the flight control computer sends a first instruction to the normally closed relay 401, the switch state of the normally closed relay 401 changes from the closed state to the open state. Since the normally closed relay 401 and the magnetic latching relay 402 are connected in series. Therefore, when the switch state of the normally closed relay 401 is the open state, the switch state of the aircraft power switch module 40 changes from the closed state to the open state, and the aircraft power supply 50 stops supplying power to the aircraft.

[0067] In the embodiment of the present application, the internal circuit of the flight control computer controls the switch state of the normally closed relay to change from the normally closed state to the normally open state by sending a first instruction to the normally closed relay, significantly improving the safety of the aircraft power supply under extreme working conditions.

[0068] Figure 5 It is a schematic flowchart of a method for powering on an aircraft provided by an embodiment of the present application. This method is applied to an aircraft power-on system, which includes: a ground power supply, a transmitting end of a wireless power supply module, a receiving end of a wireless power supply module, an aircraft power switch module, and an aircraft power supply. As Figure 5 shown, this method includes: S501. The transmitting end of the wireless power supply module 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 the embodiment of the present application, the transmitting end of the wireless power supply module converts the first DC voltage signal into an AC voltage signal through a PWM pulse width modulation signal, and inputs the AC voltage signal into the 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 to obtain an AC current. According to Faraday's law of electromagnetic induction, a changing current will generate an induced magnetic field, and the magnetic field signal of the induced magnetic field is transmitted to the receiving end of the wireless power supply module 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 according to 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 the embodiment of the present 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. Inside the receiving end of the wireless power supply module, there is a coil capable of sensing magnetic field changes. When the magnetic field signal passes through these coils, an induced electromotive force will be generated in the coils. The magnitude of the induced electromotive force is proportional to the change rate 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 receiving end of the wireless power supply module converts the sensed AC voltage signal into a DC voltage signal through a rectifier bridge. It should be noted that the role of the rectifier bridge is to convert the AC voltage signal into a DC voltage signal while keeping the magnitude and direction of the DC voltage signal unchanged; after the rectifier bridge outputs the DC voltage signal, a filter circuit is usually set to remove the high-frequency harmonics and noise in the rectified DC voltage signal to make the DC voltage signal smoother and more stable; after the filter circuit, a linear voltage regulator circuit is usually set. The linear voltage 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 switch module. It should be noted that in the embodiment of the present application, the linear voltage regulator circuit includes but is not limited to types such as linear voltage regulators and switching voltage regulators, and those skilled in the art can determine according to the actual situation.

[0073] Specifically, after rectification, filtering, and voltage regulation, the receiving end of the wireless power supply module 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 off state to the on 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 the embodiments of the present application, the aircraft power switch module receives a second DC voltage signal from the receiving end of the wireless power supply module. If the detected voltage value reaches or exceeds the preset operating voltage threshold, the aircraft power switch module will switch from the off state to the on 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 the power supply process.

[0077] Through the wireless power supply technology, the embodiments of the present application can remotely control the power-on process of the aircraft, improving the convenience and flexibility of operation; at the same time, the designs of the wireless power supply module and the aircraft power switch module ensure the safe and reliable transmission and control of electric energy, avoiding potential safety hazards caused by poor electrical connections or misoperations.

[0078] Based on the above embodiments, as an alternative embodiment, the wireless power supply module receives a magnetic field signal and generates a second DC voltage signal according to the magnetic field signal, including: Generating a first AC voltage signal according to the magnetic field signal; Converting the first AC voltage signal into a third DC voltage signal, and stabilizing the third DC voltage signal to obtain the second DC voltage signal.

[0079] In the embodiments of the present application, the receiving end of the wireless power supply module receives the magnetic field signal generated by the transmitting end through the induction coil. This magnetic field signal is a changing magnetic field, which will generate an induced electromotive force in the receiving end coil, thereby generating an AC voltage signal; since the electronic devices on the aircraft use DC voltage; therefore, in the embodiments of the present application, the rectifier circuit is used to convert the AC voltage signal into a DC voltage signal, but there are still large fluctuations in the DC voltage signal at this time; in order to ensure the stable and reliable output of the DC voltage, the embodiments of the present application use a linear voltage regulator circuit to stabilize the rectified DC voltage to eliminate the fluctuations in the DC voltage and output a stable DC voltage signal.

