Intelligent power supply control system and method for aircraft

Abstract

The invention discloses an intelligent power supply control system and method for an aircraft, and relates to the field of power supplies, and the system comprises a power supply voltage stabilization module which is used for stabilizing the voltage of an introduced main power supply, and the stabilized main power supply supplies power to a post-stage circuit and a standby battery working module; the standby battery working module is used for charging and storing energy when the main power supply supplies power, and supplying power to a post-stage circuit when the main power supply is insufficient in power supply or has an electric leakage risk; compared with the prior art, the system has the beneficial effects that the standby battery working module and the electric leakage monitoring control module are intelligently linked, and when the high-altitude insulation degradation causes the electric leakage risk of the power supply of the main power supply, the standby battery with lower voltage is automatically switched to supply power, so that the leakage current is reduced, and the high-altitude electric leakage problem is relieved; the power supply safety and reliability of the aircraft in a high-altitude environment are improved, and an innovative self-adaptive protection strategy is provided for an aircraft power supply system.

Description

Technical Field

[0001] This invention relates to the field of power supply, specifically to an intelligent power control system and method for aircraft. Background Technology

[0002] In aircraft power supply systems, both the main power supply and backup batteries are critical power supply units, and modern designs include their own leakage (insulation) detection functions. However, existing systems generally operate in isolation regarding leakage detection and management of the main and backup power supplies.

[0003] As an aircraft climbs to high altitudes, the low air pressure significantly reduces the strength of air insulation. At this point, electrical clearances that are safe at lower altitudes may leak or experience point discharge. Because the main power supply has a higher voltage, leakage paths are more likely to form under the harsh insulation conditions at high altitudes. This not only wastes energy but can also trigger a chain reaction of faults such as localized overheating, electromagnetic interference, and even insulation breakdown, threatening flight safety. While backup batteries typically have a slightly lower output voltage than the main power supply, their potential for leakage protection within the system architecture is not effectively utilized and needs improvement. Summary of the Invention

[0004] The purpose of this invention is to provide an intelligent power control system and method for aircraft to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: An intelligent power control system for aircraft, comprising: The power supply voltage regulator module is used to regulate the voltage of the main power supply. The regulated main power supply then powers the subsequent circuits and the backup battery working module. The backup battery module is used to charge and store energy when the main power supply is on, and to supply power to the downstream circuit when the main power supply is insufficient or there is a risk of leakage in the main power supply. The battery overcharge protection module is used to detect whether there is an overcharge risk in the backup battery. When there is an overcharge risk, the backup battery is controlled to discharge. After the backup battery discharges, it returns to the initial state. The overcharge risk is when the backup battery voltage reaches the first reference voltage, and the backup battery continues to charge for a set time (i.e., the second capacitor is charged enough to turn on the sixth transistor). The leakage current monitoring and control module is used to detect whether there is a leakage current risk when the main power supply is powered. If there is a leakage current risk, the power supply voltage regulator module is controlled to discharge. The leakage current risk is the voltage difference between the positive terminal of the main power supply and the casing, which is greater than the second reference voltage after rectification, filtering and amplification. The first output terminal of the power supply regulator module is connected to the first input terminal of the backup battery working module, the output terminal of the leakage current monitoring and control module is connected to the first input terminal of the power supply regulator module, the first output terminal of the backup battery working module is connected to the input terminal of the battery overcharge protection module, and the output terminal of the battery overcharge protection module is connected to the second input terminal of the backup battery working module.

[0006] As a further embodiment of the present invention: the subsequent circuit includes: An EMI filter is used to suppress electromagnetic interference at the input voltage of the power supply regulator module or backup battery module, and outputs the voltage after suppressing electromagnetic interference to the overvoltage and overcurrent protection module. Overvoltage and overcurrent protection module, used to provide overvoltage and overcurrent protection; The step-down converter module is used to convert the input voltage to 12V voltage to power multiple step-down converter modules; The multi-channel step-down converter module is used to convert 12V voltage to 1.0V, 1.8V, 1.5V, and 3.3V voltage to power the aircraft processor; The input of the EMI filter is connected to the second output of the power supply regulator module and the second output of the backup battery module. The output of the EMI filter is connected to the input of the overvoltage and overcurrent protection module. The output of the overvoltage and overcurrent protection module is connected to the input of the buck converter module. The output of the buck converter module is connected to the input of the multi-channel buck converter module.

