Arc ignition circuit and ignition control strategy of micro-nano satellite solid-liquid mixed thruster

Abstract

The invention discloses a micro-nano satellite solid-liquid mixed thruster arc ignition circuit and an ignition control strategy. The arc ignition circuit comprises a control module, an ignition module, a signal acquisition module, an ignition switch circuit, a secondary power supply and a bus. The ignition control strategy comprises a three-section type ignition protection strategy and two ignition control strategies. The state of the system is monitored and managed in real time, so that stray current between two ignition charge electrodes and in a front-end circuit can be effectively eliminated, and controllable ignition is realized. A good solution is provided for the design of a high-reliability and high-safety solid-liquid mixed arc ignition system in a complex space environment.

Description

Technical Field

[0001] This invention belongs to the field of micro-nano satellite technology, specifically relating to an arc ignition circuit and ignition control strategy for a solid-liquid hybrid thruster of a micro-nano satellite. Background Technology

[0002] Hybrid thrusters possess high safety and exhibit strong competitiveness and promising application prospects in areas such as rapid satellite maneuvering, close-range observation, space interception, space avoidance, and on-orbit capture. However, the ignition system remains one of the most sensitive control components. Improving its safety and reliability is crucial in the harsh electromagnetic environment of space, including high-energy particle radiation, solar storms, and radio frequency interference. To enhance the safety and reliability of the ignition charge, the ignition circuit must effectively prevent accidental ignition of the ignition charge under environmental influences and interference when not in operation; and it must effectively control the ignition power and current when in operation.

[0003] Currently, most ignition circuits use only one relay or MOSFET to connect the bus to the ignition charge. To enable multiple-start functionality in a solid-liquid hybrid thruster, the ignition system needs to be able to ignite the charge multiple times. However, after the initial ignition, a voltage difference may remain across the ignition charge, posing a risk of accidental ignition.

[0004] Currently, the ignition systems of hybrid solid-liquid thrusters typically rely on bus power supplied by the main satellite or payload, making them primary power sources that often exhibit significant voltage ripple and inrush current. Furthermore, unlike traditional propellants, the propellant in hybrid solid-liquid thrusters contains little or no oxidizer, and its combustion is diffusion combustion. This results in a very low recoil rate on the propellant surface, leading to a long ignition delay time, requiring the igniter to provide power for an extended period. Therefore, highly reliable circuit design is particularly crucial for the ignition systems of hybrid solid-liquid thrusters. Summary of the Invention

[0005] This invention proposes an arc ignition circuit and ignition control strategy for a micro / nano satellite solid-liquid hybrid thruster. It can provide short-circuit protection for the ignition charge under normal conditions to ensure that there is no risk of accidental ignition, and can also implement effective and reliable ignition control for the ignition charge during operation.

[0006] The technical solution for achieving this invention is as follows: an arc ignition circuit for a micro / nano satellite solid-liquid hybrid thruster, comprising a control module, an ignition module, a signal acquisition module, an ignition switch circuit, a secondary power supply, and a busbar. The control module is connected to the secondary power supply, the signal acquisition module, the ignition module, the ignition switch module, and the spacecraft. The spacecraft is the main satellite or payload. The ignition switch circuit is connected to the ignition module and the busbar. The signal acquisition module is connected to the ignition module and the secondary power supply. The ignition module is then externally connected to the ignition propellant. The busbar is connected to the secondary power supply and the spacecraft. The aircraft provides 13V~16V power to the bus, which in turn powers the secondary power supply and ignition switch circuit. The secondary power supply converts the 13V~16V to 3.3V and 5V. The 3.3V power supply is provided to the control module, and the 5V power supply is provided to the signal acquisition module. The aircraft communicates with the control module via RS422 or CAN. The control module executes the ignition strategy to control the ignition module and the ignition switch module. The signal acquisition module collects the analog signals from the ignition module and feeds them back to the control module to form control feedback. Under ignition conditions, the aircraft outputs 150W@50V3A of energy to the ignition charge.

[0007] An ignition control strategy for an arc ignition circuit of a micro / nano satellite solid-liquid hybrid thruster, comprising the following steps:

[0008] Step 1: After powering on, initialize the circuit. The aircraft communicates with the ignition module through the control module to transmit ignition commands.

[0009] Step 2: Determine whether the ignition module has received an ignition command. If no ignition command is received, proceed to Step 3. If an ignition command is received, proceed to Step 4.

[0010] Step 3: When no ignition command is received, the control module is in ignition protection mode and executes a three-stage ignition protection strategy.

[0011] Step 4: When the ignition command is received, the control module is in ignition mode and has two ignition control strategies.

[0012] Compared with the prior art, the significant advantages of this invention are:

[0013] (1) Since most igniters currently use non-common ground mounting for their propellant electrodes, stray currents inevitably accumulate at both ends of the electrodes after long-term storage or multiple ignitions, posing a certain safety hazard to the ignition charge. This invention employs multiple field-effect transistor circuits at the front end of the positive electrode of the ignition charge, which can effectively eliminate stray currents between the two electrodes of the ignition charge and in the front-end circuit, effectively reducing the possibility of false triggering of the ignition charge.

[0014] (2) Most ignition circuits primarily employ a series connection of multi-stage switching circuits to ensure system safety, but neglect the possibility of switching circuit failure. Solid-liquid hybrid thrusters are rarely used in space propulsion missions, and their ignition circuits are rarely designed to handle single-point failures in complex space environments. To improve system reliability, this invention employs two parallel Buck-Boost circuits and two parallel MOSFET switching circuits, ensuring normal ignition operation even in the event of a single-point failure in complex space environments.