[0080] In the embodiments of the present application, the receiving end of the wireless power supply module receives the magnetic field signal, and through the conversion from AC to DC and voltage stabilization processing, finally generates 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 alternative 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, send a first signal to the wireless power supply module. The first signal includes the second power value, so that the wireless power supply module adjusts the intensity 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 allows to receive.

[0082] Specifically, in the embodiment of the present application, the second microcontroller calculates the first power value according to the voltage value of the first AC voltage signal and the resistance value of the receiving end of the wireless power supply module; compares the calculated first power value with the maximum power value that the receiving end of the wireless power supply module allows to receive. If the first power value is less than the maximum power value that the receiving end of the wireless power supply module allows to receive, send a first message to the transmitting end of the wireless power supply module; the transmitting end of the wireless power supply module adjusts the intensity of the output magnetic field signal according to the first message, so that the receiving end of the wireless power supply module can operate at its own maximum power.

[0083] In the embodiment of the present application, the receiving end of the wireless power supply module monitors the received power and sends a first message 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 allows to receive; this power management and adjustment mechanism is an important part of the aircraft power-on system and is crucial for the stable and efficient operation of the aircraft power-on system.

[0084] On the basis of the above embodiments, as an optional embodiment, the system further includes a flight control computer. The aircraft power switch module receives the second DC voltage signal and switches from the off state to the on state according to the voltage value of the second DC voltage signal, controlling the aircraft power supply to supply power to the aircraft. After that, it further includes: The flight control computer sends a first instruction to the aircraft power switch module. The first instruction is used to instruct the aircraft power switch module to switch from the on state to the off state, controlling the aircraft power supply to stop supplying power to the aircraft.

[0085] In the embodiment of the present application, the aircraft power switch module receives the second DC voltage signal. When the voltage value reaches or exceeds its operating voltage threshold, the switch state of the aircraft power switch module switches from the off state to the on state, allowing the aircraft power supply to supply power to the aircraft. Further, 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 is used to instruct the aircraft power switch module to switch from the on state to the off state, thereby cutting off the power supply of the aircraft.

[0086] In some alternative embodiments, the aircraft power switch module includes a normally closed relay. The initial switch state of the normally closed relay is the normally closed state. At this time, the switch state of the aircraft power switch module is the closed state. When the aircraft needs to stop power supply urgently or perform maintenance, the flight control computer sends a first instruction to the normally closed relay. The first instruction is used to indicate that the switch state of the normally closed relay changes from the normally closed state to the normally open state, and the 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 the embodiments of the present application, when the aircraft needs to stop power supply urgently or perform maintenance, the flight control computer can quickly send an instruction, achieving precise control of the aircraft power switch module. It can flexibly control the on / off of the aircraft power supply according to the actual operating state and requirements of the aircraft to meet different flight missions and maintenance needs. At the same time, the entire power supply and power-off process can be automatically completed by the flight control computer, reducing manual intervention and improving the automation level of the aircraft power-on system.

[0088] To facilitate those skilled in the art to more intuitively and comprehensively understand the interaction process between each execution entity in the ground measurement, launch, and control system in the embodiments of the present application, the embodiments of the present application provide an interaction schematic diagram of an aircraft power-on method, as Figure 6 shown, including the following steps: Step 601: The ground power supply sends a first DC voltage signal to the wireless power supply module; Step 602: The transmitting end of the wireless power supply module converts the first DC voltage signal into a magnetic field signal; Step 603: The transmitting end of the wireless power supply module sends the magnetic field signal to the receiving end of the wireless power supply module; Step 604: The receiving end of the wireless power supply module sends a first message to the transmitting end of the wireless power supply module; Step 604: The receiving end of the wireless power supply module sends an adjusted magnetic field signal; Step 606: The receiving end of the wireless power supply module converts the magnetic field signal into a second DC voltage signal; Step 607: The transmitting end of the wireless power supply module sends a second DC voltage signal to the aircraft power switch module; Step 608: The switch 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; Step 609: The flight control computer sends a first instruction to the aircraft power switch module; Step 610: The aircraft power switch module changes the switch state from the closed state to the open state according to the first instruction, controlling the aircraft power supply to stop supplying power to the aircraft.

