An on-board power control system for powering airport aircraft

Abstract

The present invention discloses an on-board power supply control system for powering airport aircraft, comprising an inverter module, a dual-output DC-DC module, a rectifier module, an energy storage module, and a control module. The control module is connected to the energy storage module, the rectifier module, and the dual-output DC-DC module. The dual-output DC-DC module is connected to the inverter module. The control module comprises a detection unit, an adjustment unit, and a first control unit. The detection unit is used to detect the cable type and connection status of the on-board power supply and based on this, feed back an AC or DC power demand signal to the adjustment unit. The adjustment unit is used to set the DC power supply specification and feed back an adjustment signal to the dual-output DC-DC module. The first control unit feeds back a switching signal to the adjustment unit and automatically resets the test time based on the set test time and whether a verification pass signal is obtained within the test time.

Description

Technical Field

[0001] The invention relates to the technical field of aviation ground power supply, and in particular to a vehicle-mounted power supply control system for powering aircraft at an airport. Background Art

[0002] When existing aircraft are powered on the ground, three-phase 400Hz, 115VAC AC power standards are generally used to meet the needs of reducing weight and improving efficiency. However, due to the diversity of aircraft types and aviation needs, aircraft's requirements for ground DC power are different. Therefore, the on-board power control system for airport aircraft power supply needs to be flexible and can provide both AC power and adapt to a variety of DC power specifications. When the on-board power supply is connected to the aircraft power socket through a cable, the aircraft's external power system will strictly test the quality of the external power supply. Once the test is verified, the electronic equipment in the aircraft will seamlessly switch to the external power supply, and automatically cut off the aircraft's internal power supply system. In order to meet the aircraft's diverse specifications for ground DC power, the existing on-board power control system has adopted a variety of strategies. Some systems are equipped with DC power output terminals of multiple specifications for operators to connect cables according to needs, while others are... Multiple sets of cables are designed for the output ends of DC power supplies of different specifications, so that operators can select and connect them according to the needs of the aircraft. There are also systems that allow operators to manually adjust the output voltage of the on-board power supply according to the specifications of the required DC power supply. These on-board power supply control systems will undoubtedly increase the number of cables on the on-board power supply, the number of configuration interfaces of the DC power supply specifications, and the quality requirements for operators. Therefore, an on-board power supply control system for airport aircraft power supply is proposed. The waiting time can be set based on the detection and verification of the external power supply by the external power supply system of the aircraft, and the output voltage of the on-board power supply can be automatically adjusted according to the set waiting time and whether the verification pass signal is obtained within the waiting time. After each adjustment, the waiting time is automatically reset until the aircraft's DC power supply specifications for the ground are met, thereby reducing the number of cables and configuration interfaces of the on-board power supply specifications, reducing the quality requirements for operators, and improving the flexibility of power supply. Summary of the invention

[0003] In view of the above technical problems, the purpose of the present invention is to provide an on-board power supply control system for powering airport aircraft, comprising an inverter module, a dual-output DC-DC module, a rectifier module, an energy storage module, and a control module. The control module is connected to the energy storage module, the rectifier module, and the dual-output DC-DC module. The dual-output DC-DC module is connected to the inverter module. The control module comprises a detection unit, an adjustment unit, and a first control unit. The detection unit is used to detect the cable type and connection status of the on-board power supply and based on this, feedback an AC or DC power demand signal to the adjustment unit. The adjustment unit is used to set the DC power supply specification and feedback the adjustment signal to the dual-output DC-DC module. The first control unit feedbacks a switching signal to the adjustment unit and automatically resets the inspection time based on the set inspection time and whether a verification pass signal is obtained within the inspection time.