[0015] (3) Most current ignition circuits do not have adjustable voltage and current functions, and cannot provide a good solution for situations such as unignition or incomplete combustion of ignition charges in complex space environments. This invention has programmable ignition, which can realize adjustable voltage, current and constant power output. The ignition command is issued by the aircraft, and this problem can be solved by increasing the ignition voltage and current, extending the ignition time and extending the contact time between the oxidizer and the ignition charge. Attached Figure Description

[0016] Figure 1 This is a schematic block diagram of the present invention.

[0017] Figure 2 This is a schematic diagram of the ignition switch circuit of the present invention.

[0018] Figure 3 This is a schematic diagram of the ignition module circuit of the present invention.

[0019] Figure 4 This is a flowchart of the ignition control strategy of the present invention. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0021] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0022] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly and specifically defined.

[0023] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixing," etc., should be interpreted broadly. For example, "fixing" can mean a fixed connection, a detachable connection, or an integral part; "connection" can mean a mechanical connection or an electrical connection. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0024] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are feasible to those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

[0025] The following section will further introduce the specific implementation method, as well as the technical difficulties and inventive points of this invention, using this design example as an example.

[0026] Combination Figure 1 This invention provides an arc ignition circuit for a solid-liquid hybrid thruster for micro / nano satellites, comprising a control module, an ignition module, a signal acquisition module, an ignition switch circuit, a secondary power supply, and a busbar. The control module is connected to the secondary power supply, the signal acquisition module, the ignition module, the ignition switch module, and the spacecraft, with the spacecraft serving as the main satellite or payload. The ignition switch circuit is connected to the ignition module and the busbar, the signal acquisition module is connected to the ignition module and the secondary power supply, the ignition module is externally connected to the ignition propellant, and the busbar is connected to the secondary power supply and the spacecraft. The aircraft provides 13V to 16V power to the busbar, which supplies power to the secondary power supply and ignition switch circuit. The secondary power supply converts the 13V to 16V to 3.3V and 5V. The 3.3V power supply is provided to the control module, and the 5V power supply is provided to the signal acquisition module. The aircraft communicates with the control module via RS422 or CAN. The control module executes the ignition strategy to control the ignition module and the ignition switch module. The signal acquisition module collects the analog signals from the ignition module and feeds them back to the control module to form control feedback. Under ignition conditions, the aircraft outputs 150W@50V3A of energy to the ignition charge.

[0027] The aircraft needs to have the power distribution capability to provide 16V / 10A (transient) power. One busbar provides 3.3V and 5V power to the circuit through a secondary power supply transformer, and the other busbar connects to the ignition switch circuit to power the ignition module.

[0028] The aircraft communicates with the control module via RS422 or CAN to transmit ignition commands. The control module receives signals from the signal acquisition module and controls the ignition module to ignite, ensuring the stable operation of the ignition module.

[0029] Combination Figure 2 The ignition switch circuit consists of a first-stage switch circuit and a second-stage switch circuit. The first-stage switch circuit includes resistors R1, R2, R3, R4, R5, and R6; transistors Q1 and Q2; diodes D1, D2, D3, and D4; a magnetic latching relay J1; the bus power supply port BUSOUT; the first enable port EN1; and the second enable port EN2. The second-stage switch circuit includes resistors R7, R8, R9, R10, and R11; MOSFETs Q3 and Q4; and the ignition power supply port V. ignition The third enable port is EN3.

[0030] The first enable port EN1 is connected to one end of the first resistor R1. The other end of the first resistor R1 is connected to the base of the first transistor Q1 and one end of the second resistor R2. The other end of the second resistor R2 is connected to ground. The bus power supply port BUSOUT is connected to one end of the fifth resistor R5. The other end of the fifth resistor R5 is connected to the collector of the first transistor Q1. The emitter of the first transistor Q1 is connected to one end of the coil of the first magnetic latching relay J1 and the cathode of the first diode D1. The second enable port EN2 is connected to one end of the fourth resistor R4. The other end of the fourth resistor R4 is connected to the base of the second transistor Q2 and one end of the third resistor R3. The other end of the third resistor R3 is connected to ground. The bus power supply port BUSOUT is connected to one end of the sixth resistor R6. The other end of the sixth resistor R6 is connected to the collector of the second transistor Q2. The emitter of the second transistor Q2 is connected to the other end of the coil of the first magnetic latching relay J1 and the cathode of the fourth diode D4. The anode of the first diode D1 is connected to the cathode of the second diode D2. The positive terminal of the second diode D2 is connected to the other end of the two coils of the first magnetic latching relay J1, and the third diode D3 is connected to ground. The positive terminal of the fourth diode D4 is connected to the negative terminal of the third diode D3. The bus power supply port BUSOUT is connected to the power supply pin of the first magnetic latching relay J1, the ground pin of the first magnetic latching relay J1 is connected to ground, the switch pin of the first magnetic latching relay J1 is connected to the source of the third field-effect transistor Q3, and the source of the fourth field-effect transistor Q4 is connected to one end of the eighth resistor R8. The drain of the third field-effect transistor Q3 is connected to the drain of the fourth field-effect transistor Q4 and the ignition power supply port V. ignition Connections: The other end of the eighth resistor R8 is connected to one end of the seventh resistor R7 and one end of the ninth resistor R9. The other end of the seventh resistor R7 is connected to the gate of the third field-effect transistor Q3 and the gate of the fourth field-effect transistor Q4. The other end of the ninth resistor R9 is connected to the collector of the fifth transistor Q5. The third enable port EN3 is connected to one end of the tenth resistor R10. The other end of the tenth resistor R10 is connected to one end of the eleventh resistor R11 and the base of the fifth transistor Q5. The other end of the eleventh resistor R11 is connected to the emitter of the fifth field-effect transistor Q5 and ground.

