Aerospace and aviation fuel pump running state monitoring circuit based on micro-processing monitoring chip

Abstract

The invention provides an aerospace fuel pump operation state monitoring circuit based on a micro-processing monitoring chip, and relates to the technical field of aerospace fuel pumps, the device comprises a micro-processing monitoring circuit, a brushless direct current motor Hall sensor, a power supply input circuit and a driving control logic circuit; wherein the micro-processing monitoring circuit is respectively connected with the brushless direct current motor Hall sensor, the power supply input circuit and the driving control logic circuit, and the brushless direct current motor Hall sensor is connected with the driving control logic circuit. According to the invention, a brushless direct current motor operation monitoring hardware circuit of an aerospace pure hardware driver fuel pump is simplified.

Description

Technical Field

[0001] This specification relates to the field of aerospace fuel pump technology, and in particular to an aerospace fuel pump operation status monitoring circuit based on a microprocessor monitoring chip. Background Technology

[0002] In the aerospace field, the stable operation of fuel pumps and fuel supply pumps is directly related to the safety and performance of aircraft. Currently, the motor control system of aerospace low-pressure fuel pumps typically uses hardware IC chips or gate circuits to build logic control, without involving software code control. For motor control of aerospace fuel pumps, commonly used dedicated hardware logic motor control chips such as the MC33035 and UC3625 can achieve basic motor drive control, such as providing appropriate controller logic and overcurrent protection to ensure the motor operates at a certain speed and direction. However, they have significant shortcomings in monitoring motor operating status. From a real-time perspective, when the motor stops abnormally, its speed changes abnormally, or the power input is abnormal, these chips cannot capture these signals, leading to the inability to detect and handle faults in a timely manner, posing a potential threat to the safe and stable operation of aerospace equipment. In terms of monitoring methods, traditional solutions often rely on software algorithms and additional hardware circuits. Software algorithms not only increase development costs and time but may also malfunction due to software vulnerabilities, compatibility issues, or interference from space radiation, leading to monitoring failure. The additional hardware circuitry not only increases the system's size and weight, which contradicts the stringent requirements of aerospace equipment for lightweight, miniaturization, and low cost, but also increases the system's cost. Summary of the Invention

[0003] To address the aforementioned shortcomings in the prior art, this invention provides a simplified hardware circuit for monitoring the operation of a brushless DC motor in aerospace fuel pumps based on a microprocessor monitoring chip.

[0004] To achieve the aforementioned objectives, the technical solution adopted by this invention is: a monitoring circuit for the operating status of an aerospace fuel pump based on a microprocessor monitoring chip, comprising: The system includes a microprocessor monitoring circuit, a brushless DC motor Hall sensor, a power input circuit, and a drive control logic circuit. The microprocessor monitoring circuit is connected to the brushless DC motor Hall sensor, the power input circuit, and the drive control logic circuit, respectively. The brushless DC motor Hall sensor is connected to the drive control logic circuit.

[0005] Furthermore, the microprocessor monitoring circuit includes: The circuit consists of chip U2, resistors R2, R4, R6, R27, Zener diode V5, and grounding capacitor C1. The first pin of chip U2 is connected to one end of resistor R2. The second pin of chip U2 is connected to one end of resistor R27, the output terminal of Zener diode V5, and grounding capacitor C1. The other end of resistor R27 is connected to the 15V voltage terminal. The third pin of chip U2 is grounded to the input terminal of Zener diode V5. The fourth pin of chip U2 is connected to the power input circuit. The fifth pin of chip U2 is connected to the drive control logic circuit. The sixth pin of chip U2 is connected to one end of resistor R6, and the other end of resistor R6 is connected to the brushless DC motor Hall sensor. The seventh pin of chip U2 is connected to one end of resistor R4, and the other end of resistor R4 is connected to the drive control logic circuit. The eighth pin of chip U2 is connected to the other end of resistor R2.