[0004] Further, the first control unit includes a first operational amplifier U1, a second operational amplifier U2, a first field effect transistor Q1, a third field effect transistor Q3, a second diode D2, a sixth diode D6, a first capacitor C1, a first connector P1, a second connector P2, a third connector P3, a first resistor R1, a second resistor R2, a third resistor R3, a sixth resistor R6, an eighth resistor R8, and a ninth resistor R9;

[0005] The first operational amplifier U1 is connected to the same phase end with one end of the first resistor R1, one end of the second resistor R2, and the anode of the second diode D2; the first operational amplifier U1 is connected to the opposite phase end with one end of the third resistor R3; the first operational amplifier U1 output end is connected to the drain of the first field effect transistor Q1, the drain of the third field effect transistor Q3, and the other end of the third resistor R3; the second operational amplifier U2 is connected to the same phase end with the source of the third field effect transistor Q3, one end of the sixth resistor R6, and one end of the first capacitor C1; the second operational amplifier U2 is connected to the opposite phase end with one end of the eighth resistor R8, the second diode D2 The cathode of D2 is connected, the output end of the second operational amplifier U2 is connected to one end of the ninth resistor R9 and the end of the third connector P3, the gate of the first field effect transistor Q1 is connected to the cathode of the sixth diode D6, the gate of the third field effect transistor Q3 is connected to the end of the first connector P1, the anode of the sixth diode D6 is connected to the end of the second connector P2, the other end of the first resistor R1 is connected to the power supply, the other end of the second resistor R2, the other end of the sixth resistor R6, the other end of the eighth resistor R8, the other end of the ninth resistor R9, the other end of the first capacitor C1, the source of the first field effect transistor Q1 and the ground are connected.

[0006] Further, the first control unit also includes a third operational amplifier U3, a fourth operational amplifier U4, a second triode Q2, a first diode D1, a third diode D3, a fourth diode D4, a fifth diode D5, a seventh resistor R7, a tenth resistor R10, an eleventh resistor R11, a twelfth resistor R12, a thirteenth resistor R13, a fourteenth resistor R14, a fifteenth resistor R15, and a sixteenth resistor R16;

[0007] The third operational amplifier U3 is connected at the same phase end to one end of the seventh resistor R7 and one end of the sixteenth resistor R16, the third operational amplifier U3 is connected at the inverting end to one end of the first capacitor C1, the output end of the third operational amplifier U3 is connected to one end of the fourteenth resistor R14 and the anode of the fourth diode D4, the fourth operational amplifier U4 is connected at the same phase end to one end of the eleventh resistor R11, one end of the thirteenth resistor R13, the cathode of the first diode D1, the cathode of the third diode D3, and the collector of the second transistor Q2, the fourth operational amplifier U4 is connected at the inverting end to one end of the tenth resistor R10, one end of the twelfth resistor R12, and the cathode of the fourth diode D4, and the fourth operational amplifier U The output end is connected to the anode of the first diode D1 and the anode of the fifth diode D5, the base of the second triode Q2 is connected to the end of the first connector P1, the emitter of the second triode Q2 is connected to one end of the fifteenth resistor R15, the anode of the third diode D3 is connected to the end of the third connector P3, the cathode of the fifth diode D5 is connected to the cathode of the sixth diode D6, the other end of the seventh resistor R7, the other end of the eleventh resistor R11, the other end of the twelfth resistor R12, and the other end of the fifteenth resistor R15 are connected to the power supply, and the other end of the tenth resistor R10, the other end of the thirteenth resistor R13, the other end of the fourteenth resistor R14, and the other end of the sixteenth resistor R16 are connected to the ground end.

[0008] Further, the control module also includes a second control unit, which includes a fourth transistor Q4, a first conversion switch S1, a second switch S2, a fourth connector P4, a fifth connector P5, a sixth connector P6, a seventeenth resistor R17, an eighteenth resistor R18, and a nineteenth resistor R19;

[0009] The collector of the fourth transistor Q4 is connected to one end of the nineteenth resistor R19, the emitter of the fourth transistor Q4 is connected to one end of the eighteenth resistor R18 and the positive electrode of the first conversion switch S1, the base of the fourth transistor Q4 is connected to one end of the seventeenth resistor R17, the second end of the first conversion switch S1, the positive electrode of the second switch S2, and the end of the sixth connector P6, the first end of the first conversion switch S1 is connected to the end of the fourth connector P4, the common end of the first conversion switch S1 is connected to the end of the fifth connector P5, the other end of the nineteenth resistor R19 is connected to the power supply, and the negative electrode of the first conversion switch S1, the negative electrode of the second switch S2, the other end of the seventeenth resistor R17, the other end of the eighteenth resistor R18 and the ground are connected.