[0031] The current flow is as follows: When the control module outputs a 0V voltage signal to EN1, EN2, and EN3, transistors Q1, Q2, and Q5 are in the off state, and the current is cut off at the collectors of transistors Q1 and Q2. When the control module outputs a 3.3V high level to EN1 and EN3, transistors Q1 and Q5 are turned on. The current flows through the fifth resistor R5 and the first transistor Q1 to supply power to the left coil of the first magnetic latching relay J1. The coil causes the power supply pin to be energized, and the current flows from the power supply pin to the source of the third and fourth field-effect transistors Q3 and Q4, then to the eighth resistor R8, and finally through the ninth resistor R9 to ground. Since the gate potential of the field-effect transistor is lower than the source potential at this time, the field-effect transistor is turned on, and the current flows to the ignition power supply port.

[0032] Combination Figure 3 The ignition module consists of an input filtering circuit, a voltage and current acquisition circuit, and a Buck-Boost topology circuit. The input filtering circuit includes a first capacitor C1 and a second capacitor C2. The voltage and current acquisition circuit includes a 3.3V power supply port, a first chip U1, a second chip U2, a third chip U3, a twelfth resistor R12, a thirteenth resistor R13, a fourteenth resistor R14, a fifteenth resistor R15, a sixteenth resistor R16, a seventeenth resistor R17, an eighteenth resistor R18, a nineteenth resistor R19, a twenty-second resistor R22, a first analog port (dect1), a second analog port (dect2), a third analog port (dect3), a fourth analog port (dect4), and a fifth analog port (dect5). The analog input port is dec5, the sixth analog input port is dec6, and the Buck-Boost topology circuit includes the sixth field-effect transistor Q6, the seventh field-effect transistor Q7, the eighth field-effect transistor Q8, the ninth field-effect transistor Q9, the tenth field-effect transistor Q10, the eleventh field-effect transistor Q11, the twelfth field-effect transistor Q12, the thirteenth field-effect transistor Q13, the first inductor L1, the second inductor L2, the third capacitor C3, the fourth capacitor C4, the first signal port PWM1, the second signal port PWM2, the third signal port PWM3, the fourth signal port PWM4, the fifth signal port PWM5, the sixth signal port PWM6, the seventh signal port PWM7, the eighth signal port PWM8, and the output port V. out .

[0033] Among them, the ignition power supply port V of the second-stage switching circuit ignitionThe capacitors C1, C2, Q6, and Q10 are connected to their respective drains. The other end of capacitor C1 is connected to ground, the other end of capacitor C2 is connected to ground. The source of Q6 is connected to pins 1 and 2 of chip U1, and its gate is connected to the first signal port PWM1. Pins 3 and 4 of chip U1 are connected to one end of resistor R12, and the other end of resistor R12 is connected to one end of resistor R13 and the second analog port dec2. Pin 5 of chip U1 is connected to analog ground, the other end of resistor R13 is connected to analog ground. Pin 7 of chip U1 is connected to one end of resistor R16, and resistor R16 is connected to the first analog port dec1. Pin 8 of chip U1 is connected to the 3.3V power supply port. The source of Q10 is connected to pins 1 and 2 of chip U3, and its gate is connected to the fifth signal port PWM5. Pins 3 and 4 of the third chip U3 are connected to one end of the eighteenth resistor R18. The other end of the eighteenth resistor R18 is connected to one end of the nineteenth resistor R19 and the sixth analog port dec6. Pin 5 of the third chip U3 is connected to the other end of the nineteenth resistor R19 and analog ground. Pin 7 of the third chip U3 is connected to one end of the twenty-second resistor R22. The twenty-second resistor R22 is connected to the fifth analog port dec5. Pin 8 of the third chip U3 is connected to the 3.3V power supply port. One end of the twelfth resistor R12 is connected to one end of the first inductor L1 and the drain of the eighth field-effect transistor Q8. One end of the eighteenth resistor R18 is connected to one end of the second inductor L2 and the drain of the twelfth field-effect transistor Q12. The gate of the eighth field-effect transistor Q8 is connected to the third signal port PWM3, and the source of the eighth field-effect transistor Q8 is connected to ground. The gate of the twelfth field-effect transistor Q12 is connected to the seventh signal port PWM7, and the source of the twelfth field-effect transistor Q12 is connected to ground. The other end of the first inductor L1 is connected to the source of the seventh field-effect transistor Q7 and the drain of the ninth field-effect transistor Q9. The other end of the second inductor L2 is connected to the source of the eleventh field-effect transistor Q11 and the drain of the thirteenth field-effect transistor Q13. The gate of the ninth field-effect transistor Q9 is connected to the fourth signal port PWM4, and the source of the eighth field-effect transistor Q8 is connected to ground. The gate of the thirteenth field-effect transistor Q13 is connected to the eighth signal port PWM8, and the source of the thirteenth field-effect transistor Q13 is connected to ground. The gate of the seventh field-effect transistor Q7 is connected to the second signal port PWM2, and the gate of the eleventh field-effect transistor Q11 is connected to the sixth signal port PWM6. The drain of the seventh field-effect transistor Q7 is connected to the eleventh field-effect transistor Q11 and pins 1 and 2 of the second chip U2. Pins 3 and 4 of the second chip U2 are connected to one end of the fourteenth resistor R14, one end of the third capacitor C3, one end of the fourth capacitor C4, and the output port V. outConnections: The other end of the fourteenth resistor R14 is connected to one end of the fifteenth resistor R15 and the fourth analog port dec4. Pin 5 of the second chip U2 is connected to the other end of the fifteenth resistor R15 and analog ground. Pin 7 of the second chip U2 is connected to one end of the seventeenth resistor R17. The other end of the seventeenth resistor R17 is connected to the third analog port dec3. Pin 8 of the second chip U2 is connected to the 3.3V power supply port. The other end of the third capacitor C3 is connected to the other end of the fourth capacitor C4 and ground. The twenty-fourth resistor R24 ​​and the twenty-fifth resistor R25 are for the ignition charge.