[0007] As a further embodiment of the present invention: the power supply regulator module includes a TVS protection transistor, a fourth resistor, a fifth resistor, a sixth resistor, a three-terminal regulator, a third amplifier, a second MOSFET, a first inductor, a first capacitor, and a second diode. The non-inverting input of the third amplifier is connected to one end of the fourth resistor, the negative terminal of the TVS protection transistor, and the main power supply. The positive terminal of the TVS protection transistor is grounded. The other end of the fourth resistor is connected to one end of the fifth resistor and one end of the sixth resistor. The other end of the fifth resistor is grounded. The other end of the sixth resistor is connected to the reference terminal of the three-terminal regulator. The positive terminal of the three-terminal regulator is grounded. The negative terminal of the three-terminal regulator is connected to the gate (G) terminal of the second MOSFET. The drain (D) terminal of the second MOSFET is connected to the output terminal and the inverting input of the third amplifier. The source (S) terminal of the second MOSFET is connected to one end of the first inductor and the output terminal of the leakage current monitoring and control module. The other end of the first inductor is connected to one end of the first capacitor, the positive terminal of the second diode, and the first input terminal of the backup battery working module. The other end of the first capacitor is grounded. The negative terminal of the second diode is connected to the subsequent circuit.

[0008] As a further embodiment of the present invention: the backup battery working module includes a third diode, a seventh resistor, a third MOSFET, an eighth resistor, a backup battery, a fourth diode, a fourth MOSFET, and a ninth resistor. The positive terminal of the third diode is connected to the first output terminal of the power supply regulator module, the negative terminal of the third diode is connected to one end of the seventh resistor and the drain terminal of the third MOSFET, the other end of the seventh resistor is connected to the gate terminal of the third MOSFET, the source terminal of the third MOSFET is connected to one end of the eighth resistor, the other end of the eighth resistor is connected to the positive terminal of the fourth diode, the positive terminal of the backup battery, and the drain terminal of the fourth MOSFET, the negative terminal of the fourth diode is connected to the subsequent circuit, the negative terminal of the backup battery is grounded, the gate terminal of the fourth MOSFET is connected to the output terminal of the battery overcharge protection module, and the source terminal of the fourth MOSFET is grounded through the ninth resistor.

[0009] As a further embodiment of the present invention: the battery overcharge protection module includes a fifth diode, a fifth amplifier, an AND gate, a tenth resistor, a first potentiometer, a second capacitor, an eleventh resistor, a twelfth resistor, a fifth transistor, a sixth transistor, a thirteenth resistor, a seventh diode, a fourteenth resistor, a seventh transistor, a sixth diode, and a third capacitor. One end of the input terminal of the AND gate is connected to the negative terminal of the fifth diode and the output terminal of the differential amplifier circuit. The two input terminals of the differential amplifier circuit are respectively connected to the two ends of the eighth resistor. The positive terminal of the fifth diode is grounded. The other end of the input terminal of the AND gate is connected to the output terminal of the fifth amplifier. The inverting input terminal of the fifth amplifier is connected to the first reference voltage, and the non-inverting input terminal of the fifth amplifier is connected to the positive terminal of the backup battery. The output terminal of the AND gate is connected to one end of the tenth resistor, and the other end of the tenth resistor is connected to the first potentiometer. One end of the first potentiometer is connected to one end of the second capacitor, one end of the eleventh resistor, the collector of the seventh transistor, one end of the thirteenth resistor, and the anode of the seventh diode. The other end of the eleventh resistor is connected to the base of the sixth transistor. The emitter of the sixth transistor is grounded. The collector of the sixth transistor is connected to one end of the twelfth resistor and the base of the fifth transistor. The other end of the twelfth resistor is connected to the emitter of the fifth transistor and the power supply voltage. The collector of the fifth transistor is connected to the other end of the thirteenth resistor. The cathode of the seventh diode is connected to one end of the fourteenth resistor and the gate of the fourth MOSFET. The other end of the fourteenth resistor is connected to the cathode of the sixth diode and one end of the third capacitor. The other end of the third capacitor is grounded. The anode of the sixth diode is connected to the base of the seventh transistor. The emitter of the seventh transistor is grounded.

[0010] As a further embodiment of the present invention: the leakage current monitoring and control module includes a first diode, a rectifier, a fourth capacitor, a fifth capacitor, a second inductor, a first resistor, a second resistor, a third resistor, a first amplifier, a second amplifier, and a first MOSFET. The positive terminal of the first diode is connected to the main power supply, the negative terminal of the first diode is connected to the first terminal of the rectifier, the second terminal of the rectifier is grounded, the third terminal of the rectifier is connected to the outer casing (the outer casing of this system), the fourth terminal of the rectifier is connected to one end of the fourth capacitor and one end of the second inductor, the other end of the fourth capacitor is grounded, the other end of the second inductor is connected to one end of the fifth capacitor and one end of the first resistor, the other end of the fifth capacitor is grounded, the other end of the first resistor is connected to the non-inverting input of the first amplifier, the inverting input of the first amplifier is connected to one end of the second resistor and one end of the third resistor, the other end of the second resistor is grounded, the other end of the third resistor is connected to the output terminal of the first amplifier and the non-inverting input of the second amplifier, the inverting input of the second amplifier is connected to the second reference voltage, the output terminal of the second amplifier is connected to the gate (G) of the first MOSFET, the source (S) of the first MOSFET is grounded, and the drain (D) of the first MOSFET is connected to the first input terminal of the power supply regulator module.

