A UPS power supply device applicable to an aviation electromagnetic launch system

Abstract

The present invention provides a UPS power supply device applicable to an aviation electromagnetic launch system, which is used to solve the problem of unstable power supply mode at the coil in the current helicopter airborne transient electromagnetic system. It includes: an induction circuit, a protection circuit, a rectification circuit, a voltage stabilization and energy storage circuit, a filtering circuit, a voltage conversion circuit, a lithium battery power supply circuit, and a power supply switching circuit. When the aviation electromagnetic launch system is in the high-power launch stage, the power supply for the electrical facilities at the coil is provided by the induction circuit; when the system is in the soft start or discharge stage, the power of the induction circuit is insufficient, and the power supply is automatically switched to the lithium battery power supply circuit through the power supply switching circuit for uninterrupted power supply. Based on the present invention, the power supply problem of each electrical facility at the launch coil during the normal operation of the aviation electromagnetic launch system can be effectively solved, and the long-term safe and stable operation of the aviation electromagnetic launch system can be realized.

Description

Technical Field

[0001] The present invention relates to the field of power electronics technology, and particularly to a UPS power supply with current induction power taking and lithium battery hybrid power supply suitable for high-power electromagnetic emission devices. Background Art

[0002] Geophysical electromagnetic methods are important technical means for underground mineral resource exploration. By observing the electromagnetic responses generated by the earth under the excitation of natural or artificial field sources, the electromagnetic transfer function of the earth system is obtained, and based on this, the distribution information of the electrical parameters of the earth is extracted. As an important branch of geophysical exploration, airborne electromagnetic method is an airborne geophysical exploration measurement method with the advantages of high exploration efficiency, low detection cost, good passability, and wide coverage area for a single exploration, which is suitable for operating in areas with complex geological and topographical conditions and can achieve tasks difficult to complete by ground exploration means. The airborne transient electromagnetic (ATEM) exploration system can be divided into a fixed-wing aircraft airborne transient electromagnetic (FTEM) system and a helicopter airborne transient electromagnetic (HTEM) system according to different carrier platforms. Among them, the application range of the FTEM system is relatively narrow due to factors such as high aircraft modification cost and the need for an airport for takeoff and landing near the exploration area.

[0003] The helicopter airborne transient electromagnetic system mainly includes an airborne exploration system and a ground analysis system. Among them, the exploration system includes a transmitting system and a receiving system. The transmitting system uses the helicopter airborne power supply as the input power supply, and after a series of power conversions, it is modulated into a pulse emission current with a specific waveform. A transmitting coil is hoisted at the bottom of the helicopter by a rope about 30m to 60m long. Generally, the transmitting coil is about 30m to 50m from the ground. The helicopter hoists the coil and flies in a certain exploration area. The pulse emission current is converted into a pulse electromagnetic signal through the hoisted transmitting coil and is emitted underground. The pulse electromagnetic signal will excite the underground medium to generate an induced electromagnetic signal. The receiving coil of the receiving system receives the induced electromagnetic signal generated by the underground medium and converts it into an electrical signal for data acquisition and processing. By analyzing the different induced magnetic field information generated by different underground media, the distribution of underground mineral deposits is inversely deduced.

[0004] The helicopter airborne transient electromagnetic (HTEM) system uses a helicopter as the equipment carrier platform, with low aircraft modification cost and high flexibility, and has become the main development trend of the current airborne electromagnetic exploration system. Key issues such as the front-stage transmitting device, carrier mechanical mechanism, data collection and processing method of the helicopter airborne transient electromagnetic system have gradually become the current mainstream research directions. Summary of the Invention

[0005] Aiming at the problem of unstable power supply mode at the coil in the current helicopter airborne transient electromagnetic (HTEM) system, the present invention aims to propose a UPS power supply device applicable to an airborne electromagnetic emission system.

[0006] Specifically, it includes: an induction circuit, a lithium battery power supply circuit, a power supply switching circuit, a rectification circuit, a protection circuit, a voltage stabilization and energy storage circuit, a filtering circuit, and a voltage conversion circuit.