[0006] Furthermore, the brushless DC motor Hall sensor includes: The system includes a motor Hall effect sensor P1, resistors R23, R24, and R25, and grounding capacitors C18, C20, and C22. The first pin of the Hall effect sensor P1 is connected to a 15V voltage terminal, the second pin is grounded, the third pin is connected to one end of resistor R23 and the other end of resistor R6, the fourth pin is connected to one end of resistor R24, the fifth pin is connected to one end of resistor R25, the other end of resistor R23 and grounding capacitor C18 are both connected to the drive control logic circuit, the other end of resistor R24 ​​and grounding capacitor C20 are both connected to the drive control logic circuit, and the other end of resistor R25 and grounding capacitor C22 are both connected to the drive control logic circuit.

[0007] Furthermore, the power input circuit includes: The circuit consists of resistors R1, R3, and R5; capacitors C2, C3, C4, and C5; a TVS diode V2; and a chip U1. One end of resistor R1 is connected to the 28V input terminal. The other end of resistor R1 is connected to one end of resistor R3, one end of capacitor C2, the first pin of chip U1, and one end of TVS diode V2. The other end of resistor R3 is connected to grounding resistor R5, grounding capacitor C5, and the fourth pin of chip U2. The other end of TVS diode V2, the other end of resistor C2, the third pin of chip U1, the negative terminal of polarized capacitor C4, and one end of capacitor C3 are grounded. The second pin of chip U1, the positive terminal of polarized capacitor C4, and the other end of capacitor C3 are all connected to the 15V voltage terminal.

[0008] Furthermore, the drive control logic circuit includes: Resistors R7, R8, R10, R11, R12, R14, R15, R16, R17, R19, R21, R22; transistor V3; capacitors C6, C8, C9, C10, C11, C12, C13, C16, C17, C19, C21; and chip U3. The first pin of chip U3 is connected to one end of resistor R8 and the grounding capacitor C6. The other end of resistor R8 is connected to one end of resistor R7, the third pin of transistor V3, and the grounding resistor R11. The other end of resistor R7 is connected to... With the 5V voltage terminal connected, the first pin of transistor V3 is connected to the other end of resistor R4, and the second pin of transistor V3 is grounded. The second pin of chip U3 is connected to the 5V voltage terminal, the grounding capacitor C12, and one end of resistor R14. The third pin of chip U3 is connected to the grounding capacitor C13. The fourth and fifteenth pins of chip U3 are grounded. The sixth pin of chip U3 is connected to the other end of resistor R14 and the grounding resistor R19. The seventh pin of chip U3 is connected to one end of resistor R21 and the grounding capacitor C16. The other end of resistor R21 is connected to the twentieth pin of chip U3. The eighth pin of chip U3 is connected to the other end of resistor R23. One end of the resistor is connected to the grounding capacitor C18. The ninth pin of chip U3 is connected to the other end of resistor R24 ​​and the grounding capacitor C20. The tenth pin of chip U3 is connected to the other end of resistor R25 and the grounding capacitor C22. The eleventh pin of chip U3 is connected to the 15V voltage terminal and the grounding capacitor C21. The nineteenth pin of chip U3 is connected to the grounding capacitor C19 and the 15V voltage terminal. The twenty-first pin of chip U3 is connected to the grounding resistor R22 and the grounding capacitor C17. The twenty-second pin of chip U3 is connected to one end of resistor R16, and the other end of resistor R16 is connected to the 5V voltage terminal. The twenty-third pin of chip U3 is connected to the core... The fifth pin of chip U2 is connected to the ground capacitor C10 and one end of resistor R17 respectively. The other end of resistor R17 is connected to the 5V voltage terminal. The twenty-fifth and twenty-sixth pins of chip U3 are connected to the ground capacitor C11 and one end of resistor R15 respectively. The other end of resistor R15 is connected to the 5V voltage terminal. The twenty-seventh pin of chip U3 is connected to one end of resistor R10. The other end of resistor R10 is connected to one end of capacitor C8. The twenty-eighth pin of chip U3 is connected to the other end of capacitor C8 and one end of resistor R12 respectively. The other end of resistor R12 and ground capacitor C9 are both connected to the output terminal.