[0011] A smart power control method for aircraft includes the following steps: When the main power supply is used, the voltage is regulated by the power supply voltage regulator module to supply power to the backup battery working module and the subsequent circuit, and to charge the backup battery. During the charging process of the backup battery, the battery overcharge protection module monitors the charging status of the backup battery. If there is a risk of overcharging, it controls the backup battery to discharge to avoid overcharging. If the main power supply is insufficient, the backup battery module will automatically switch to power the downstream circuits. As the aircraft climbs, the air insulation strength decreases. If there is a risk of leakage, the leakage monitoring and control module will detect the leakage signal and control the power supply voltage regulator module to ground and discharge. It will then automatically switch to the backup battery module to power the subsequent circuits. Since the backup battery output voltage is lower than the main power supply output voltage, the leakage current is reduced, thus alleviating the leakage problem at high altitudes.

[0012] Compared with the prior art, the beneficial effects of the present invention are as follows: The present invention intelligently links the backup battery working module and the leakage monitoring and control module, and automatically switches to the backup battery with a lower voltage when the main power supply is at risk of leakage due to high-altitude insulation degradation, thereby reducing leakage current and alleviating the high-altitude leakage problem; it improves the power supply safety and reliability of the aircraft in the high-altitude environment, and provides an innovative adaptive protection strategy for the aircraft power system. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of an intelligent power control system for aircraft.

[0014] Figure 2 This is a circuit diagram of an intelligent power control system for aircraft. Detailed Implementation

[0015] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0016] Please see Figure 1 An intelligent power control system for aircraft, comprising: The power supply regulator module 1 is used to regulate the voltage of the main power supply VCC. The regulated main power supply VCC supplies power to the subsequent circuits and the backup battery working module 2. Backup battery working module 2 is used to charge and store energy when the main power supply VCC is powered, and to supply power to the downstream circuit when the main power supply VCC is insufficient or there is a risk of leakage in the main power supply VCC. The battery overcharge protection module 3 is used to detect whether there is an overcharge risk in the backup battery E1. When there is an overcharge risk, it controls the backup battery E1 to discharge. After the backup battery E1 finishes discharging, it returns to the initial state. The overcharge risk is when the voltage of the backup battery E1 reaches the first reference voltage VREF1, the backup battery E1 continues to charge for a set time (i.e., the second capacitor C2 is charged enough to turn on the sixth transistor V6). The leakage current monitoring and control module 4 is used to detect whether there is a leakage current risk when the main power supply VCC is powered. When there is a leakage current risk, the power supply voltage regulator module 1 is controlled to discharge. The leakage current risk is that the voltage difference between the positive terminal of the main power supply VCC and the casing is greater than the second reference voltage VREF2 after rectification, filtering and amplification. The first output terminal of the power supply voltage regulator module 1 is connected to the first input terminal of the backup battery working module 2, the output terminal of the leakage current monitoring and control module 4 is connected to the first input terminal of the power supply voltage regulator module 1, the first output terminal of the backup battery working module 2 is connected to the input terminal of the battery overcharge protection module 3, and the output terminal of the battery overcharge protection module 3 is connected to the second input terminal of the backup battery working module 2.

[0017] In this embodiment, please refer to Figure 1 The subsequent circuitry includes: EMI filter 5 is used to suppress electromagnetic interference on the input voltage of the power supply regulator module 1 or the backup battery working module 2, and outputs the voltage after suppressing electromagnetic interference to the overvoltage and overcurrent protection module 6. Overvoltage and overcurrent protection module 6 is used to provide overvoltage and overcurrent protection; The step-down converter module 7 is used to convert the input voltage into 12V voltage to power the multi-channel step-down converter module 8; The multi-channel step-down converter module 8 is used to convert 12V voltage into 1.0V, 1.8V, 1.5V, and 3.3V voltages to power the aircraft processor; The input terminal of EMI filter 5 is connected to the second output terminal of power supply regulator module 1 and the second output terminal of backup battery working module 2. The output terminal of EMI filter 5 is connected to the input terminal of overvoltage and overcurrent protection module 6. The output terminal of overvoltage and overcurrent protection module 6 is connected to the input terminal of buck converter module 7. The output terminal of buck converter module 7 is connected to the input terminal of multi-channel buck converter module 8.