[0034] The current flow is as follows: Due to Figure 3 The circuit is a dual-backup circuit, so only the current flow of the main circuit will be explained. The current flow of the backup circuit is the same as that of the main circuit. When the required output voltage V... out Less than the input voltage V ignition When the circuit is in Buck mode, the duty cycle of the PWM4 control signal input to the gate of the ninth field-effect transistor Q9 is 0, so the ninth field-effect transistor Q9 is continuously off. The duty cycle of the PWM2 control signal input to the gate of the seventh field-effect transistor Q7 is 1, so the seventh field-effect transistor Q7 is continuously on. The PWM1 and PWM3 control signals input to the gates of field-effect transistors Q6 and Q8 are complementary, so the switching of field-effect transistors Q6 and Q8 is complementary. When the sixth field-effect transistor Q6 is on and the eighth field-effect transistor Q8 is off, the current flows from the ignition power supply port through the sixth field-effect transistor Q6, through the first chip U1, to the first inductor L1 to charge it, and then through the seventh field-effect transistor Q7 and the second chip U2 to the ignition terminal V. out At this point, when the sixth field-effect transistor Q6 is in the off state and Q8 is in the on state, due to the presence of the first inductor L1, the current direction will remain unchanged, that is, it flows to the ignition terminal V after passing through the seventh field-effect transistor Q7 and the second chip U2. out Place.

[0035] When the required output voltage V out Equal to input voltage V ignition When the circuit is in Buck-Boost mode, the PWM1 and PWM3 control signals input to the gates of MOSFETs Q6 and Q8 are complementary and turned on, as are the PWM2 and PWM4 control signals input to the gates of MOSFETs Q7 and Q9. That is, when MOSFETs Q6 and Q9 are on, MOSFETs Q8 and Q7 are off. At this time, current flows from the ignition control port through the sixth MOSFET Q6, the first chip U1, the first inductor L1, and the ninth MOSFET Q9 before flowing to ground. When MOSFETs Q6 and Q9 are off, MOSFETs Q8 and Q7 are on. Due to the presence of the first inductor L1, the current direction remains unchanged, flowing through the seventh MOSFET Q7 and the second chip U2 to the ignition terminal V.out Place.

[0036] When the required output voltage V out Greater than the input voltage V ignition When the circuit is in Boost mode, the duty cycle of the PWM1 control signal input to the gate of the sixth field-effect transistor Q6 is 1, so the sixth field-effect transistor Q6 is continuously on. The duty cycle of the PWM3 control signal input to the gate of the eighth field-effect transistor Q8 is 0, so the eighth field-effect transistor Q8 is continuously off. The PWM2 and PWM4 control signals input to the gates of field-effect transistors Q7 and Q9 are complementary, so the switching of field-effect transistors Q7 and Q9 is complementary. When the seventh field-effect transistor Q7 is on and the ninth field-effect transistor Q9 is off, the current flows from the ignition port through the sixth field-effect transistor Q6 and the first chip U1 to the first inductor L1 and charges it, then flows through the seventh field-effect transistor Q7 and the second chip U2 to the ignition terminal V. out When the seventh field-effect transistor Q7 is in the off state and the ninth field-effect transistor Q9 is in the on state, the current flows through the ignition power supply port, through the sixth field-effect transistor Q6, the first chip U1, the first inductor L1, and the ninth field-effect transistor Q9, and then flows into the ground. During this process, the inductor is continuously charged to achieve the required output voltage.

[0037] Combination Figure 4 An ignition control strategy for an arc ignition circuit of a micro / nano satellite solid-liquid hybrid thruster is as follows:

[0038] Step 1: After power-on, initialize the circuit. The aircraft communicates with the ignition module through the control module to transmit ignition commands.

[0039] Step 2: Determine whether the ignition module has received an ignition command. If no ignition command is received, proceed to Step 3. If an ignition command is received, proceed to Step 4.

[0040] Step 3: When no ignition command is received, the control module is in ignition protection mode and executes a three-stage ignition protection strategy, as follows:

[0041] Step 3-1, First stage protection: The control module outputs 0V to the third enable port EN3, and the base potential of the fifth transistor Q5 is 0V, which does not meet the NPN transistor conduction condition. Therefore, the gate potentials of the third MOSFET Q3 and the fourth MOSFET Q4 are equal to the potential of the bus power supply port BUSOUT, which does not meet the PMOS conduction condition. The second stage switching circuit is disconnected, and the ignition power supply port V... ignition The voltage is close to zero.

[0042] Step 3-2, Second Stage Protection: The control module sends a 10ms 3.3V high-level pulse to the second enable port EN2, and the second diode Q2 has a 10ms conduction time. During this time, the bus power supply port BUSOUT supplies power to the coil of the first magnetic latching relay J1 through the sixth resistor R6, ensuring that its switch is engaged with the ground pin. Here, the sixth resistor R6 is used for voltage division of the coil, providing a suitable operating voltage for the coil; the third diode D3 and the fourth diode D4 are freewheeling diodes, used to suppress back electromotive force and provide freewheeling current to the coil after the coil's operation, dissipating its stored energy.