[0009] The beneficial effects of the present invention are as follows: The present invention provides an aerospace fuel pump operation status monitoring circuit based on a microprocessor monitoring chip. By monitoring the Hall signal square wave output by the brushless DC motor and the power input voltage, the motor operation status is judged in real time, ensuring the stable and reliable operation of the fuel pump and the fuel supply pump. The pure hardware motor control scheme based on the microprocessor monitoring circuit realizes the real-time monitoring of the operation status of the brushless DC motor and the power supply voltage, which significantly improves the reliability and safety of the aerospace fuel pump. Without significantly increasing the cost and volume, the motor control performance is optimized to ensure that the fuel pump and the fuel supply pump work stably and efficiently in the complex and ever-changing aerospace environment, meeting the requirements of the aerospace field for high reliability, high performance and real-time performance of equipment. (1) The watchdog function of MAX706 is used to monitor the rotation status of the motor in real time. When the motor does not work, the reset mechanism is automatically triggered to ensure that the motor can continue to operate stably, greatly improving the reliability of the system and reducing the risk of equipment downtime due to motor failure. (2) The power supply voltage is monitored in real time by MAX706. When the input power supply is over-voltage or under-voltage, the control of the motor is stopped immediately to protect the hardware circuit from damage by abnormal voltage, enhance the safety and stability of the system, and reduce the probability of hardware damage. Attached Figure Description

[0010] This specification will be further described by way of exemplary embodiments, which will be described in detail with reference to the accompanying drawings. These embodiments are not limiting; in these embodiments, the same reference numerals denote the same structures, wherein: Figure 1 This is an exemplary structural diagram of an aerospace fuel pump operation status monitoring circuit based on a microprocessor monitoring chip, as shown in some embodiments of this specification. Figure 2 This is an exemplary schematic diagram of a microprocessor monitoring circuit according to some embodiments of this specification; Figure 3 This is an exemplary schematic diagram of a brushless DC motor Hall sensor according to some embodiments of this specification; Figure 4 This is an exemplary schematic diagram of a power input circuit according to some embodiments of this specification; Figure 5 This is an exemplary schematic diagram of a drive control logic circuit according to some embodiments of this specification. Detailed Implementation

[0011] The specific embodiments of the present invention are described below to enable those skilled in the art to understand the present invention. However, it should be understood that the present invention is not limited to the scope of the specific embodiments. For those skilled in the art, various changes are obvious as long as they are within the spirit and scope of the present invention as defined and determined by the appended claims. All inventions utilizing the concept of the present invention are protected.

[0012] Example Figure 1 This is an exemplary structural diagram of an aerospace fuel pump operation status monitoring circuit based on a microprocessor monitoring chip, as shown in some embodiments of this specification.

[0013] In some embodiments, an aerospace fuel pump operation status monitoring circuit based on a microprocessor monitoring chip may include a microprocessor monitoring circuit, a brushless DC motor Hall sensor, a power input circuit, and a drive control logic circuit; wherein, the microprocessor monitoring circuit is connected to the brushless DC motor Hall sensor, the power input circuit, and the drive control logic circuit respectively, and the brushless DC motor Hall sensor is connected to the drive control logic circuit.

[0014] In some embodiments, such as Figure 2 As shown, the microprocessor monitoring circuit includes: chip U2, resistors R2, R4, R6, R27, Zener diode V5, and grounding capacitor C1; wherein, the first pin of chip U2 is connected to one end of resistor R2, the second pin of chip U2 is connected to one end of resistor R27, the output terminal of Zener diode V5, and grounding capacitor C1 respectively, the other end of resistor R27 is connected to the 15V voltage terminal, the third pin of chip U2 and the input terminal of Zener diode V5 are grounded, the fourth pin of chip U2 is connected to the power input circuit, the fifth pin of chip U2 is connected to the drive control logic circuit, the sixth pin of chip U2 is connected to one end of resistor R6, the other end of resistor R6 is connected to the brushless DC motor Hall sensor, the seventh pin of chip U2 is connected to one end of resistor R4, the other end of resistor R4 is connected to the drive control logic circuit, and the eighth pin of chip U2 is connected to the other end of resistor R2.