[0018] The EMI filter 5 is selected from devices that meet aviation standards, have a wide operating temperature range, and have high reliability historical data.

[0019] The overvoltage and overcurrent protection module 6 uses the LTC4291 chip to construct the protection circuit. The step-down converter module 7 uses the SM4613EIP chip to build the step-down circuit, so as to reduce the voltage to 12V. The multi-channel buck converter module 8 uses the SM4644EIP chip to achieve multi-channel buck conversion. The SM4644EIP is a four-channel power module product that provides four voltage outputs. 1.0V: Powers the core of the ZYNQ7 (FMQL20S400) processor.

[0020] 1.8V: Provides power for the auxiliary voltage of ZYNQ7, the reference voltage of DDR3 (a common type of memory), etc.

[0021] 1.5V: Powers the DDR3 memory chips.

[0022] 3.3V: Powers most of the onboard logic chips, interface transceivers, clocks, and other digital circuits.

[0023] In this embodiment, please refer to Figure 2The power supply regulator module 1 includes a TVS diode, a fourth resistor R4, a fifth resistor R5, a sixth resistor R6, a three-terminal regulator U4, a third amplifier U3, a second MOSFET V2, a first inductor L1, a first capacitor C1, and a second diode D2. The non-inverting input of the third amplifier U3 is connected to one end of the fourth resistor R4, the negative terminal of the TVS diode, and the main power supply VCC. The positive terminal of the TVS diode is grounded. The other end of the fourth resistor R4 is connected to one end of the fifth resistor R5 and one end of the sixth resistor R6. The other end of the fifth resistor R5 is grounded. The other end of the sixth resistor R6 is connected to the three-terminal regulator. The reference terminal of the three-terminal regulator U4 is connected to the ground. The negative terminal of the three-terminal regulator U4 is connected to the gate of the second MOSFET V2. The drain of the second MOSFET V2 is connected to the output terminal and the inverting terminal of the third amplifier U3. The source terminal of the second MOSFET V2 is connected to one end of the first inductor L1 and the output terminal of the leakage current monitoring and control module 4. The other end of the first inductor L1 is connected to one end of the first capacitor C1, the positive terminal of the second diode D2, and the first input terminal of the backup battery working module 2. The other end of the first capacitor C1 is grounded. The negative terminal of the second diode D2 is connected to the subsequent circuit.

[0024] Considering significant voltage surges (such as 80V transients) and spikes, a TVS protection diode is designed for transient grounding and current dissipation. During normal voltage changes, the voltage is collected by voltage divider through the fourth resistor R4 and the fifth resistor R5 and output to the three-terminal regulator U4 (specifically, the TL431). The higher the reference voltage of the three-terminal regulator U4, the lower the negative voltage. Therefore, the larger the main power supply VCC, the lower the conduction degree of the second MOSFET V2; the smaller the main power supply VCC, the higher the conduction degree of the second MOSFET V2, thus constructing a regulated output. The voltage after passing through the second MOSFET V2 is then filtered by the first inductor L1 and the first capacitor C1 to ensure voltage stability, and finally output to the subsequent circuit through the second diode D2.

[0025] In another embodiment, the second MOSFET V2 can be other types of switching transistors, such as transistors, IGBTs, etc.

[0026] In this embodiment, please refer to Figure 2The backup battery working module 2 includes a third diode D3, a seventh resistor R7, a third MOSFET V3, an eighth resistor R8, a backup battery E1, a fourth diode D4, a fourth MOSFET V4, and a ninth resistor R9. The positive terminal of the third diode D3 is connected to the first output terminal of the power supply regulator module 1. The negative terminal of the third diode D3 is connected to one end of the seventh resistor R7 and the drain terminal of the third MOSFET V3. The other end of the seventh resistor R7 is connected to the gate terminal of the third MOSFET V3. The source terminal of the third MOSFET V3 is connected to one end of the eighth resistor R8. The other end of the eighth resistor R8 is connected to the positive terminal of the fourth diode D4, the positive terminal of the backup battery E1, and the drain terminal of the fourth MOSFET V4. The negative terminal of the fourth diode D4 is connected to the subsequent circuit. The negative terminal of the backup battery E1 is grounded. The gate terminal of the fourth MOSFET V4 is connected to the output terminal of the battery overcharge protection module 3. The source terminal of the fourth MOSFET V4 is grounded through the ninth resistor R9.

[0027] When the main power supply VCC is in operation, the voltage charges the backup battery E1 through the third MOSFET V3 and the eighth resistor R8, and the backup battery E1 stores electrical energy. When the main power supply VCC is insufficient, the backup battery E1 supplies power to the subsequent circuit through the fourth diode D4, maintaining the normal operation of the subsequent circuit.