[0007] The induction circuit is used to convert the alternating current on the transmission line into electric energy by the principle of electromagnetic induction when the helicopter airborne transient electromagnetic emission device is working normally.

[0008] The lithium battery power supply circuit is used for the backup power supply when the power obtained through the induction circuit is insufficient to maintain the power requirements of the electrical facilities under the cabin during the soft start and discharge stages of the emission device, so as to maintain uninterrupted power supply of the power supply device.

[0009] The power supply switching circuit is used to switch between the two power supply modes of power supply by induction power taking and lithium battery power supply.

[0010] The rectification circuit is used to rectify the alternating current taken by the induction circuit into direct current.

[0011] The protection circuit includes two parts. The first part is located after the induction circuit and is used to discharge the current spikes generated after the induction circuit to protect the subsequent rectification circuit. The second part is located after the rectification circuit and is used to discharge the overvoltage of the electric energy exceeding the capacitor withstand voltage value to protect the subsequent voltage stabilization and energy storage circuit.

[0012] The voltage stabilization and energy storage circuit is located after the second part of the protection circuit and is used to stabilize the voltage after the rectification circuit and store the electric energy taken by induction.

[0013] The filtering circuit is used to filter the current in the induction circuit to suppress the rising rate of the current in the circuit.

[0014] The voltage conversion circuit includes two-stage voltage conversion. The first stage is located after the voltage stabilization and energy storage circuit and is used to convert the output voltage of the voltage stabilization and energy storage circuit. The second stage is located after the power supply switching circuit and is used to convert the output voltage of the power supply switching circuit again.

[0015] The current obtained by the induction circuit enters the rectification circuit after the peak discharge of the protection circuit. After the AC-DC conversion of the rectification circuit, it passes through the protection circuit again for overvoltage discharge, and then enters the voltage stabilization and energy storage circuit for voltage stabilization and storage. Next, the output voltage of the voltage stabilization and energy storage circuit is subjected to a primary conversion through the voltage conversion circuit; the lithium battery power supply circuit is the backup power supply. The induction circuit and the lithium battery power supply circuit are connected to the power supply switching circuit, and the power supply switching circuit is used to switch between the two power supply methods of induction power extraction and lithium battery power supply. The output voltage of the power supply switching circuit is subjected to another voltage conversion through the voltage conversion circuit to meet the requirements of the electrical equipment.

[0016] The induction circuit described in the present invention includes a current transformer core and a coil, and the output side is connected to the input end of the protection circuit. The output end of the protection circuit is connected to the input end of the rectification circuit. The output end of the rectification circuit is connected to the input end of the voltage stabilization and energy storage circuit. The output end of the voltage stabilization and energy storage circuit is connected to the input end of the voltage conversion circuit. The output end of the voltage conversion circuit is connected to the input end of the power supply switching circuit. The output end of the power supply switching circuit is connected to the load.

[0017] Compared with the existing technologies at home and abroad, the innovation points of the present invention are as follows:

[0018] In the airborne exploration system of the helicopter airborne transient electromagnetic system, the current mainstream method for the power supply problem of the electrical facilities at the transmitting coil is to use an auxiliary device for power supply, and the main forms include solar power supply, lithium battery power supply, and cabin cable power supply. Among them, the solar cells have high costs, large volumes, limited installation positions, unstable power, and inconvenient use. The lithium battery power supply outputs stable and reliable power during normal operation, but there is no charging device at the coil, so it cannot operate for a long time and is prone to danger when the battery runs out. And directly powering through the cabin cable will increase the complexity of the design of the carrier mechanism of the exploration system, and it cannot guarantee whether the transmitted power is stable and reliable over a distance of about 30m to 60m in the air.

[0019] First, the present invention uses the induction power extraction power supply as the main power supply source for the electrical facilities at the coil. It utilizes the electromagnetic induction principle and magnetic saturation technology to obtain electrical energy by inducing the current on the high-voltage side through a current transformer. Compared with solar cells, the induction power extraction power supply has the advantages of low cost, small volume, flexible installation, and stable output.