[0089] The embodiments of the present application achieve the opening and closing of the power supply of the remote-controlled aircraft, avoiding the risks brought by the close-range opening of the aircraft power supply in the prior art, and effectively improving the safety of the power-on operation of the aircraft power supply. Further, the aircraft and the ground are connected wirelessly, avoiding the abnormal separation of cables from affecting the launch of the aircraft in the prior art.

[0090] Figure 7 FIG. is a schematic structural diagram of an electronic device provided by an embodiment of the present application, as Figure 7 shown, the electronic device 4000 includes: a processor 4001 and a memory 4003. Among them, the processor 4001 and the memory 4003 are connected, such as connected through a bus 4002. Optionally, the electronic device 4000 may further include a transceiver 4004, and the transceiver 4004 may be used for data interaction between the electronic device and other electronic devices, such as sending and / or receiving data, etc. It should be noted that in practical applications, the transceiver 4004 is not limited to one, and the structure of the electronic device 4000 does not constitute a limitation to the embodiments of the present application.

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

[0092] The bus 4002 may include a path for transmitting information between the above components. The bus 4002 may be a PCI (Peripheral Component Interconnect, peripheral component interconnect standard) bus or an EISA (Extended Industry Standard Architecture, extended industry standard architecture) bus, etc. The bus 4002 may be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 7 only a thick line is used to represent it in the figure, but it does not mean that there is only one bus or one type of bus.

[0093] The memory 4003 can be a ROM (Read Only Memory), or other types of static storage devices that can store static information and instructions, a RAM (Random Access Memory), or other types of dynamic storage devices that can store information and instructions. It can also be an EEPROM (Electrically Erasable Programmable Read Only Memory), a CD-ROM (Compact Disc Read Only Memory), or other optical disc storage, optical disc storage (including compact discs, laser discs, optical discs, digital versatile discs, Blu-ray discs, etc.), magnetic disk storage media, other magnetic storage devices, or any other medium that can be used to carry or store computer programs and can be read by a computer, which is not limited herein.

[0094] The memory 4003 is used to store the computer program for implementing the embodiments of the present application and is controlled by the processor 4001 to execute. The processor 4001 is used to execute the computer program stored in the memory 4003 to implement the steps shown in the foregoing method embodiments.

[0095] Among them, the electronic device package may include, but is not limited to, mobile terminals such as mobile phones, laptop computers, digital broadcast receivers, PDAs (Personal Digital Assistants), PADs (Tablet Computers), PMPs (Portable Multimedia Players), in-vehicle terminals (such as in-vehicle navigation terminals), etc., and fixed terminals such as digital TVs, desktop computers, etc. Figure 7 The shown electronic device is only an example and should not bring any limitation to the functions and usage scope of the embodiments of the present disclosure.

[0096] The embodiments of the present application provide a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the steps and corresponding contents shown in the foregoing method embodiments can be implemented.

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

[0098] The embodiments of the present application also provide a computer program product, including a computer program, and when the computer program is executed by a processor, it can implement the steps and corresponding content of the foregoing method embodiments. Compared with the prior art, it can achieve: The terms "first", "second", "third", "fourth", "1", "2", etc. (if any) in the specification, claims, and the above-mentioned drawings of the present application are used to distinguish similar objects and do not necessarily describe a specific order or sequence. It should be understood that the data used in this way can be interchanged under appropriate circumstances so that the embodiments of the present application described here can be implemented in an order other than the one illustrated or described in words.

[0099] It should be understood that although the flowcharts of the embodiments of the present application indicate each operation step by arrows, the execution order of these steps is not limited to the order indicated by the arrows. Unless otherwise clearly stated in this article, in some implementation scenarios of the embodiments of the present application, the implementation steps in each flowchart can be executed in other orders according to requirements. In addition, some or all of the 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 among these sub-steps or stages can also be executed at different times respectively. In the scenario where the execution times are different, the execution order of these sub-steps or stages can be flexibly configured according to requirements, and the embodiments of the present application do not limit this.

[0100] The above are only optional implementation manners of some implementation scenarios of the present application. It should be noted that for those of ordinary skill in the art, without departing from the technical concept of the solution of the present application, using other similar implementation means based on the technical idea of the present application also belongs to the protection scope of the embodiments of the present application.