[0010] Furthermore, the first control unit also includes a fourth resistor R4 and a fifth resistor R5;

[0011] One end of the fourth resistor R4 is connected to the gate of the first field effect transistor Q1, one end of the fifth resistor R5 is connected to the gate of the third field effect transistor Q3, and the other ends of the fourth resistor R4 and the fifth resistor R5 are connected to the ground.

[0012] Furthermore, the first capacitor C1 is an adjustable capacitor.

[0013] The beneficial effects of the present invention compared with the prior art are:

[0014] The present invention can set a waiting time based on the detection and verification of the external power supply by the external power supply system of the aircraft, and automatically adjust the output voltage of the on-board power supply according to the set waiting time and whether a verification pass signal is obtained within the waiting time, and automatically reset the waiting time after each adjustment until the specification requirements of the aircraft for the ground DC power supply are met, so as to reduce the number of cables of the on-board power supply and the configuration interfaces of the DC power supply specifications, reduce the quality requirements for operators, and improve the power supply flexibility. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the prior art and the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0016] Figure 1 The overall structure diagram provided by the present invention.

[0017] Figure 2 This is a circuit structure diagram of the first control unit provided by the present invention.

[0018] Figure 3 This is a circuit structure diagram of the second control unit provided by the present invention. DETAILED DESCRIPTION

[0019] In order to make the objects and advantages of the present invention more clearly understood, the present invention is specifically described below in conjunction with embodiments. It should be understood that the following text is only used to describe one or several specific implementations of the present invention, and does not strictly limit the scope of protection specifically requested by the present invention.

[0020] The present invention discloses an on-board power supply control system for powering airport aircraft, comprising an inverter module, a dual-output DC-DC module, a rectifier module, an energy storage module, and a control module. The control module is connected to the energy storage module, the rectifier module, and the dual-output DC-DC module. The dual-output DC-DC module is connected to the inverter module. The control module comprises a detection unit, an adjustment unit, and a first control unit. The detection unit is used to detect the cable type and connection status of the on-board power supply and based on this, feed back an AC or DC power demand signal to the adjustment unit. The adjustment unit is used to set the DC power supply specification and feed back an adjustment signal to the dual-output DC-DC module. The first control unit feeds back a switching signal to the adjustment unit and automatically resets the test time based on the set test time and whether a verification pass signal is obtained within the test time.

[0021] like Figure 2 As shown, specifically, the first control unit includes a first operational amplifier U1, a second operational amplifier U2, a first field effect transistor Q1, a third field effect transistor Q3, a second diode D2, a sixth diode D6, a first capacitor C1, a first connector P1, a second connector P2, a third connector P3, a first resistor R1, a second resistor R2, a third resistor R3, a sixth resistor R6, an eighth resistor R8, and a ninth resistor R9;

[0022] The first operational amplifier U1 is connected to the same phase end with one end of the first resistor R1, one end of the second resistor R2, and the anode of the second diode D2; the first operational amplifier U1 is connected to the opposite phase end with one end of the third resistor R3; the first operational amplifier U1 output end is connected to the drain of the first field effect transistor Q1, the drain of the third field effect transistor Q3, and the other end of the third resistor R3; the second operational amplifier U2 is connected to the same phase end with the source of the third field effect transistor Q3, one end of the sixth resistor R6, and one end of the first capacitor C1; the second operational amplifier U2 is connected to the opposite phase end with one end of the eighth resistor R8, the second diode D2 The cathode of D2 is connected, the output end of the second operational amplifier U2 is connected to one end of the ninth resistor R9 and the end of the third connector P3, the gate of the first field effect transistor Q1 is connected to the cathode of the sixth diode D6, the gate of the third field effect transistor Q3 is connected to the end of the first connector P1, the anode of the sixth diode D6 is connected to the end of the second connector P2, the other end of the first resistor R1 is connected to the power supply, the other end of the second resistor R2, the other end of the sixth resistor R6, the other end of the eighth resistor R8, the other end of the ninth resistor R9, the other end of the first capacitor C1, the source of the first field effect transistor Q1 and the ground are connected.