[0028] In another embodiment: the backup battery E1 can be a battery string consisting of multiple batteries.

[0029] In this embodiment, please refer to Figure 2The battery overcharge protection module 3 includes a fifth diode D5, a fifth amplifier U5, an AND gate U6, a tenth resistor R10, a first potentiometer RP1, a second capacitor C2, an eleventh resistor R11, a twelfth resistor R12, a fifth transistor V5, a sixth transistor V6, a thirteenth resistor R13, a seventh diode D7, a fourteenth resistor R14, a seventh transistor V7, a sixth diode D6, and a third capacitor C3. One input terminal of the AND gate U6 is connected to the negative terminal of the fifth diode D5 and the output terminal of the differential amplifier circuit. The two input terminals of the differential amplifier circuit are respectively connected to the two ends of the eighth resistor R8. The positive terminal of the fifth diode D5 is grounded. The other input terminal of the AND gate U6 is connected to the output terminal of the fifth amplifier U5. The inverting input of the fifth amplifier U5 is connected to the first reference voltage VREF1. The non-inverting input of the fifth amplifier U5 is connected to the positive terminal of the backup battery E1. The output terminal of the AND gate U6 is connected to one end of the tenth resistor R10, and the other end of the tenth resistor R10 is connected to one end of the first potentiometer RP1. One end of the first potentiometer RP1 is connected to one end of the second capacitor C2, one end of the eleventh resistor R11, the collector of the seventh transistor V7, one end of the thirteenth resistor R13, and the positive terminal of the seventh diode D7. The other end of the eleventh resistor R11 is connected to the base of the sixth transistor V6. The emitter of the sixth transistor V6 is grounded. The collector of the sixth transistor V6 is connected to one end of the twelfth resistor R12 and the base of the fifth transistor V5. The other end of the twelfth resistor R12 is connected to the emitter of the fifth transistor V5 and the supply voltage VDD. The collector of the fifth transistor V5 is connected to the other end of the thirteenth resistor R13. The negative terminal of the seventh diode D7 is connected to one end of the fourteenth resistor R14 and the gate of the fourth MOSFET V4. The other end of the fourteenth resistor R14 is connected to the negative terminal of the sixth diode D6 and one end of the third capacitor C3. The other end of the third capacitor C3 is grounded. The positive terminal of the sixth diode D6 is connected to the base of the seventh transistor V7. The emitter of the seventh transistor V7 is grounded.

[0030] When the voltage of the backup battery E1 is higher than the first reference voltage VREF1, the voltage at the non-inverting input of the fifth amplifier U5 is higher than the voltage at the inverting input, and the fifth amplifier U5 outputs a high level. If the backup battery E1 is still being charged through the eighth resistor R8, the differential amplifier circuit will output a voltage, making both inputs of the AND gate U6 high and the output of the AND gate U6 high. The second capacitor C2 is then charged through the tenth resistor R10 and the first potentiometer RP1. If the charging time of the second capacitor C2 continues (i.e., the backup battery E1 continues to charge when the voltage is sufficient), the voltage on the second capacitor C2 will start to turn on the sixth transistor V6. After the sixth transistor V6 turns on, it triggers the fifth transistor V5 to turn on, and then charges the second capacitor C2 through the fifth transistor V5, making both the sixth transistor V6 and the fifth transistor V5 turn on. At this time, the common point A3 is high, triggering the fourth MOSFET V4 to turn on. The backup battery E1 discharges through the fourth MOSFET V4 and the ninth resistor R9, avoiding overcharging. When the common point A3 is high, the third capacitor C3 is charged through the fourteenth resistor R14. When the third capacitor C3 is charged enough to turn on the sixth diode D6 (Zenyl 66), the seventh transistor V7 is triggered to turn on, quickly dissipating the voltage on the second capacitor C2, and the circuit returns to its initial state.

[0031] In another embodiment: a Zener diode can be set at the common point A3 to ensure stable conduction of the fourth MOSFET V4 on the one hand, and to ensure stable voltage when the third capacitor C3 is charging on the other hand.