[0020] Second, the present invention adopts a dual - power uninterruptible (UPS) power supply mode of inductive power acquisition plus a backup lithium - battery. It can automatically switch to lithium - battery power supply when the inductive power acquisition is insufficient during the soft - start or discharge stage of the electromagnetic emission system; during the normal emission stage of the electromagnetic emission system, the output power of the inductive power acquisition source can maintain the required electrical energy of various electrical facilities under the cabin. Compared with the simple lithium - battery power supply, the mode of inductive power acquisition plus lithium - battery uninterruptible power supply has the advantages of long working time, high safety and reliability.

[0021] Third, for the dual - power uninterruptible power supply mode adopted by the present invention, its hardware facilities are all built at the coil under the cabin. When the airborne electromagnetic emission system is working normally, there is no need to stretch a 30 - m to 60 - m power supply cable from the helicopter cabin to the emission coil for long - distance power transmission to the electrical facilities at the coil. Compared with the cabin cable power supply, it has the advantages of simple structure, easy operation, safe and stable power supply.

[0022] To achieve the uninterruptible power supply function, the present invention uses inductive power acquisition as the main power supply method. When the airborne transient electromagnetic emission device of the helicopter is working normally, the alternating current on the transmission line is used as the input of the inductive area electrical device, and electrical energy is obtained through the principle of electromagnetic induction; during the soft - start and discharge stages of the emission device, the power acquisition energy is insufficient to maintain the power requirements of the electrical facilities under the cabin. At this time, the device automatically switches to lithium - battery power supply to meet the demand for uninterruptible power supply of the device. Compared with the domestic and foreign airborne generator auxiliary power supply devices, this power supply device effectively reduces the installation difficulty of the emission device, improves the stability of the emission device during long - term operation, and enhances the overall performance of the airborne transient electromagnetic emission system of the helicopter. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 - Schematic diagram of the UPS power supply device structure of the airborne electromagnetic emission system;

[0024] Figure 2 - Voltage - stabilizing energy - storage circuit diagram of the UPS power supply device of the airborne electromagnetic emission system;

[0025] Figure 3 - Filter circuit diagram of the UPS power supply device of the airborne electromagnetic emission system;

[0026] Figure 4 - Voltage waveforms of the voltage - stabilizing energy - storage capacitor and the output voltage of URB4824YMD in the actual embodiment (when the power acquisition is insufficient);

[0027] Figure 5 - Voltage waveforms of the voltage - stabilizing energy - storage capacitor and the output voltage of URB4824YMD in the actual embodiment (when the power acquisition is sufficient); SPECIFIC IMPLEMENTATION SCHEMES

[0028] In order to make the objectives, technical solutions and advantages of the present application more clear and understandable, the present application will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application, that is, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. Usually, the components of the embodiments of the present application described in the drawings here can be arranged and designed in various different configurations.

[0029] For the UPS power supply device of the aviation electromagnetic emission system, as Figure 1 shown, it is divided into three parts. First, the induction power taking device part, which includes: an induction circuit, a protection circuit, a rectification circuit, a voltage stabilization and energy storage circuit, a filtering circuit, and a voltage conversion circuit; second, the lithium battery power supply part, which includes: a lithium battery power supply circuit; third, the power supply switching part, which includes: a power supply switching circuit. The specific relevant descriptions are as follows:

[0030] I. Induction power taking device part

[0031] The induction power taking device works based on the principle of electromagnetic induction. When there is current passing through the high-power charging line, the power taking coil can induce current for the use of the subsequent circuit. In this embodiment, the electromagnetic induction coil is a current transformer induction coil, which consists of a power taking magnetic core and an exciting coil. The magnetic core uses high-performance permalloy. Through the principle of electromagnetic induction, when there is current flowing through the high-voltage bus, the induction energy is obtained inside the current transformer induction coil and delivered to the subsequent circuit for use.

[0032] In this embodiment, the protection circuit consists of a bidirectional transient suppression diode and a varistor connected in parallel at the output end of the current transformer, and a zener diode connected in parallel at the output side of the rectification circuit, which is used to protect against large current or very large short-circuit fault current at the front stage, and suppress the surge current generated. At the same time, it has a voltage dividing effect, so that no sudden high voltage will be generated on the subsequent circuit, and the subsequent circuit is protected.