[0023] like Figure 2As shown, specifically, the first control unit also includes a third operational amplifier U3, a fourth operational amplifier U4, a second triode Q2, a first diode D1, a third diode D3, a fourth diode D4, a fifth diode D5, a seventh resistor R7, a tenth resistor R10, an eleventh resistor R11, a twelfth resistor R12, a thirteenth resistor R13, a fourteenth resistor R14, a fifteenth resistor R15, and a sixteenth resistor R16;

[0024] The third operational amplifier U3 is connected at the same phase end to one end of the seventh resistor R7 and one end of the sixteenth resistor R16, the third operational amplifier U3 is connected at the inverting end to one end of the first capacitor C1, the output end of the third operational amplifier U3 is connected to one end of the fourteenth resistor R14 and the anode of the fourth diode D4, the fourth operational amplifier U4 is connected at the same phase end to one end of the eleventh resistor R11, one end of the thirteenth resistor R13, the cathode of the first diode D1, the cathode of the third diode D3, and the collector of the second transistor Q2, the fourth operational amplifier U4 is connected at the inverting end to one end of the tenth resistor R10, one end of the twelfth resistor R12, and the cathode of the fourth diode D4, and the fourth operational amplifier U The output end is connected to the anode of the first diode D1 and the anode of the fifth diode D5, the base of the second triode Q2 is connected to the end of the first connector P1, the emitter of the second triode Q2 is connected to one end of the fifteenth resistor R15, the anode of the third diode D3 is connected to the end of the third connector P3, the cathode of the fifth diode D5 is connected to the cathode of the sixth diode D6, the other end of the seventh resistor R7, the other end of the eleventh resistor R11, the other end of the twelfth resistor R12, and the other end of the fifteenth resistor R15 are connected to the power supply, and the other end of the tenth resistor R10, the other end of the thirteenth resistor R13, the other end of the fourteenth resistor R14, and the other end of the sixteenth resistor R16 are connected to the ground end.

[0025] like Figure 3 As shown, specifically, the control module also includes a second control unit, which includes a fourth transistor Q4, a first conversion switch S1, a second switch S2, a fourth connector P4, a fifth connector P5, a sixth connector P6, a seventeenth resistor R17, an eighteenth resistor R18, and a nineteenth resistor R19;

[0026] The collector of the fourth transistor Q4 is connected to one end of the nineteenth resistor R19, the emitter of the fourth transistor Q4 is connected to one end of the eighteenth resistor R18 and the positive electrode of the first conversion switch S1, the base of the fourth transistor Q4 is connected to one end of the seventeenth resistor R17, the second end of the first conversion switch S1, the positive electrode of the second switch S2, and the end of the sixth connector P6, the first end of the first conversion switch S1 is connected to the end of the fourth connector P4, the common end of the first conversion switch S1 is connected to the end of the fifth connector P5, the other end of the nineteenth resistor R19 is connected to the power supply, and the negative electrode of the first conversion switch S1, the negative electrode of the second switch S2, the other end of the seventeenth resistor R17, the other end of the eighteenth resistor R18 and the ground are connected.

[0027] like Figure 2 As shown, specifically, the first control unit also includes a fourth resistor R4 and a fifth resistor R5;

[0028] One end of the fourth resistor R4 is connected to the gate of the first field effect transistor Q1, one end of the fifth resistor R5 is connected to the gate of the third field effect transistor Q3, and the other ends of the fourth resistor R4 and the fifth resistor R5 are connected to the ground.

[0029] like Figure 2 As shown, specifically, the first capacitor C1 is an adjustable capacitor.