[0032] In this embodiment, please refer to Figure 2The leakage current monitoring and control module 4 consists of a first diode D1, a rectifier T, a fourth capacitor C4, a fifth capacitor C5, a second inductor L2, a first resistor R1, a second resistor R2, a third resistor R3, a first amplifier U1, a second amplifier U2, and a first MOSFET V1. The anode of the first diode D1 is connected to the main power supply VCC, and the cathode of the first diode D1 is connected to the first terminal of the rectifier T. The second terminal of the rectifier T is grounded, and the third terminal of the rectifier T is connected to the outer casing (the casing of this system). The fourth terminal of the rectifier T is connected to one end of the fourth capacitor C4 and one end of the second inductor L2. The other end of the fourth capacitor C4 is grounded, and the other end of the second inductor L2 is connected to the fifth capacitor C5. One end of the first resistor R1 and the other end of the fifth capacitor C5 are grounded. The other end of the first resistor R1 is connected to the non-inverting input of the first amplifier U1. The inverting input of the first amplifier U1 is connected to one end of the second resistor R2 and one end of the third resistor R3. The other end of the second resistor R2 is grounded. The other end of the third resistor R3 is connected to the output of the first amplifier U1 and the non-inverting input of the second amplifier U2. The inverting input of the second amplifier U2 is connected to the second reference voltage VREF2. The output of the second amplifier U2 is connected to the gate of the first MOSFET V1. The source of the first MOSFET V1 is grounded. The drain of the first MOSFET V1 is connected to the first input of the power supply regulator module 1.

[0033] When the aircraft climbs to a high altitude, the low air pressure causes a significant decrease in air insulation strength, leading to an increase in leakage current. If the voltage difference between the main power supply VCC and the casing is small at this time, the voltage reaching the non-inverting input of the first amplifier U1 will be small. The voltage amplified by the first amplifier U1 will be less than the second reference voltage VREF2, and the second amplifier U2 will output a low level. If the voltage difference between the main power supply VCC and the casing is large at this time, the voltage at the non-inverting input of the second amplifier U2 will be higher than the voltage at the inverting input, and the second amplifier U2 will output a high level, triggering the first MOSFET V1 to conduct and discharge the power supply regulator module 1. At this time, the power supply regulator module 1 stops supplying power to the subsequent circuits, and the backup battery E1 supplies power to the subsequent circuits instead. Since the voltage on the backup battery E1 is less than the main power supply VCC, the leakage current is reduced, alleviating the leakage problem at high altitudes.

[0034] In another embodiment: the supply voltage VDD, the first reference voltage VREF1, and the second reference voltage VREF2 can be obtained by further voltage division of the voltage output by the buck converter module 7 or the multi-channel buck converter module 8.

[0035] In this embodiment, please refer to Figure 1 A smart power control method for aircraft includes the following steps: In step S1, when the main power supply VCC is supplied, the voltage is regulated by the power supply regulator module 1 to supply power to the backup battery working module 2 and the subsequent circuit, and the backup battery E1 is charged. Step S2: During the charging process of the backup battery E1, the battery overcharge protection module 3 monitors the charging status of the backup battery E1. If there is a risk of overcharging of the backup battery E1, it controls the backup battery E1 to discharge to avoid overcharging of the backup battery E1. Step S3: If the main power supply VCC is insufficient, the backup battery module 2 will automatically switch to power the subsequent circuit. In step S4, as the aircraft climbs, the air insulation strength decreases. If there is a risk of leakage, the leakage monitoring and control module 4 detects the leakage signal and controls the power supply voltage regulator module 1 to discharge to ground. It automatically switches to the backup battery working module 2 to supply power to the subsequent circuit. Since the output voltage of the backup battery E1 is less than the output voltage of the main power supply VCC, the leakage current is reduced, and the problem of leakage at high altitude is alleviated.

[0036] The working principle of this invention is as follows: Power supply voltage regulator module 1 regulates the introduced main power supply VCC, and the regulated main power supply VCC supplies power to the subsequent circuits and the backup battery working module 2; the backup battery working module 2 charges and stores energy when the main power supply VCC is supplied, and supplies power to the subsequent circuits when the main power supply VCC is insufficient or there is a risk of leakage; the battery overcharge protection module 3 detects whether there is an overcharge risk in the backup battery E1. If there is an overcharge risk, it controls the backup battery E1 to discharge. After the backup battery E1 finishes discharging, it returns to its initial state; the overcharge risk is defined as when the voltage of the backup battery E1 reaches the first reference voltage VREF1, the backup battery E1 continues to charge for a set time (i.e., the second capacitor C2 is charged enough to turn on the sixth transistor V6); the leakage monitoring and control module... 4 is used to detect whether there is a leakage risk when the main power supply VCC is powered. If there is a leakage risk, the power supply regulator module 1 is controlled to discharge. The leakage risk is the voltage difference between the positive terminal of the main power supply VCC and the casing. After rectification, filtering and amplification, the voltage difference is greater than the second reference voltage VREF2. EMI filter 5 is used to suppress electromagnetic interference of the input voltage of the power supply regulator module 1 or the backup battery working module 2, and outputs the voltage after suppressing electromagnetic interference to the overvoltage and overcurrent protection module 6. Overvoltage and overcurrent protection module 6 is used to provide overvoltage and overcurrent protection. Step-down conversion module 7 is used to convert the input voltage to 12V voltage to power the multi-channel step-down conversion module 8. Multi-channel step-down conversion module 8 is used to convert 12V voltage to 1.0V, 1.8V, 1.5V and 3.3V voltage to power the aircraft processor.