[0033] Further, the rectification circuit includes a first high-frequency rectifier diode D11, a second high-frequency rectifier diode D12, a third high-frequency rectifier diode D13, and a fourth high-frequency rectifier diode D14. All four rectifier diodes are Schottky high-frequency rectifier diodes, whose conduction voltage drop is lower than that of ordinary diodes, which can improve the switching speed and achieve low-loss high-frequency rectification. The four diodes form a full-bridge rectification circuit, whose input end is connected to the energy taking device, converting AC electrical energy into DC electrical energy. Here, the energy taking device is a current transformer.

[0034] In this embodiment, since the scenarios where the helicopter airborne transient electromagnetic emission device is applied may occur in high-altitude areas and there is a safety risk of electrolyte leakage in common electrolytic capacitors, the voltage-stabilizing energy storage capacitor in the voltage-stabilizing energy storage circuit is composed of three groups of tantalum capacitors connected in series in pairs and then connected in parallel. Compared with ordinary electrolytic capacitors, tantalum capacitors have the advantages of long life, high temperature resistance, high voltage resistance, and excellent performance in filtering high-frequency waveforms. The voltage-stabilizing energy storage capacitor is used to stabilize the voltage and store the electrical energy after inductive power extraction.

[0035] In this embodiment, the filtering circuit can be divided into a power input filtering part and a power output filtering part. According to the differences of the electrical equipment, there are three voltage conversion modules in the power supply device, which respectively correspond to three groups of filtering capacitors with different capacitance values. Their function is to filter the current in the overall circuit to suppress the rising rate of the current in the circuit.

[0036] In this embodiment, the voltage conversion circuit includes three conversion modules. The module models are URB4824YMD: the input voltage is 18V - 75VDC, the output voltage is 24VDC, the efficiency is 91%, the isolation voltage is 1500VDC, and it has input undervoltage protection, output short circuit, overcurrent, overvoltage protection and reverse connection prevention function. It can be connected after the voltage-stabilizing energy storage capacitor. During the normal emission stage, measure whether the output voltage of the DC-DC module is a stable 24V to prove whether the power extraction power meets the power demand of the electrical equipment. UWE2415S: the input voltage is 9V - 36VDC, the output voltage is ±15VDC, the efficiency is 79%, the isolation voltage is 3000VDC, and it has input undervoltage protection, output short circuit, overcurrent, overvoltage protection and reverse connection prevention function. It is used to supply electrical equipment such as voltage comparators and voltage sampling devices in the subsequent circuit. URB2412S: the input voltage is 9V - 36VDC, the output voltage is 12VDC, the efficiency is 88%, the isolation voltage is 1500VDC, and it has input undervoltage protection, output short circuit, overcurrent, overvoltage protection and reverse connection prevention function.

[0037] II. Lithium battery power supply part

[0038] In this example, the rated output voltage of the lithium battery is 24V, the battery capacity is 5AH, the output interface is a waterproof aviation plug to adapt to the operation of the helicopter airborne transient electromagnetic system in different environments, and a voltage meter display device is installed on the battery shell, which can be used as a backup power supply to supply the equipment at the transmitting coil to operate safely and stably when the inductive power extraction power is insufficient.

[0039] III. Power supply switching part

[0040] The helicopter airborne transient electromagnetic system can be divided into a soft start stage, a normal emission stage, and a discharge stage in chronological order during normal operation. At the beginning of the soft start stage and the end of the discharge stage, since the current flowing through the charging cable is small, it is not sufficient to enable the electrical energy obtained by inductive power extraction to support the normal operation of all electrical equipment at the transmitting coil. Therefore, when the inductive power extraction is insufficient, a lithium battery with high safety and reliability is used for power supply to ensure the normal operation of all electrical equipment.