[0015] In some embodiments, 28V can be supplied as 15V through an LDO.

[0016] In some embodiments, chip U2 can be a MAX706 chip. The MAX706 is a CMOS microprocessor microprocessor monitoring circuit with reset output, watchdog function and power monitoring function. If the watchdog monitoring input signal does not switch level within 1.6s, the watchdog will output a low-level reset signal to restore the system to normal and prevent abnormal system operation.

[0017] In some embodiments, the WDI pin of the MAX706 chip is connected to the HA of the Hall sensor for the brushless DC motor. When there is no signal input to HA, the REST output is high, setting the motor speed to 0 and restarting the motor controller logic. The PFI pin of the MAX706 chip is connected to the power supply voltage divider input line to monitor the power supply voltage. When the power input is greater than 42.67V, the voltage divider between R3 and R5 is greater than 1.25V, and the MAX706T output PFO is high, disabling the PWM output of the professional motor control chip; when the power input is less than 15V, the output of the V5 regulator is less than 4.65V, setting the motor speed to 0 and protecting the hardware circuit.

[0018] In some embodiments, such as Figure 3 As shown, the brushless DC motor Hall sensor includes: a motor Hall plate P1, resistors R23, R24, and R25, and grounding capacitors C18, C20, and C22. The first pin of the motor Hall plate P1 is connected to a 15V voltage terminal, the second pin of the motor Hall plate P1 is grounded, the third pin of the motor Hall plate P1 is connected to one end of resistor R23 and the other end of resistor R6, the fourth pin of the motor Hall plate P1 is connected to one end of resistor R24, the fifth pin of the motor Hall plate P1 is connected to one end of resistor R25, the other end of resistor R23 and grounding capacitor C18 are both connected to the drive control logic circuit, the other end of resistor R24 ​​and grounding capacitor C20 are both connected to the drive control logic circuit, and the other end of resistor R25 and grounding capacitor C22 are both connected to the drive control logic circuit.

[0019] In some embodiments, the brushless DC permanent magnet motor employs Hall signal feedback control, with three Hall sensors outputting square wave signals during motor rotation; the expression for the motor speed can be: ; Where N represents the number of pole pairs of the motor, RPM represents the motor speed, and f represents the frequency of the Hall signal.

[0020] RPM motor speed is directly proportional to the frequency of the Hall effect signal. Monitoring the Hall frequency reveals the motor's operating status. Microcontrollers (MCUs) typically use software to monitor this frequency to determine motor rotation, but aerospace fuel pumps are purely hardware-based and cannot use MCUs or corresponding software calculations. The general hardware approach to detecting motor speed involves converting the Hall effect signal into a corresponding voltage value, comparing this voltage value to a set threshold voltage to determine motor rotation. This method involves numerous complex components and low reliability.

[0021] In some embodiments, such as Figure 4As shown, the power input circuit includes: resistors R1, R3, and R5; capacitors C2, C3, C4, and C5; a TVS diode V2; and a chip U1. One end of resistor R1 is connected to the 28V input terminal. The other end of resistor R1 is connected to one end of resistor R3, one end of capacitor C2, the first pin of chip U1, and one end of TVS diode V2. The other end of resistor R3 is connected to grounding resistor R5, grounding capacitor C5, and the fourth pin of chip U2. The other end of TVS diode V2, the other end of resistor C2, the third pin of chip U1, the negative terminal of polarized capacitor C4, and one end of capacitor C3 are grounded. The second pin of chip U1, the positive terminal of polarized capacitor C4, and the other end of capacitor C3 are all connected to the 15V voltage terminal.

[0022] In some embodiments, the MAX706 chip operates at a voltage range of 1~5.5V and a current of approximately 1mA. The VCC voltage monitoring threshold at pin 2 is 4.65V; the PFI voltage monitoring threshold at pin 4 is 1.25V. These voltages are used to monitor the product's power supply.