[0043] Step 3-3, Third-stage protection: The control module sets the duty cycle of the third signal port PWM3, the fourth signal port PWM4, the seventh signal port PWM7, and the eighth signal port PWM8 to 1 (i.e., turning on the eighth field-effect transistor Q8, the ninth field-effect transistor Q9, the twelfth field-effect transistor Q12, and the thirteenth field-effect transistor Q13), releasing the residual energy on the first inductor L1 and the second inductor L2. The control module sets the duty cycle of the third signal port PWM3 and the seventh signal port PWM7 to 0 (i.e., turning off the eighth field-effect transistor Q8 and the twelfth field-effect transistor Q12); and sets the duty cycle of the second signal port PWM2 and the sixth signal port PWM6 to 1 (i.e., turning on the seventh field-effect transistor Q7 and the eleventh field-effect transistor Q11). At this time, the ignition charge electrodes are shorted to ground.

[0044] After completing the three-stage ignition protection strategy, return to step 2 and re-determine whether an ignition command has been received.

[0045] Step 4: Upon receiving the ignition command, the control module is in ignition mode and has two ignition control strategies, as follows:

[0046] Step 4-1: After the aircraft sends the ignition command and enters the ignition state, the control module first sets the first signal port PWM1, the second signal port PWM2, the third signal port PWM3, the fourth signal port PWM4, the fifth signal port PWM5, the sixth signal port PWM6, the seventh signal port PWM7, and the eighth signal port PWM8 (i.e., turning off the sixth field-effect transistor Q6, the seventh field-effect transistor Q7, the eighth field-effect transistor Q8, the ninth field-effect transistor Q9, the tenth field-effect transistor Q10, the eleventh field-effect transistor Q11, the twelfth field-effect transistor Q12, and the thirteenth field-effect transistor Q13), removes the common ground state of the ignition charge electrodes, and proceeds to step 4-2.

[0047] Step 4-2: Select the ignition control strategy according to the ignition command. The ignition control strategy includes constant power ignition and constant voltage / constant current ignition. If constant power ignition is selected, proceed to step 4-3. If constant voltage / constant current ignition is selected, proceed to step 4-6.

[0048] In step 4-3, when constant power ignition is selected, the control module adopts an inductor current single-loop PI control strategy. The control module sends a 10ms 3.3V high-level pulse to the first enable port EN1, and the first diode Q1 has a 10ms conduction time. During this time, the bus power supply port BUSOUT supplies power to the coil of the first magnetic latching relay J1 through the fifth resistor R5, ensuring that its switch is engaged with the power supply pin. At this time, the voltage of the bus power supply port BUSOUT is transmitted to the source of the third field-effect transistor Q3 and the source of the fourth field-effect transistor Q4, and the first-stage switching circuit is closed. Here, the fifth resistor R5 is used for voltage division of the coil to provide a suitable operating voltage for the coil; the first diode D1 and the second diode D2 are freewheeling diodes used to suppress back electromotive force and provide freewheeling current to the coil after the coil finishes working, dissipating its stored energy. The control module outputs 3.3V to the third enable port EN3, and the base potential of the fifth transistor Q5 is about 0.7V, which meets the conduction conditions of an NPN transistor. Therefore, after voltage division by resistors R8 and R9, the potentials of the gates of the third MOSFET Q3 and the fourth MOSFET Q4 are lower than the potentials of the sources of the third MOSFET Q3 and the fourth MOSFET Q4, thus satisfying the PMOS turn-on condition. The second-stage switching circuit closes, and the ignition power supply port V... ignition When the voltage is close to the bus power supply port BUSOUT, proceed to step 4-4.

[0049] Step 4-4: The control module processes the acquired analog signals and determines whether the input voltage and current meet the requirements. If not, an emergency stop protection is initiated; otherwise, the control strategy is executed. Constant power ignition employs a single-loop PI control strategy for inductor current. The control module only performs PI algorithm control on the acquired inductor current value, with a control frequency of 200kHz. Adjustments are made based on real-time acquired values ​​to ensure a constant power output of 150W. The module then checks whether the output voltage and current exceed the limits. If so, an emergency stop protection is initiated; otherwise, ignition is executed, and the process proceeds to step 4-5.

[0050] Steps 4-5: Disconnect the second-stage switching circuit and the first-stage switching circuit in sequence. Ignition ends. Return to step 2 and re-determine whether the ignition command has been received.

[0051] In steps 4-6, when constant voltage and constant current ignition is selected, the control module adopts a dual-loop control strategy of inductor current inner loop and voltage and current outer loop. The control module sends a 10ms 3.3V high-level pulse to the first enable port EN1, and the first diode Q1 has a 10ms conduction time. During this time, the bus power supply port BUSOUT supplies power to the coil of the first magnetic latching relay J1 through the fifth resistor R5, ensuring that its switch is engaged with the power supply pin. At this time, the voltage of the bus power supply port BUSOUT is transmitted to the source of the third field-effect transistor Q3 and the source of the fourth field-effect transistor Q4, and the first-stage switching circuit is closed. The control module outputs 3.3V to the third enable port EN3, and the base potential of the fifth transistor Q5 is about 0.7V, which meets the conduction condition of the NPN transistor. Therefore, after voltage division by the eighth resistor R8 and the ninth resistor R9, the potential of the gate of the third field-effect transistor Q3 and the gate of the fourth field-effect transistor Q4 is less than the potential of the source of the third field-effect transistor Q3 and the source of the fourth field-effect transistor Q4, and the PMOS conduction condition is met. The second-stage switching circuit is closed, and the ignition power supply port V... ignition When the voltage is close to the bus power supply port BUSOUT, proceed to step 4-7.