[0037] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and not restrictive.

[0038] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An intelligent power control system for aircraft, characterized in that, The intelligent power control system for the aircraft includes: The power supply voltage regulator module is used to regulate the voltage of the main power supply. The regulated main power supply then powers the subsequent circuits and the backup battery working module. The backup battery module is used to charge and store energy when the main power supply is on, and to supply power to the downstream circuit when the main power supply is insufficient or there is a risk of leakage in the main power supply. The battery overcharge protection module is used to detect whether there is an overcharge risk in the backup battery. When there is an overcharge risk, it controls the backup battery to discharge. After the backup battery finishes discharging, it returns to the initial state. The overcharge risk is when the backup battery voltage reaches the first reference voltage, and the backup battery continues to charge for a set time. The leakage current monitoring and control module is used to detect whether there is a leakage current risk when the main power supply is powered. If there is a leakage current risk, the power supply voltage regulator module is controlled to discharge. The leakage current risk is the voltage difference between the positive terminal of the main power supply and the casing, which is greater than the second reference voltage after rectification, filtering and amplification. The first output terminal of the power supply regulator module is connected to the first input terminal of the backup battery working module, the output terminal of the leakage current monitoring and control module is connected to the first input terminal of the power supply regulator module, the first output terminal of the backup battery working module is connected to the input terminal of the battery overcharge protection module, and the output terminal of the battery overcharge protection module is connected to the second input terminal of the backup battery working module.

2. The intelligent power control system for aircraft according to claim 1, characterized in that, The subsequent circuitry includes: An EMI filter is used to suppress electromagnetic interference at the input voltage of the power supply regulator module or backup battery module, and outputs the voltage after suppressing electromagnetic interference to the overvoltage and overcurrent protection module. Overvoltage and overcurrent protection module, used to provide overvoltage and overcurrent protection; The step-down converter module is used to convert the input voltage to 12V voltage to power multiple step-down converter modules; The multi-channel step-down converter module is used to convert 12V voltage to 1.0V, 1.8V, 1.5V, and 3.3V voltage to power the aircraft processor; The input terminal of the EMI filter is connected to the second output terminal of the power supply regulator module and the second output terminal of the backup battery working module. The output terminal of the EMI filter is connected to the input terminal of the overvoltage and overcurrent protection module. The output terminal of the overvoltage and overcurrent protection module is connected to the input terminal of the buck converter module. The output terminal of the buck converter module is connected to the input terminal of the multi-channel buck converter module.

3. The intelligent power control system for aircraft according to claim 1, characterized in that, The power supply regulator module includes a TVS diode, a fourth resistor, a fifth resistor, a sixth resistor, a three-terminal regulator, a third amplifier, a second MOSFET, a first inductor, a first capacitor, and a second diode. The non-inverting input of the third amplifier is connected to one end of the fourth resistor, the negative terminal of the TVS diode, and the main power supply. The positive terminal of the TVS diode is grounded. The other end of the fourth resistor is connected to one end of the fifth resistor and one end of the sixth resistor. The other end of the fifth resistor is grounded. The other end of the sixth resistor is connected to the reference terminal of the three-terminal regulator. The positive terminal of the three-terminal regulator is grounded. The negative terminal of the three-terminal regulator is connected to the gate (G) terminal of the second MOSFET. The drain (D) terminal of the second MOSFET is connected to the output terminal and the inverting input of the third amplifier. The source (S) terminal of the second MOSFET is connected to one end of the first inductor and the output terminal of the leakage current monitoring and control module. The other end of the first inductor is connected to one end of the first capacitor, the positive terminal of the second diode, and the first input terminal of the backup battery working module. The other end of the first capacitor is grounded. The negative terminal of the second diode is connected to the subsequent circuit.