[0041] In this example, the input side of the power supply switching part is connected to the output unit of the backup lithium battery and the output unit of the power extraction module. The latter-stage commutation bridge is composed of a group of commutation diodes. During normal emission, the alternating current on the high-power charging line flows through the charging line, and the inductive power extraction circuit works normally. All electrical equipment at the transmitting coil is supplied by the inductive power extraction part; when the helicopter airborne transient electromagnetic system is in the soft start or discharge state, the insufficient power extraction results in the voltage conversion module being unable to continuously output a normal voltage. At this time, the commutation tube works, and the power supply device of the circuit is switched to lithium battery power supply to complete the uninterrupted operation of the power supply device.

[0042] In this example, Figure 2 Figure 3 They respectively correspond to the voltage stabilization energy storage circuit diagram and the filter circuit diagram of the UPS power supply device of the airborne electromagnetic emission system.

[0043] The protection circuit includes two parts. The first part includes the transient suppression diode D1, which is specifically connected in parallel at the output end of the induction circuit; the second part includes the zener diode D2, the current-limiting resistor R3, the current-limiting resistor R2, the current-limiting resistor R1, and the MOS transistor T1. The cathode of the zener diode D2 is connected to the positive output of the rectification circuit, and the other end is connected to the current-limiting resistor R3. The other end of the current-limiting resistor R3 is grounded and connected in parallel on the output side of the rectification circuit; one end of the current-limiting resistor R2 is connected to the node position between the anode of the zener diode D2 and the current-limiting resistor R3, and the other end is connected to the gate of the MOS transistor T1; the drain of the MOS transistor is connected to the current-limiting resistor R1, the source is grounded, and one end of the current-limiting resistor R1 is connected to the cathode of the zener diode D2, and the other end is connected to the drain of the MOS transistor T1 and then connected in parallel in the protection circuit.

[0044] The described voltage stabilizing and energy storage circuit includes a group of parallel capacitors: tantalum capacitor C1 and tantalum capacitor C2; a second group of parallel capacitors: tantalum capacitor C3 and tantalum capacitor C4; a third group of parallel capacitors: tantalum capacitor C5 and tantalum capacitor C6. In the first group of parallel capacitors, tantalum capacitor C1 and tantalum capacitor C2 are in series; in the second group of parallel capacitors, tantalum capacitor C3 and tantalum capacitor C4 are in series; in the third group of parallel capacitors, tantalum capacitor C5 and tantalum capacitor C6 are in series. The three groups of capacitors are connected in parallel to form an energy storage and voltage stabilizing capacitor bank. The anodes of tantalum capacitor C1, tantalum capacitor C3, and tantalum capacitor C5 are connected and then connected to the anode output of the rectifier circuit; the cathodes of tantalum capacitor C2, tantalum capacitor C4, and tantalum capacitor C6 are connected and then connected to the cathode output of the rectifier circuit.

[0045] The described filter circuit is divided into two parts: the power input filter part and the power output filter part. The power input filter part consists of filter capacitor C7, filter tantalum capacitor C9, and filter tantalum capacitor C12; the power output filter part consists of filter tantalum capacitor C8, filter tantalum capacitor C10, filter tantalum capacitor C11, and filter tantalum capacitor C13.

[0046] The described voltage conversion circuit includes three conversion modules with model numbers URB4824YMD, UWE2415S, and URB2412S respectively. The input of URB4824YMD is connected to the output of the energy storage and voltage stabilizing circuit through filter capacitor C7, and the output is connected to the input of the power supply switching circuit through filter tantalum capacitor C8. The input of the voltage conversion module UWE2415S is connected to the output of the power supply switching circuit through filter tantalum capacitor C9. UWE2415S has two outputs. One output is connected to the subsequent electrical appliance through filter tantalum capacitor C10, and the other output is connected to the subsequent electrical appliance through filter tantalum capacitor C11. The input of the voltage conversion module URB2412S is connected to the output of the power supply switching circuit through filter tantalum capacitor C12, and the output is connected to the subsequent electrical appliance through filter tantalum capacitor C13.