[0030] See also Figure 1 When the vehicle power supply is connected to the aircraft power socket through a cable, the aircraft's external power supply system detects the quality of the external power supply. After the detection and verification are passed, the electronic equipment in the aircraft receives the external power supply signal, and the power supply system inside the aircraft is cut off at the same time. The detection unit detects the cable type and connection status of the output end of the vehicle power supply. When the cable for transmitting AC power is connected to the aircraft, the detection unit feeds back the AC demand signal to the adjustment unit. When the adjustment unit obtains the signal feedback, it adjusts the output voltage of the first output end of the dual-output DC-DC module to make it output the voltage required by the inverter module. The inverter module performs inversion and provides the aircraft with an AC power signal. When the cable for transmitting DC power is connected to the aircraft, the detection unit feeds back the DC demand signal to the adjustment unit. When the adjustment unit obtains the signal feedback, it adjusts the output voltage of the first output end of the dual-output DC-DC module to the initial voltage specification of the DC power supply. The voltage is the voltage amplitude of the minimum specification of the aircraft to the ground DC power supply. The number of adjustable voltage specifications is set on the adjustment module, and the setting order is set from small to large according to the voltage amplitude of each specification.

[0031] See also Figure 2, the first connector P1 on the first control unit synchronously receives the DC demand signal fed back by the detection unit, the signal at the first connector P1 end is fed back to the gate of the third field effect transistor Q3, the fifth resistor R5 is used to discharge the parasitic capacitance of the gate of the third field effect transistor Q3, when the first connector P1 feeds back the signal, the voltage difference between the gate of the third field effect transistor Q3 and the source of the third field effect transistor Q3 is higher than the conduction threshold, the third field effect transistor Q3 is turned on, the power supply signal passes through the first resistor R1 and the second resistor R2 to the ground end, the signal at the second resistor R2 end is fed back to the in-phase end of the first operational amplifier U1, the first operational amplifier U1 and the third resistor R3 form a negative feedback connection so that the first operational amplifier U1 follows the signal at the second resistor R2 end, and the first operational amplifier U1 outputs The output signal is connected to the ground terminal through the drain of the third field effect transistor Q3, the source of the third field effect transistor Q3, and the sixth resistor R6. At the same time, the signal at the end of the sixth resistor R6 is fed back to the first capacitor C1. The potential of the first capacitor C1 rises, and the signal at the end of the first capacitor C1 is fed back to the in-phase end of the second operational amplifier U2. At the same time, the signal at the end of the second resistor R2 is connected to the ground terminal through the second diode D2 and the eighth resistor R8. The end of the eighth resistor R8 obtains the signal at the end of the second resistor R2 after the voltage drop of the second diode D2. The signal at the end of the eighth resistor R8 is fed back to the inverting end of the second operational amplifier U2. When the potential of the first capacitor C1 rises and is higher than the potential of the eighth resistor R8, the second operational amplifier U2 outputs, and the first connector P1 obtains the signal and then sends it to the second operational amplifier U 2 output is the waiting time for the external power control system on the aircraft to detect the input power signal and pass the test. The response matching can be performed by adjusting the capacitance of the first capacitor C1. When the vehicle power passes the test within the waiting time, the second connector P2 obtains a verification pass signal. The signal can be fed back by the cable plug / aircraft power socket, the external power control system of the aircraft, and the operator. The feedback mode can be selected as needed. When the second connector P2 end obtains signal feedback, the signal is fed back to the gate of the first field effect transistor Q1 after passing through the sixth diode D6. The fourth resistor R4 is used to discharge the parasitic capacitance of the gate of the first field effect transistor Q1. The voltage difference between the gate of the first field effect transistor Q1 and the source of the first field effect transistor Q1 is higher than the conduction threshold. The first field effect tube Q1 is turned on, and the signal at the output end of the first operational amplifier U1 is connected to the ground terminal through the drain of the first field effect tube Q1 and the source of the first field effect tube Q1. The potential of the output end of the first operational amplifier U1 is pulled to the ground potential. At the same time, the signal at the end of the first capacitor C1 is connected to the ground terminal through the sixth resistor R6. At this time, the vehicle power supply is the initial voltage specification set by the aircraft feedback. When the second connector P2 end does not obtain the verification pass signal within the waiting time, the second operational amplifier U2 outputs, and the signal at the output end of the second operational amplifier U2 is connected to the ground terminal through the ninth resistor R9. The signal at the end of the ninth resistor R9 is fed back to the adjustment unit through the third connector P3. The signal at the end of the ninth resistor R9 is a switching signal. When the adjustment unit obtains the signal feedback from the third connector P3 end,The regulating unit regulates the output voltage of the first output terminal of the dual-output DC-DC module to the next specification voltage in the setting sequence, so as to automatically switch when the initial voltage specification cannot meet the specification requirements of the aircraft for the ground DC power supply.