4. The intelligent power control system for aircraft according to claim 1, characterized in that, The backup battery working module includes a third diode, a seventh resistor, a third MOSFET, an eighth resistor, a backup battery, a fourth diode, a fourth MOSFET, and a ninth resistor. The positive terminal of the third diode is connected to the first output terminal of the power supply regulator module. The negative terminal of the third diode is connected to one end of the seventh resistor and the drain (D) terminal of the third MOSFET. The other end of the seventh resistor is connected to the gate (G) terminal of the third MOSFET. The source (S) terminal of the third MOSFET is connected to one end of the eighth resistor. The other end of the eighth resistor is connected to the positive terminal of the fourth diode, the positive terminal of the backup battery, and the drain (D) terminal of the fourth MOSFET. The negative terminal of the fourth diode is connected to the subsequent circuit. The negative terminal of the backup battery is grounded. The gate (G) terminal of the fourth MOSFET is connected to the output terminal of the battery overcharge protection module. The source (S) terminal of the fourth MOSFET is grounded through the ninth resistor.

5. The intelligent power control system for aircraft according to claim 4, characterized in that, The battery overcharge protection module includes a fifth diode, a fifth amplifier, an AND gate, a tenth resistor, a first potentiometer, a second capacitor, an eleventh resistor, a twelfth resistor, a fifth transistor, a sixth transistor, a thirteenth resistor, a seventh diode, a fourteenth resistor, a seventh transistor, a sixth diode, and a third capacitor. One input of the AND gate is connected to the negative terminal of the fifth diode and the output of the differential amplifier circuit. The two inputs of the differential amplifier circuit are respectively connected to the two ends of the eighth resistor. The positive terminal of the fifth diode is grounded. The other input of the AND gate is connected to the output of the fifth amplifier. The inverting input of the fifth amplifier is connected to the first reference voltage, and the non-inverting input of the fifth amplifier is connected to the positive terminal of the backup battery. The output of the AND gate is connected to one end of the tenth resistor, and the other end of the tenth resistor is connected to one end of the first potentiometer. The other end of the bit is connected to one end of the second capacitor, one end of the eleventh resistor, the collector of the seventh transistor, one end of the thirteenth resistor, and the anode of the seventh diode. The other end of the eleventh resistor is connected to the base of the sixth transistor. The emitter of the sixth transistor is grounded. The collector of the sixth transistor is connected to one end of the twelfth resistor and the base of the fifth transistor. The other end of the twelfth resistor is connected to the emitter of the fifth transistor and the supply voltage. The collector of the fifth transistor is connected to the other end of the thirteenth resistor. The cathode of the seventh diode is connected to one end of the fourteenth resistor and the gate of the fourth MOSFET. The other end of the fourteenth resistor is connected to the cathode of the sixth diode and one end of the third capacitor. The other end of the third capacitor is grounded. The anode of the sixth diode is connected to the base of the seventh transistor. The emitter of the seventh transistor is grounded.

6. The intelligent power control system for an aircraft according to any one of claims 1 to 5, characterized in that, The leakage current monitoring and control module includes a first diode, a rectifier, a fourth capacitor, a fifth capacitor, a second inductor, a first resistor, a second resistor, a third resistor, a first amplifier, a second amplifier, and a first MOSFET. The anode of the first diode is connected to the main power supply, the cathode of the first diode is connected to the first terminal of the rectifier, the second terminal of the rectifier is grounded, the third terminal of the rectifier is connected to the casing, the fourth terminal of the rectifier is connected to one end of the fourth capacitor and one end of the second inductor, the other end of the fourth capacitor is grounded, the other end of the second inductor is connected to one end of the fifth capacitor and one end of the first resistor, the other end of the fifth capacitor is grounded, the other end of the first resistor is connected to the non-inverting input of the first amplifier, the inverting input of the first amplifier is connected to one end of the second resistor and one end of the third resistor, the other end of the second resistor is grounded, the other end of the third resistor is connected to the output terminal of the first amplifier and the non-inverting input of the second amplifier, the inverting input of the second amplifier is connected to the second reference voltage, the output terminal of the second amplifier is connected to the gate (G) of the first MOSFET, the source (S) of the first MOSFET is grounded, and the drain (D) of the first MOSFET is connected to the first input terminal of the power supply regulator module.

7. A smart power control method for aircraft, characterized in that, The intelligent power control method for aircraft includes the following steps: When the main power supply is used, the voltage is regulated by the power supply voltage regulator module to supply power to the backup battery working module and the subsequent circuit, and to charge the backup battery. During the charging process of the backup battery, the battery overcharge protection module monitors the charging status of the backup battery. If there is a risk of overcharging, it controls the backup battery to discharge to avoid overcharging. If the main power supply is insufficient, the backup battery module will automatically switch to power the downstream circuits. As the aircraft climbs, the air insulation strength decreases. If there is a risk of leakage, the leakage monitoring and control module will detect the leakage signal and control the power supply voltage regulator module to ground and discharge. It will then automatically switch to the backup battery module to power the subsequent circuits. Since the backup battery output voltage is lower than the main power supply output voltage, the leakage current is reduced, thus alleviating the leakage problem at high altitudes.

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