[0052] Steps 4-7: The control module processes the acquired analog signals and determines whether the input voltage and current meet the requirements. If not, an emergency stop protection is initiated; otherwise, the control strategy is executed. Constant voltage and constant current ignition employs an inner-loop inductor current control strategy and an outer-loop PI control strategy for output voltage and current. The control module uses the outer-loop PI algorithm to control the acquired output voltage and current values. The outer-loop PI controller uses a dual-loop competition method to obtain the target inductor current value, which is then subtracted from the acquired inductor current value to obtain the error value, which is then entered into the inner-loop PI algorithm control. The control frequency is 200kHz and is adjusted based on real-time acquired values ​​to ensure a maximum output of 150W@50V3A with constant voltage followed by constant current distribution capability. The module then checks whether the output voltage and current exceed the limits. If they do, an emergency stop protection is initiated; otherwise, ignition is executed, and the process proceeds to step 4-8.

[0053] Steps 4-8: Disconnect the second-stage switching circuit and the first-stage switching circuit in sequence. Ignition ends. Return to step 2 and re-determine whether the ignition command has been received.

[0054] Although one embodiment of the invention has been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to that embodiment. Therefore, the appended claims are intended to be interpreted as including the described embodiment as well as all changes and modifications falling within the scope of the invention.

[0055] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. An arc ignition circuit for a micro / nano satellite solid-liquid hybrid thruster, characterized in that: The system includes a control module, an ignition module, a signal acquisition module, an ignition switch circuit, a secondary power supply, and a bus. The control module is connected to the secondary power supply, signal acquisition module, ignition module, ignition switch module, and spacecraft. The spacecraft is the main satellite or payload. The ignition switch circuit is connected to the ignition module and the bus. The signal acquisition module is connected to the ignition module and the secondary power supply. The ignition module is then connected to the ignition charge. The bus is connected to the secondary power supply and the spacecraft. The spacecraft provides 13V-16V power to the bus, which in turn powers the secondary power supply and the ignition switch circuit. The secondary power supply converts the 13V-16V to 3.3V and 5V. The 3.3V power supply is provided to the control module, and the 5V power supply is provided to the signal acquisition module. The spacecraft communicates with the control module via RS422 or CAN. The control module executes the ignition strategy to control the ignition module and the ignition switch module. The signal acquisition module collects analog signals from the ignition module and feeds them back to the control module, forming control feedback. Under ignition conditions, the spacecraft outputs 150W@50V3A of energy to the ignition charge.

2. The arc ignition circuit for a micro / nano satellite solid-liquid hybrid thruster according to claim 1, characterized in that: The ignition switch circuit consists of a first-stage switching circuit and a second-stage switching circuit. The first-stage switching circuit includes resistors R1, R2, R3, R4, R5, and R6; transistors Q1 and Q2; diodes D1, D2, D3, and D4; a magnetic latching relay J1; the bus power supply port BUSOUT; and the first enable port EN1 and EN2. The second-stage switching circuit includes resistors R7, R8, R9, R10, and R11; MOSFETs Q3 and Q4; and the ignition power supply port V. ignition Third enable port EN3; Specifically, the first enable port EN1 is connected to one end of the first resistor R1, and the other end of the first resistor R1 is connected to the base of the first transistor Q1 and one end of the second resistor R2, with the other end of the second resistor R2 connected to ground; the bus power supply port BUSOUT is connected to one end of the fifth resistor R5, and the other end of the fifth resistor R5 is connected to the collector of the first transistor Q1, with the emitter of the first transistor Q1 connected to one end of the coil of the first magnetic latching relay J1 and the cathode of the first diode D1; the second enable port EN2 is connected to one end of the fourth resistor R4, and the other end of the fourth resistor R4 is connected to the base of the second transistor Q2 and one end of the third resistor R3, with the other end of the third resistor R3 connected to ground; the bus power supply port BUSOUT is connected to one end of the sixth resistor R6, and the other end of the sixth resistor R6 is connected to the base of the second transistor Q2 and one end of the second transistor D1. The collector of transistor Q2 is connected; the emitter of transistor Q2 is connected to one end of the other coil of the first magnetic latching relay J1 and the negative terminal of the fourth diode D4; the positive terminal of the first diode D1 is connected to the negative terminal of the second diode D2; the positive terminal of the second diode D2 is connected to the other end of both coils of the first magnetic latching relay J1, the third diode D3, and ground; the positive terminal of the fourth diode D4 is connected to the negative terminal of the third diode D3; the bus power supply port BUSOUT is connected to the power supply pin of the first magnetic latching relay J1; the ground pin of the first magnetic latching relay J1 is connected to ground; the switch pin of the first magnetic latching relay J1 is connected to the source of the third field-effect transistor Q3; the source of the fourth field-effect transistor Q4 is connected to one end of the eighth resistor R8; the drain of the third field-effect transistor Q3 is connected to the drain of the fourth field-effect transistor Q4 and the ignition power supply port V. ignition Connections: The other end of the eighth resistor R8 is connected to one end of the seventh resistor R7 and one end of the ninth resistor R9; the other end of the seventh resistor R7 is connected to the gate of the third field-effect transistor Q3 and the gate of the fourth field-effect transistor Q4; the other end of the ninth resistor R9 is connected to the collector of the fifth transistor Q5; the third enable port EN3 is connected to one end of the tenth resistor R10; the other end of the tenth resistor R10 is connected to one end of the eleventh resistor R11 and the base of the fifth transistor Q5; the other end of the eleventh resistor R11 is connected to the emitter of the fifth field-effect transistor Q5 and ground; When the control module outputs a 0V voltage signal to EN1, EN2, and EN3, transistors Q1, Q2, and Q5 are in the off state, and the current is cut off at the collectors of transistors Q1 and Q2. When the control module outputs a 3.3V high level to EN1 and EN3, transistors Q1 and Q5 are turned on, and the current flows through the fifth resistor R5 and the first transistor Q1 to supply power to the left coil of the first magnetic latching relay J1. The coil causes the power supply pin to be energized, and the current flows from the power supply pin to the source of the third and fourth field-effect transistors Q3 and Q4, then to the eighth resistor R8, and then through the ninth resistor R9 to ground. Since the gate potential of the field-effect transistor is lower than the source potential at this time, the field-effect transistor is turned on, and the current flows to the ignition power supply port.