[0023] In some embodiments, the overvoltage monitoring and protection strategy is as follows: the PFI voltage at pin 4 of the chip monitors the bus overvoltage. The monitoring method for the input bus voltage is: VPFI = V ÷ (R3 + R5) × R5. According to the PFI voltage comparison threshold in MAX706, VPFI = 1.25V, resistor R3 is 169KΩ, and resistor R5 is 5.1KΩ. When the Vinput input voltage is greater than 42.67V, the chip pin 5PFO outputs.

[0024] In some embodiments, the undervoltage monitoring and protection strategy is as follows: the Vcc voltage at pin 2 of the chip monitors a 15V undervoltage signal. The secondary power supply of 15V is obtained through conversion by the CW7815. According to the conversion characteristics of the CW7815, when the Vinput input voltage is lower than 15V, the output voltage is approximately equal to the output voltage. Therefore, the 15Vout voltage can be monitored to monitor the low voltage condition of the monitoring bus.

[0025] The voltage is limited by resistor R27 in series with the Zener diode V5. After regulation, V5 provides power to the MAX706. V5 is a 5.1V Zener diode (4.8~5.4V). The minimum voltage regulation across the entire temperature range is approximately 4.8V, which is greater than the monitoring threshold of 4.65V. It should not malfunction under normal conditions.

[0026] When Vinput≈15Vout<15V, after the voltage divider R27 and R28, the voltage of V5 is lower than 4.8V, and V5 exhibits a high-resistivity state with a leakage current in the range of μA.

[0027] In some embodiments, the voltage expression of Zener diode V5 is: V5 = 15Vout ÷ (R27 + R28) × R28, the voltage comparison threshold V5 = 4.65V, the resistor R27 is 2KΩ, the resistor R28 is 1.1KΩ, and the chip pin 8 WDO is activated when the 15Vout input voltage is less than 13V.

[0028] Traditional hardware circuits require at least a frequency-to-voltage converter, a voltage reference chip, and a comparator circuit. This ingenious design cleverly utilizes a single MAX706 chip to monitor both motor speed and bus over / under voltage.

[0029] In some embodiments, such as Figure 5As shown, the drive control logic circuit includes: resistors R7, R8, R10, R11, R12, R14, R15, R16, R17, R19, R21, and R22; transistor V3; capacitors C6, C8, C9, C10, C11, C12, C13, C16, C17, C19, and C21; and chip U3. The first pin of chip U3 is connected to one end of resistor R8 and the grounded capacitor C6. The other end of resistor R8 is connected to one end of resistor R7, the third pin of transistor V3, and the grounded resistor R11. Connect the other end of resistor R7 to the 5V voltage terminal. Connect the first pin of transistor V3 to the other end of resistor R4. Connect the second pin of transistor V3 to ground. Connect the second pin of chip U3 to the 5V voltage terminal, the grounding capacitor C12, and one end of resistor R14. Connect the third pin of chip U3 to the grounding capacitor C13. Connect the fourth and fifteenth pins of chip U3 to ground. Connect the sixth pin of chip U3 to the other end of resistor R14 and the grounding resistor R19. Connect the seventh pin of chip U3 to one end of resistor R21 and the grounding capacitor C16. Connect the other end of resistor R21 to the twentieth pin of chip U3. Connect the eighth pin of chip U3 to... The other end of resistor R23 is connected to grounding capacitor C18. Pin 9 of chip U3 is connected to the other end of resistor R24 ​​and grounding capacitor C20. Pin 10 of chip U3 is connected to the other end of resistor R25 and grounding capacitor C22. Pin 11 of chip U3 is connected to the 15V voltage terminal and grounding capacitor C21. Pin 19 of chip U3 is connected to grounding capacitor C19 and the 15V voltage terminal. Pin 21 of chip U3 is connected to grounding resistor R22 and grounding capacitor C17. Pin 22 of chip U3 is connected to one end of resistor R16. The other end of resistor R16 is connected to the 5V voltage terminal. Pin 23 of chip U3... Pin 5 is connected to pin 5 of chip U2. Pin 24 of chip U3 is connected to one end of ground capacitor C10 and resistor R17. The other end of resistor R17 is connected to the 5V voltage terminal. Pins 25 and 26 of chip U3 are connected to one end of ground capacitor C11 and resistor R15. The other end of resistor R15 is connected to the 5V voltage terminal. Pin 27 of chip U3 is connected to one end of resistor R10. The other end of resistor R10 is connected to one end of capacitor C8. Pin 28 of chip U3 is connected to the other end of capacitor C8 and one end of resistor R12. The other end of resistor R12 and ground capacitor C9 are both connected to the output terminal.