[0032] See also Figure 2, when the first connector P1 end does not obtain signal feedback, the power signal passes through the fifteenth resistor R15, the emitter of the second transistor Q2, the base of the second transistor Q2, and the fifth resistor R5 to the ground end, the emitter of the second transistor Q2 and the base of the second transistor Q2 are forward biased, the second transistor Q2 is turned on, the power signal passes through the fifteenth resistor R15, the emitter of the second transistor Q2, the collector of the second transistor Q2, and the thirteenth resistor R13 to the ground end, the signal amplitude of the thirteenth resistor R13 end is pulled high, the power signal passes through the seventh resistor R7 and the sixteenth resistor R16 to the ground end, the signal at the sixteenth resistor R16 end is the offset reference signal, at this time the potential of the first capacitor C1 end is zero potential, and the signal at the first capacitor C1 end is synchronously fed back to the third operation The inverting end of the amplifier U3 is output by the third operational amplifier U3. The output end signal of the third operational amplifier U3 is connected to the ground end through the fourteenth resistor R14. The signal at the end of the fourteenth resistor R14 is connected to the ground end through the fourth diode D4 and the tenth resistor R10, so that the signal at the end of the tenth resistor R10 is increased to the signal amplitude of the output end of the third operational amplifier U3 after the voltage drop of the fourth diode D4. At this time, the fourth operational amplifier U4 outputs, and the output end signal of the fourth operational amplifier U4 is fed back to the gate of the first field effect tube Q1 through the fifth diode D5, so that the first field effect tube Q1 is turned on and the output end potential of the first operational amplifier U1 is pulled down to the ground potential. When the first connector P1 obtains signal feedback, the second transistor Q2 is turned off, the third field effect tube Q3 is turned on, and the first transistor Q4 is turned on. The signal at the thirteenth resistor R13 end is pulled down to the signal amplitude of the power supply signal after the eleventh resistor R11 and the thirteenth resistor R13 divide the voltage, the fourth operational amplifier U4 is turned off, the first field effect tube Q1 is turned off, the potential of the first capacitor C1 rises, when the potential of the first capacitor C1 is higher than the signal at the sixteenth resistor R16 end, the third operational amplifier U3 is turned off, the signal at the tenth resistor R10 end is pulled down to the signal amplitude of the power supply signal after the twelfth resistor R12 and the tenth resistor R10 divide the voltage, the fourth operational amplifier U4 is still in the cut-off state, when the potential of the first capacitor C1 is higher than the signal at the eighth resistor R8 end, the second operational amplifier U2 outputs, the adjustment unit obtains the switching signal through the third connector P3, and the second operational amplifier U2 outputs the signal The signal is transmitted through the third diode D3 and the thirteenth resistor R13 to the ground terminal, so that the voltage signal at the thirteenth resistor R13 terminal is increased to the signal amplitude at the output terminal of the second operational amplifier U2 after the voltage drop of the second diode D2, and the fourth operational amplifier U4 is output, the first field effect tube Q1 is turned on, and the potential of the first capacitor C1 decreases. When the potential of the first capacitor C1 decreases to the signal at the end of the sixteenth resistor R16, the third operational amplifier U3 is output, the fourth operational amplifier U4 is turned off, and the potential of the first capacitor C1 terminal rises again for re-verification, so that after the adjustment unit obtains the switching signal, the first control unit can automatically reset the waiting time and re-verify until the second connector P2 terminal obtains the verification pass signal to meet the aircraft's specifications for the ground DC power supply.Based on the set waiting time and whether the verification signal is obtained during the waiting time, the output voltage of the vehicle power supply is automatically adjusted, and the waiting time is automatically reset after each adjustment until the aircraft meets the DC power supply specification requirements for the ground, so as to reduce the number of cables and DC power supply specification configuration interfaces of the vehicle power supply, reduce the quality requirements for operators, and improve the flexibility of power supply.