3. The arc ignition circuit for a micro / nano satellite solid-liquid hybrid thruster according to claim 1, characterized in that: The ignition module consists of an input filtering circuit, a voltage and current acquisition circuit, and a Buck-Boost topology circuit. The input filtering circuit includes a first capacitor C1 and a second capacitor C2. The voltage and current acquisition circuit includes a 3.3V power supply port, a first chip U1, a second chip U2, a third chip U3, a twelfth resistor R12, a thirteenth resistor R13, a fourteenth resistor R14, a fifteenth resistor R15, a sixteenth resistor R16, a seventeenth resistor R17, an eighteenth resistor R18, a nineteenth resistor R19, a twenty-second resistor R22, a first analog port (dect1), a second analog port (dect2), a third analog port (dect3), a fourth analog port (dect4), and a fifth analog port (dect5). The analog input port is dec5, the sixth analog input port is dec6, and the Buck-Boost topology circuit includes the sixth field-effect transistor Q6, the seventh field-effect transistor Q7, the eighth field-effect transistor Q8, the ninth field-effect transistor Q9, the tenth field-effect transistor Q10, the eleventh field-effect transistor Q11, the twelfth field-effect transistor Q12, the thirteenth field-effect transistor Q13, the first inductor L1, the second inductor L2, the third capacitor C3, the fourth capacitor C4, the first signal port PWM1, the second signal port PWM2, the third signal port PWM3, the fourth signal port PWM4, the fifth signal port PWM5, the sixth signal port PWM6, the seventh signal port PWM7, the eighth signal port PWM8, and the output port V. out ; The ignition power supply port V of the second-stage switching circuit ignition The first capacitor C1 is connected to one end of the first capacitor C1, one end of the second capacitor C2, and the drains of the sixth field-effect transistor Q6 and the tenth field-effect transistor Q10, respectively. The other end of the first capacitor C1 is connected to the other end of the second capacitor C2 and ground. The source of the sixth field-effect transistor Q6 is connected to pins 1 and 2 of the first chip U1, and the gate of the sixth field-effect transistor Q6 is connected to the first signal port PWM1. Pins 3 and 4 of the first chip U1 are connected to one end of the twelfth resistor R12, and the other end of the twelfth resistor R12 is connected to one end of the thirteenth resistor R13 and the second analog port dec2. Pin 5 of the first chip U1 is connected to the other end of the thirteenth resistor R13 and analog ground. Pin 7 of the first chip U1 is connected to one end of the sixteenth resistor R16, and the sixteenth resistor R16 is connected to the first analog port dec1. Pin 8 of the first chip U1 is connected to the 3.3V power supply port. The source of the tenth field-effect transistor Q10 is connected to pin 1 of the third chip U3. Pins 1 and 2 are connected; the gate of the tenth MOSFET Q10 is connected to the fifth signal port PWM5; pins 3 and 4 of the third chip U3 are connected to one end of the eighteenth resistor R18; the other end of the eighteenth resistor R18 is connected to one end of the nineteenth resistor R19 and the sixth analog port dec6; pin 5 of the third chip U3 is connected to the other end of the nineteenth resistor R19 and analog ground; pin 7 of the third chip U3 is connected to one end of the twenty-second resistor R22; the twenty-second resistor R22 is connected to the fifth analog port dec5; pin 8 of the third chip U3 is connected to the 3.3V power supply port; one end of the twelfth resistor R12 is connected to one end of the first inductor L1 and the drain of the eighth MOSFET Q8; one end of the eighteenth resistor R18 is connected to one end of the second inductor L2 and the drain of the twelfth MOSFET Q12; the gate of the eighth MOSFET Q8 is connected to the third signal port PWM3; the source of the eighth MOSFET Q8 is connected to ground. The gate of the twelfth field-effect transistor Q12 is connected to the seventh signal port PWM7, and the source of the twelfth field-effect transistor Q12 is connected to ground; the other end of the first inductor L1 is connected to the source of the seventh field-effect transistor Q7 and the drain of the ninth field-effect transistor Q9. The other end of the second inductor L2 is connected to the source of the eleventh field-effect transistor Q11 and the drain of the thirteenth field-effect transistor Q13; the gate of the ninth field-effect transistor Q9 is connected to the fourth signal port PWM4; and the source of the eighth field-effect transistor Q8 is connected to ground. The gate of the thirteenth field-effect transistor Q13 is connected to the eighth signal port PWM8, and the source of the thirteenth field-effect transistor Q13 is connected to ground. The gate of the seventh field-effect transistor Q7 is connected to the second signal port PWM2, and the gate of the eleventh field-effect transistor Q11 is connected to the sixth signal port PWM6. The drain of the seventh field-effect transistor Q7 is connected to the eleventh field-effect transistor Q11 and pins 1 and 2 of the second chip U2. Pins 3 and 4 of the second chip U2 are connected to one end of the fourteenth resistor R14, one end of the third capacitor C3, one end of the fourth capacitor C4, and the output port V. out Connections: The other end of the fourteenth resistor R14 is connected to one end of the fifteenth resistor R15 and the fourth analog port dec4; pin 5 of the second chip U2 is connected to the other end of the fifteenth resistor R15 and analog ground; pin 7 of the second chip U2 is connected to one end of the seventeenth resistor R17; the other end of the seventeenth resistor R17 is connected to the third analog port dec3; pin 8 of the second chip U2 is connected to the 3.3V power supply port; the other end of the third capacitor C3 is connected to the other end of the fourth capacitor C4 and ground; the twenty-fourth resistor R24 ​​and the twenty-fifth resistor R25 are for ignition charges.