[0030] In some embodiments, the second pin of chip U3 can output a 5V voltage on its own.

[0031] Working principle: Connect the VCC pin of the MAX706 chip to a stable positive power supply and the GND pin to a negative power supply to provide operating power to the chip; connect the output pins of the brushless DC motor Hall sensor to the watchdog monitoring pins of the MAX706 to ensure that the signal can be accurately transmitted to the MAX706 for monitoring; connect the voltage monitoring pin of the MAX706 to the power input line through appropriate voltage divider resistors and other circuits to accurately acquire the power supply voltage signal; connect the reset signal output pin of the MAX706 to the reset terminal of the motor control circuit, and connect the control signal output pin to the enable terminal of the motor control circuit to realize the control of the motor.

[0032] Based on the normal speed of the brushless DC motor and the characteristics of the Hall signal, an appropriate watchdog time is set within the MAX706. For example, if the minimum transition period of the Hall signal is 1.6 seconds when the motor is running normally, this ensures timely detection of motor stoppage without false alarms. A reasonable undervoltage threshold is set in the MAX706 according to the normal operating voltage range of the aerospace equipment power supply. For instance, if the normal operating voltage is 28V±2V, the undervoltage threshold can be set to 13V. When the power supply voltage is detected to be below 13V, the motor is immediately stopped.

[0033] The MAX706's watchdog function WDI pin is connected to the output of the brushless DC motor's Hall sensor. The Hall sensor converts the motor's mechanical rotation into an electrical signal. When the motor is rotating normally, its output Hall signal exhibits periodic transitions. The MAX706 continuously monitors this signal and has an internally set watchdog timer. When a Hall signal transition is detected within the set watchdog time, the motor is determined to be rotating; if no transition is detected within this time period, the motor is determined to be stopped. Once the motor is determined to be not rotating, the MAX706 automatically sends a reset signal to the motor control circuit, attempting to restart the motor speed control to restore normal operation and maintain continuous motor operation.

[0034] The MAX706's voltage monitoring pin PFI is connected to the power input line for overvoltage detection, and the power supply VCC uses a Zener diode to collect the secondary power supply voltage for undervoltage detection. The power input of aerospace equipment is susceptible to various factors, such as changes in aircraft attitude and power system fluctuations, resulting in voltage fluctuations. The MAX706 integrates circuits such as a voltage comparator. When it detects that the power supply voltage is lower than a preset undervoltage threshold, it immediately outputs a control signal to the motor control circuit, stopping the motor. This effectively prevents hardware circuits from being subjected to excessively high or low voltages due to power supply abnormalities, thus protecting the hardware safety of the entire system and preventing malfunctions and damage caused by power supply problems.