Claims

1. An aircraft power-on system, characterized in that, The system includes: a ground power supply, a transmitting end of a wireless power supply module, a receiving end of the wireless power supply module, an aircraft power switch module, and an aircraft power supply; Among them, the transmitting end of the wireless power supply module 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 receiving end of the wireless power supply module in a wireless manner; The receiving end of the wireless power supply module receives the magnetic field signal and converts the magnetic field signal into a second DC voltage signal; among them, 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, switches from an off state to an on state according to the voltage value of the second DC voltage signal, and controls the aircraft power supply to supply power to the aircraft.

2. The aircraft power-on system according to claim 1, wherein The transmitting end of the wireless power supply module includes: a power full-bridge circuit, a first LC resonance circuit, and a first microcontroller; Among them, 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 resonance circuit; The first LC resonance 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 by means of electromagnetic waves.

3. The aircraft power-on system according to claim 2, characterized in that, The receiving end of the wireless power supply module includes a second LC resonance circuit, a rectifier bridge, and a linear voltage regulator circuit; Among them, the second LC resonance circuit generates a first AC voltage signal according to the magnetic field signal, and outputs the first AC current voltage signal to the rectifier bridge; among them, 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 stabilizes the third DC voltage signal to obtain a second DC voltage signal.

4. The aircraft power-on system according to claim 3, wherein, The receiving end of the wireless power supply module further includes a second microcontroller; Among them, the second microcontroller determines the power value of the second LC resonance circuit as a first power value according to the first AC voltage signal and the resistance value of the receiving end of the wireless power supply module; If the first power value is less than the second power value, a first signal is sent to the transmitting end of the wireless power supply module, and the first signal includes the second power value; among them, the second power value is the maximum power value allowed to be received by the receiving end of the wireless power supply module; The first microcontroller obtains 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 resonance circuit adjusts the intensity of the magnetic field signal output to the receiving end of the wireless power supply module according to the adjusted duty cycle of 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 intensity of the adjusted magnetic field signal, so as to control the first power value to be the same as the second power value.

5. The aircraft power-on system according to claim 3, wherein, The aircraft power switch module includes a magnetic latching relay; Wherein, according to the voltage value of the second DC voltage signal, the contacts of the magnetic latching relay are closed, and the state of the aircraft power switch module is switched from the off state to the on state, so as to control the aircraft power supply to supply power to the aircraft.

6. The aircraft power-on system according to claim 5, characterized in that, The system further includes a flight control computer; the aircraft power switch module further includes a normally closed relay, and the normally closed relay 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, and the first instruction is used to instruct the normally closed relay to switch from the normally closed state to the normally open state; The normally closed relay receives the first instruction and switches from the normally closed state to the normally open state, so as to control the aircraft power supply to stop supplying power to the aircraft.

7. A method for powering on an aircraft, characterized in that, The method is applied to an aircraft power-on system, and the system includes: a ground power supply, a transmitting end of a wireless power supply module, a receiving end of the wireless power supply module, an aircraft power switch module, and an aircraft power supply; The method includes: The transmitting end of the wireless power supply module 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 according to 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 the off state to the on state according to the voltage value of the second DC voltage signal, so as to control the aircraft power supply to supply power to the aircraft.

8. The aircraft power-on method according to claim 7, wherein The wireless power supply module receives the magnetic field signal and generates a second DC voltage signal according to the magnetic field signal, including: Generating a first AC voltage signal according to the magnetic field signal; Converting the first AC voltage signal into a third DC voltage signal, and stabilizing the voltage of the third DC voltage signal to obtain the second DC voltage signal.

9. The aircraft power-on method according to claim 8, wherein The 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, sending a first signal to the wireless power supply module, and the first signal includes a second power value, so that the wireless power supply module adjusts the intensity 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 allowed to be received by the receiving end of the wireless power supply module.

10. The aircraft power-on method according to claim 8, wherein The system further includes a flight control computer; After the aircraft power switch module receives the second DC voltage signal and switches from the off state to the on state according to the voltage value of the second DC voltage signal, so as to control the aircraft power supply to supply power to the aircraft, it further includes: The flight control computer sends a first instruction to the aircraft power switch module, and the first instruction is used to instruct the aircraft power switch module to switch from a closed state to an open state, so as to control the aircraft power supply to stop powering the aircraft.

11. An electronic device, comprising a memory, a processor, and a computer program stored on the memory, characterized in that, The processor executes the computer program to implement the method according to any one of claims 7 to 10.

12. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, the method according to any one of claims 7 to 10 is implemented.

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