[0047] The described power supply switching circuit includes commutation bridge diodes VD1 and VD2. The positive pole of the output circuit of the lithium battery is connected to the positive pole of commutation diode VD2, and the negative pole is connected to the negative pole of the first-stage voltage conversion circuit and grounded as the negative pole of the power supply switching circuit. The positive pole of the first-stage voltage conversion circuit is connected to the positive pole of commutation diode VD1. Commutation diode VD1 is connected to the negative pole of commutation diode VD2 as the positive pole of the power supply switching circuit.

[0048] The described rectifier circuit is a bridge rectifier circuit. Rectifier diodes D11, D12, D13, and D14 are all high-frequency rectifier Schottky diodes. The withstand voltage values of commutation bridge diodes VD1 and VD2 in the power supply switching circuit are both higher than 50V.

[0049] In this example,Figure 4 Figure 5 They respectively correspond to the output voltage waveforms of the energy storage and voltage stabilizing capacitor and URB4824YMD when the helicopter airborne transient electromagnetic system is in the soft start and discharge stages during normal operation, and in the normal emission stage, that is, when the induction power taking part has insufficient output power and sufficient output power.

Claims

1. A UPS power supply device applicable to an aviation electromagnetic launch system, characterized in that, Including: An induction circuit, which is used to convert the alternating current on the transmission line into electric energy by the principle of electromagnetic induction when the helicopter airborne transient electromagnetic emission device is working normally; A lithium battery power supply circuit, which is used for the backup power supply when the electric energy obtained through the induction circuit is insufficient to maintain the power requirements of the electrical facilities under the cabin during the soft start and discharge stages of the emission device, so as to maintain uninterrupted power supply of the power supply device; A power supply switching circuit, which is used to switch between the two power supply methods of induction power taking and lithium battery power supply; A rectification circuit, which is used to rectify the alternating current taken by the induction circuit into direct current; A protection circuit, including two parts. The first part is located after the induction circuit and is used to discharge the current spikes generated after the induction circuit to protect the subsequent rectification circuit. The second part is located after the rectification circuit and is used to discharge the overvoltage of the electric energy exceeding the capacitor withstand voltage value to protect the subsequent voltage stabilization and energy storage circuit; A voltage stabilization and energy storage circuit, which is used to stabilize the voltage after the rectification circuit and store the electric energy obtained by induction power taking; A voltage stabilization and energy storage circuit, which is located after the second part of the protection circuit and is used to stabilize the voltage after the rectification circuit and store the electric energy obtained by induction power taking; A filtering circuit, which is used to filter the current in the induction circuit to suppress the rising rate of the current in the circuit; A voltage conversion circuit, including two-stage voltage conversion. The first stage is located after the voltage stabilization and energy storage circuit and is used to convert the output voltage of the voltage stabilization and energy storage circuit. The second stage is located after the power supply switching circuit and is used to convert the output voltage of the power supply switching circuit again; The current obtained by the induction circuit enters the rectification circuit after the spike discharge of the protection circuit. After the AC-DC conversion of the rectification circuit, it passes through the protection circuit again for overvoltage discharge, and then enters the voltage stabilization and energy storage circuit for voltage stabilization and storage. Next, the output voltage of the voltage stabilization and energy storage circuit is subjected to a first-stage conversion through the voltage conversion circuit; the lithium battery power supply circuit is the backup power supply. The induction circuit and the lithium battery power supply circuit are connected to the power supply switching circuit. The power supply switching circuit is used to switch between the two power supply methods of induction power taking and lithium battery power supply. The output voltage of the power supply switching circuit is subjected to another voltage conversion through the voltage conversion circuit to meet the requirements of the electrical equipment; The described induction circuit includes a current transformer core and a coil. The primary coil is a high-power charging cable, and the secondary coil is wound with an exciting wire, and the output side is connected to the subsequent protection circuit; the power supply switching circuit includes a commutation bridge diode VD1 and a commutation bridge diode VD2; the positive pole of the lithium battery output circuit is connected to the positive pole of the commutation diode VD2, and the negative pole is connected to the ground through the negative pole of the first-stage voltage conversion circuit as the negative pole of the power supply switching circuit; the positive pole of the first-stage voltage conversion circuit is connected to the positive pole of the commutation tube diode VD1; the commutation tube diode VD1 is connected to the negative pole of the commutation diode VD2 as the positive pole of the power supply switching circuit.