[0035] In some embodiments of this specification, an aerospace fuel pump operation status monitoring circuit based on a microprocessor monitoring chip is provided. By monitoring the Hall signal square wave output by the brushless DC motor and the power input voltage, the motor operation status is judged in real time, ensuring the stable and reliable operation of the fuel pump and the fuel supply pump. The pure hardware motor control scheme based on the microprocessor monitoring circuit realizes the real-time monitoring of the operation status of the brushless DC motor and the power supply voltage, which significantly improves the reliability and safety of the aerospace fuel pump. Without significantly increasing the cost and volume, the motor control performance is optimized to ensure that the fuel pump and the fuel supply pump work stably and efficiently in the complex and ever-changing aerospace environment, meeting the requirements of the aerospace field for high reliability, high performance and real-time performance of equipment. (1) The watchdog function of MAX706 is used to monitor the rotation status of the motor in real time. When the motor does not work, the reset mechanism is automatically triggered to ensure that the motor can continue to operate stably, greatly improving the reliability of the system and reducing the risk of equipment downtime due to motor failure. (2) The power supply voltage is monitored in real time by MAX706. When the input power supply is undervoltage, the control of the motor is stopped immediately to protect the hardware circuit from damage by abnormal voltage, enhance the safety and stability of the system, and reduce the probability of hardware damage.

Claims

1. A microprocessor-based monitoring circuit for monitoring the operating state of an aerospace fuel pump, comprising: a microprocessor; a memory coupled to the microprocessor; a plurality of sensors coupled to the microprocessor; and a plurality of indicators coupled to the microprocessor. Comprise: Micro-processing monitoring circuit, brushless DC motor Hall sensor, power input circuit and drive control logic circuit; wherein, wherein the micro-processing monitoring circuit monitors the motor operation and power state, the brushless DC motor Hall sensor feeds back the motor rotor position, the drive control logic circuit outputs the corresponding full-bridge control signal according to the input brushless DC motor Hall signal to make the motor rotate, the power input circuit is used for converting the input 28VDC into 15VDC to provide power for other currents, the micro-processing monitoring circuit is connected with the brushless DC motor Hall sensor, the power input circuit and the drive control logic circuit respectively, the brushless DC motor Hall sensor is connected with the drive control logic circuit.

2. The microprocessor-based monitoring chip-based aerospace fuel pump operating condition monitoring circuit according to claim 1, characterized in that, The micro-processing monitoring circuit comprises: Chip U2, resistor R2, resistor R4, resistor R6, resistor R27, voltage stabilizing diode V5 and ground capacitor C1; wherein, the first pin of chip U2 is connected with one end of resistor R2, the second pin of chip U2 is connected with one end of resistor R27, the output end of voltage stabilizing diode V5 and ground capacitor C1 respectively, the other end of resistor R27 is connected with 15V voltage end, the third pin of chip U2 and the input end of voltage stabilizing diode V5 are grounded, the fourth pin of chip U2 is connected with the power input circuit, the fifth pin of chip U2 is connected with the drive control logic circuit, the sixth pin of chip U2 is connected with one end of resistor R6, the other end of resistor R6 is connected with the brushless DC motor Hall sensor, the seventh pin of chip U2 is connected with one end of resistor R4, the other end of resistor R4 is connected with the drive control logic circuit, the eighth pin of chip U2 is connected with the other end of resistor R2.

3. The microprocessor-based chip monitoring circuit for monitoring the operating state of an aerospace fuel pump according to claim 2, wherein The brushless DC motor Hall sensor comprises: Motor Hall board P1, resistor R23, resistor R24, resistor R25, ground capacitor C18, ground capacitor C20 and ground capacitor C22; wherein, the first pin of motor Hall board P1 is connected with 15V voltage end, the second pin of motor Hall board P1 is grounded, the third pin of motor Hall board P1 is connected with one end of resistor R23 and the other end of resistor R6 respectively, the fourth pin of motor Hall board P1 is connected with one end of resistor R24, the fifth pin of motor Hall board P1 is connected with one end of resistor R25, the other end of resistor R23 and ground capacitor C18 are connected with the drive control logic circuit respectively, the other end of resistor R24 and ground capacitor C20 are connected with the drive control logic circuit respectively, the other end of resistor R25 and ground capacitor C22 are connected with the drive control logic circuit respectively.