[0033] See also Figure 3 When the input end of the vehicle power supply is not connected to the power frequency power signal, the output end of the energy storage module is fed back to the control module, and the fourth connector P4 of the second control unit in the control module is used to receive the signal. The signal at the fourth connector P4 end is fed back to the signal input end of the dual-output DC-DC module via the first end of the first conversion switch S1, the common end of the first conversion switch S1, and the fifth connector P5. When the vehicle power supply is connected to the power frequency power signal, the signal is fed back to the rectifier module, and the rectifier module outputs the signal to the control module after rectification. The sixth connector P6 of the second control unit in the control module is used to receive the signal. The signal at the sixth connector P6 end is connected to the ground end via the seventeenth resistor R17, and the signal at the seventeenth resistor R17 end is connected to the ground end via the base of the fourth transistor Q4, the emitter of the fourth transistor Q4, and the eighteenth resistor R18. The base of the fourth transistor Q4 and the emitter of the fourth transistor Q4 are forward biased, the fourth transistor Q4 is turned on, and the power signal is connected to the nineteenth resistor R18. The resistor R19, the collector of the fourth transistor Q4, the emitter of the fourth transistor Q4, and the eighteenth resistor R18 are connected to the ground end. The signal at the end of the eighteenth resistor R18 is fed back to the positive electrode of the first conversion switch S1, and the path of the first conversion switch S1 is switched. The signal at the end of the sixth connector P6 is fed back to the signal input end of the dual-output DC-DC module via the second end of the first conversion switch S1, the common end of the first conversion switch S1, and the fifth connector P5. The second output end of the dual-output DC-DC module is connected to one end of the second switch S2, and the energy storage module is connected to the other end of the second switch S2. When the sixth connector P6 end obtains signal feedback, the signal at the end of the sixth connector P6 is synchronously fed back to the adjustment unit. The adjustment unit adjusts the voltage of the second output end of the dual-output DC-DC module to the charging voltage of the energy storage module. At the same time, the second switch S2 is closed, and the energy storage module is charged, thereby adjusting the power signal channel of the dual-output DC-DC module based on the input state of the industrial frequency power supply.

[0034] It will be apparent to those skilled in the art that the 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 the spirit or essential features of the invention. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations within the meaning and scope of the equivalent elements of the claims be included in the invention. Any marking in a claim should not be considered as limiting the claim to which it relates.

Claims

1. An on-board power supply control system for airport aircraft power supply, comprising an inverter module, a dual-output DC-DC module, a rectifier module, an energy storage module, and a control module, wherein the control module is connected to the energy storage module, the rectifier module, and the dual-output DC-DC module, and the dual-output DC-DC module is connected to the inverter module, characterized in that: The control module includes a detection unit, an adjustment unit, and a first control unit. The detection unit is used to detect the cable type and connection status of the vehicle power supply and based on this, feed back an AC or DC power demand signal to the adjustment unit. The adjustment unit is used to set the DC power supply specification and feed back an adjustment signal to the dual-output DC-DC module. The first control unit feeds back a switching signal to the adjustment unit and automatically resets the test time based on the set test time and whether a verification pass signal is obtained within the test time. The first control unit includes a first operational amplifier, a second operational amplifier, a first field effect transistor, a third field effect transistor, a second diode, a sixth diode, a first capacitor, a first connector, a second connector, a third connector, a first resistor, a second resistor, a third resistor, a sixth resistor, an eighth resistor, and a ninth resistor; The first operational amplifier non-inverting end is connected to one end of the first resistor, one end of the second resistor, and the anode of the second diode. The first operational amplifier inverting end is connected to one end of the third resistor. The first operational amplifier output end is connected to the drain of the first field effect transistor, the drain of the third field effect transistor, and the other end of the third resistor. The second operational amplifier non-inverting end is connected to the source of the third field effect transistor, one end of the sixth resistor, and one end of the first capacitor. The second operational amplifier inverting end is connected to one end of the eighth resistor and the cathode of the second diode. The second operational amplifier output end is connected to one end of the ninth resistor and the end of the third connector. The gate of the first field effect transistor is connected to the cathode of the sixth diode. The gate of the third field effect tube is connected to the first connector end, the anode of the sixth diode is connected to the second connector end, the other end of the first resistor is connected to the power supply, the other end of the second resistor, the other end of the sixth resistor, the other end of the eighth resistor, the other end of the ninth resistor, the other end of the first capacitor, the source of the first field effect tube and the ground end are connected, the first connector on the first control unit synchronously receives the DC demand signal fed back by the detection unit, when the vehicle-mounted power supply passes the detection within the waiting time, the second connector obtains the verification pass signal, the signal at the ninth resistor end is fed back to the adjustment unit via the third connector, and the signal at the ninth resistor end is a switching signal.