2. The UPS power supply device applicable to an aviation electromagnetic launch system according to claim 1, characterized in that: The protection circuit includes two parts. The first part includes a transient suppression diode D1, which is specifically connected in parallel at the output end of the induction circuit. The second part includes a voltage stabilizing diode D2, a current limiting resistor R3, a current limiting resistor R2, a current limiting resistor R1, and a MOS transistor T1. The cathode of the voltage stabilizing diode D2 is connected to the positive output of the rectifying circuit, and the other end is connected to the current limiting resistor R3. The other end of the current limiting resistor R3 is grounded and connected in parallel on the output side of the rectifying circuit. One end of the current limiting resistor R2 is connected to the node position between the anode of the voltage stabilizing diode D2 and the current limiting resistor R3, and the other end is connected to the gate of the MOS transistor T1. The drain of the MOS transistor is connected to the current limiting resistor R1, the source is grounded, and one end of the current limiting resistor R1 is connected to the cathode of the voltage stabilizing diode D2. After the other end is connected to the drain of the MOS transistor T1, it is connected in parallel in the protection circuit.

3. The UPS power supply device applicable to an aviation electromagnetic launch system according to claim 1, characterized in that: The voltage stabilizing energy storage circuit includes a group of parallel capacitors: tantalum capacitors C1 and C2, a second group of parallel capacitors: tantalum capacitors C3 and C4, and a third group of parallel capacitors: tantalum capacitors C5 and C6. The tantalum capacitors C1 and C2 in the first group of parallel capacitors are connected in series, the tantalum capacitors C3 and C4 in the second group of parallel capacitors are connected in series, and the tantalum capacitors C5 and C6 in the third group of parallel capacitors are connected in series. The three groups of capacitors are connected in parallel to form an energy storage voltage stabilizing capacitor bank. The anodes of the tantalum capacitors C1, C3, and C5 are connected and then connected to the anode output of the rectifying circuit. The cathodes of the tantalum capacitors C2, C4, and C6 are connected and then connected to the cathode output of the rectifying circuit.

4. The UPS power supply device applicable to an aviation electromagnetic launch system according to claim 1, characterized in that: The filtering circuit is divided into two parts: a power input filtering part and a power output filtering part. The power input filtering part consists of a filtering capacitor C7, a filtering tantalum capacitor C9, and a filtering tantalum capacitor C12. The power output filtering part consists of a filtering tantalum capacitor C8, a filtering tantalum capacitor C10, a filtering tantalum capacitor C11, and a filtering tantalum capacitor C13.

5. The UPS power supply device applicable to an aviation electromagnetic launch system according to claim 4, characterized in that: The voltage conversion circuit includes three conversion modules, with model numbers URB4824YMD, UWE2415S, and URB2412S respectively. The input of the URB4824YMD is connected to the output of the energy storage voltage stabilizing circuit through the filtering capacitor C7, and the output is connected to the input of the power switching circuit through the filtering tantalum capacitor C8. The input of the voltage conversion module UWE2415S is connected to the output of the power switching circuit through the filtering tantalum capacitor C9. The UWE2415S has two outputs. One output is connected to the subsequent electrical appliance through the filtering tantalum capacitor C10, and the other output is connected to the subsequent electrical appliance through the filtering tantalum capacitor C11. The input of the voltage conversion module URB2412S is connected to the output of the power switching circuit through the filtering tantalum capacitor C12, and the output is connected to the subsequent electrical appliance through the filtering tantalum capacitor C13.

6. The UPS power supply device applicable to an aviation electromagnetic launch system according to claim 1, characterized in that: The rectifying circuit is a bridge rectifying circuit. The rectifying diodes D11, D12, D13, and D14 are all high-frequency rectifying Schottky diodes. The breakdown voltages of the commutating bridge diodes VD1 and VD2 in the power switching circuit are both higher than 50V.

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