4. The microprocessor-based chip monitoring circuit for monitoring the operating state of an aerospace fuel pump according to claim 2, wherein The power input circuit comprises: The resistor R1, the resistor R3, the resistor R5, the capacitor C2, the capacitor C3, the capacitor C4, the capacitor C5, the TVS tube V2 and the chip U1; wherein one end of the resistor R1 is connected with the 28V input end, the other end of the resistor R1 is respectively connected with one end of the resistor R3, one end of the capacitor C2, the first pin of the chip U1 and one end of the TVS tube V2, the other end of the resistor R3 is respectively connected with the ground resistor R5, the ground capacitor C5 and the fourth pin of the chip U2, the other end of the TVS tube V2, the other end of the capacitor C2, the third pin of the chip U1, the negative pole of the polar capacitor C4 and one end of the capacitor C3 are grounded, the second pin of the chip U1, the positive pole of the polar capacitor C4 and the other end of the capacitor C3 are connected with the 15V voltage end.

5. The microprocessor-based chip monitoring circuit for monitoring the operating state of an aerospace fuel pump according to claim 3, wherein The driving control logic circuit comprises: The resistance R7, the resistance R8, the resistance R10, the resistance R11, the resistance R12, the resistance R14, the resistance R15, the resistance R16, the resistance R17, the resistance R19, the resistance R21, the resistance R22, the triode V3, the capacitor C6, the capacitor C8, the capacitor C9, the capacitor C10, the capacitor C11, the capacitor C12, the capacitor C13, the capacitor C16, the capacitor C17, the capacitor C19, the capacitor C21 and the chip U3; wherein the first pin of the chip U3 is connected with one end of the resistance R8 and the ground capacitor C6, the other end of the resistance R8 is connected with one end of the resistance R7, the third pin of the triode V3 and the ground resistance R11 respectively, the other end of the resistance R7 is connected with the 5V voltage terminal, the first pin of the triode V3 is connected with the other end of the resistance R4, the second pin of the triode V3 is grounded, the second pin of the chip U3 is connected with the 5V voltage terminal, the ground capacitor C12 and one end of the resistance R14 respectively, the third pin of the chip U3 is connected with the ground capacitor C13, the fourth pin and the fifteenth pin of the chip U3 are grounded, the sixth pin of the chip U3 is connected with the other end of the resistance R14 and the ground resistance R19 respectively, the seventh pin of the chip U3 is connected with one end of the resistance R21 and the ground capacitor C16 respectively, the other end of the resistance R21 is connected with the twentieth pin of the chip U3, the eighth pin of the chip U3 is connected with the other end of the resistance R23 and the ground capacitor C18 respectively, the ninth pin of the chip U3 is connected with the other end of the resistance R24 and the ground capacitor C20 respectively, the tenth pin of the chip U3 is connected with the other end of the resistance R25 and the ground capacitor C22 respectively, the eleventh pin of the chip U3 is connected with the 15V voltage terminal and the ground capacitor C21 respectively, the nineteenth pin of the chip U3 is connected with the ground capacitor C19 and the 15V voltage terminal respectively, the twenty-first pin of the chip U3 is connected with the ground resistance R22 and the ground capacitor C17 respectively, the twenty-second pin of the chip U3 is connected with one end of the resistance R16, the other end of the resistance R16 is connected with the 5V voltage terminal, the twenty-third pin of the chip U3 is connected with the fifth pin of the chip U2, the twenty-fourth pin of the chip U3 is connected with the ground capacitor C10 and one end of the resistance R17 respectively, the other end of the resistance R17 is connected with the 5V voltage terminal, the twenty-fifth pin of the chip U3 and the twenty-sixth pin of the chip U3 are connected with the ground capacitor C11 and one end of the resistance R15 respectively, the other end of the resistance R15 is connected with the 5V voltage terminal, the twenty-seventh pin of the chip U3 is connected with one end of the resistance R10, the other end of the resistance R10 is connected with one end of the capacitor C8, the twenty-eighth pin of the chip U3 is connected with the other end of the capacitor C8 and one end of the resistance R12 respectively, the other end of the resistance R12 and the ground capacitor C9 are connected with the output terminal.

Images