2. The on-board power supply control system for airport aircraft power supply according to claim 1, characterized in that: The first control unit also includes a third operational amplifier, a fourth operational amplifier, a second triode, a first diode, a third diode, a fourth diode, a fifth diode, a seventh resistor, a tenth resistor, an eleventh resistor, a twelfth resistor, a thirteenth resistor, a fourteenth resistor, a fifteenth resistor, and a sixteenth resistor; The third operational amplifier in-phase end is connected to one end of the seventh resistor and one end of the sixteenth resistor, the third operational amplifier inverting end is connected to one end of the first capacitor, the third operational amplifier output end is connected to one end of the fourteenth resistor and the anode of the fourth diode, the fourth operational amplifier in-phase end is connected to one end of the eleventh resistor, one end of the thirteenth resistor, the cathode of the first diode, the cathode of the third diode, and the collector of the second transistor, the fourth operational amplifier inverting end is connected to one end of the tenth resistor, one end of the twelfth resistor, and the cathode of the fourth diode, the fourth operational amplifier output end is connected to the anode of the first diode and the anode of the fifth diode, and the base of the second transistor is connected to the first connector end , the emitter of the second triode is connected to one end of the fifteenth resistor, the anode of the third diode is connected to the third connector end, the cathode of the fifth diode is connected to the cathode of the sixth diode, the other end of the seventh resistor, the other end of the eleventh resistor, the other end of the twelfth resistor, the other end of the fifteenth resistor are connected to the power supply, the other end of the tenth resistor, the other end of the thirteenth resistor, the other end of the fourteenth resistor, the other end of the sixteenth resistor are connected to the ground end, when the first connector end does not obtain signal feedback, the fourth operational amplifier outputs, when the first connector end obtains signal feedback, the fourth operational amplifier is cut off, the second operational amplifier outputs, and the adjustment unit obtains the switching signal through the third connector.

3. The on-board power supply control system for airport aircraft power supply according to claim 1, characterized in that: The control module further includes a second control unit, which includes a fourth transistor, a first conversion switch, a second switch, a fourth connector, a fifth connector, a sixth connector, a seventeenth resistor, an eighteenth resistor, and a nineteenth resistor; The collector of the fourth triode is connected to one end of the nineteenth resistor, the emitter of the fourth triode is connected to one end of the eighteenth resistor and the positive electrode of the first conversion switch, the base of the fourth triode is connected to one end of the seventeenth resistor, the second end of the first conversion switch, the positive electrode of the second switch, and the sixth connector end, the first end of the first conversion switch is connected to the fourth connector end, the common end of the first conversion switch is connected to the fifth connector end, the other end of the nineteenth resistor is connected to the power supply, the negative electrode of the first conversion switch, the negative electrode of the second switch, the other end of the seventeenth resistor, the other end of the eighteenth resistor and the ground end are connected, the output end of the energy storage module is fed back to the control module, the fourth connector of the second control unit in the control module is used to receive the signal, and the signal at the fourth connector end is fed back to the signal input end of the dual-output DC-DC module via the first end of the first conversion switch, the common end of the first conversion switch, and the fifth connector.

4. The on-board power supply control system for airport aircraft power supply according to claim 1, characterized in that: The first control unit also includes a fourth resistor and a fifth resistor; One end of the fourth resistor is connected to the gate of the first field effect transistor, one end of the fifth resistor is connected to the gate of the third field effect transistor, and the other end of the fourth resistor and the other end of the fifth resistor are connected to the ground.

5. The on-board power supply control system for airport aircraft power supply according to claim 1, characterized in that: The first capacitor is an adjustable capacitor.

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