4. The arc ignition circuit for a micro / nano satellite solid-liquid hybrid thruster according to claim 3, characterized in that: The ignition module has a dual backup circuit. For the main circuit, When the required output voltage V out Less than the input voltage V ignition When the circuit is in Buck mode, the duty cycle of the PWM4 control signal input to the gate of the ninth field-effect transistor Q9 is 0, so the ninth field-effect transistor Q9 is continuously off. The duty cycle of the PWM2 control signal input to the gate of the seventh field-effect transistor Q7 is 1, so the seventh field-effect transistor Q7 is continuously on. The PWM1 and PWM3 control signals input to the gates of field-effect transistors Q6 and Q8 are complementary, so the switching of field-effect transistors Q6 and Q8 is complementary. When the sixth field-effect transistor Q6 is on and the eighth field-effect transistor Q8 is off, the current flows from the ignition power supply port through the sixth field-effect transistor Q6, through the first chip U1, to the first inductor L1 to charge it, and then through the seventh field-effect transistor Q7 and the second chip U2 to the ignition terminal V. out At this point, when the sixth field-effect transistor Q6 is in the off state and Q8 is in the on state, due to the presence of the first inductor L1, the current direction will remain unchanged, that is, it flows to the ignition terminal V after passing through the seventh field-effect transistor Q7 and the second chip U2. out Place; When the required output voltage V out Equal to input voltage V ignition When the circuit is in Buck-Boost mode, the PWM1 and PWM3 control signals input to the gates of MOSFETs Q6 and Q8 are complementary and turned on, as are the PWM2 and PWM4 control signals input to the gates of MOSFETs Q7 and Q9. That is, when MOSFETs Q6 and Q9 are on, MOSFETs Q8 and Q7 are off. At this time, current flows from the ignition control port through the sixth MOSFET Q6, the first chip U1, the first inductor L1, and the ninth MOSFET Q9 before flowing to ground. When MOSFETs Q6 and Q9 are off, MOSFETs Q8 and Q7 are on. Due to the presence of the first inductor L1, the current direction remains unchanged, flowing through the seventh MOSFET Q7 and the second chip U2 to the ignition terminal V. out Place; When the required output voltage V out Greater than the input voltage V ignition When the circuit is in Boost mode, the duty cycle of the PWM1 control signal input to the gate of the sixth field-effect transistor Q6 is 1, so the sixth field-effect transistor Q6 is continuously on. The duty cycle of the PWM3 control signal input to the gate of the eighth field-effect transistor Q8 is 0, so the eighth field-effect transistor Q8 is continuously off. The PWM2 and PWM4 control signals input to the gates of field-effect transistors Q7 and Q9 are complementary, so the switching of field-effect transistors Q7 and Q9 is complementary. When the seventh field-effect transistor Q7 is on and the ninth field-effect transistor Q9 is off, the current flows from the ignition port through the sixth field-effect transistor Q6 and the first chip U1 to the first inductor L1 and charges it, then flows through the seventh field-effect transistor Q7 and the second chip U2 to the ignition terminal V. out When the seventh field-effect transistor Q7 is in the off state and the ninth field-effect transistor Q9 is in the on state, the current flows through the ignition power supply port, through the sixth field-effect transistor Q6, the first chip U1, the first inductor L1, and the ninth field-effect transistor Q9, and then flows into the ground. During this process, the inductor is continuously charged to achieve the required output voltage. The current flow in the backup circuit is the same as that in the main circuit.

5. An ignition control strategy for the arc ignition circuit of a micro / nano satellite solid-liquid hybrid thruster as described in any one of claims 1 to 4, characterized in that, The steps are as follows: Step 1: After power-on, initialize the circuit. The aircraft communicates with the ignition module through the control module to transmit ignition commands. Step 2: Determine whether the ignition module has received an ignition command. If no ignition command is received, proceed to Step 3. If an ignition command is received, proceed to Step 4. Step 3: When no ignition command is received, the control module is in ignition protection mode and executes a three-stage ignition protection strategy. Step 4: When the ignition command is received, the control module is in ignition mode and has two ignition control strategies.

6. The ignition control strategy of the arc ignition circuit for the micro / nano satellite solid-liquid hybrid thruster according to claim 5, characterized in that, In step 3, if no ignition command is received, the control module is in ignition protection mode and executes a three-stage ignition protection strategy, as follows: Step 3-1, First stage protection: The control module outputs 0V to the third enable port EN3, and the base potential of the fifth transistor Q5 is 0V, which does not meet the NPN transistor conduction condition; therefore, the potentials of the gates of the third field-effect transistor Q3 and the fourth field-effect transistor Q4 are equal to the potential of the bus power supply port BUSOUT, which does not meet the PMOS conduction condition; the second stage switching circuit is disconnected, and the ignition power supply port V... ignition The voltage is close to zero; Step 3-2, Second stage protection: The control module sends a 10ms 3.3V high-level pulse to the second enable port EN2, and the second diode Q2 has a 10ms conduction time; during this time, the bus power supply port BUSOUT supplies power to the coil of the first magnetic latching relay J1 through the sixth resistor R6, ensuring that its switch is engaged with the ground pin; here, the sixth resistor R6 is used for voltage division of the coil to provide a suitable operating voltage for the coil; the third diode D3 and the fourth diode D4 are freewheeling diodes, used to suppress back electromotive force and provide freewheeling current to the coil after the coil finishes working, dissipating its stored energy; Step 3-3, Third-stage protection: The control module sets the duty cycle of the third signal port PWM3, the fourth signal port PWM4, the seventh signal port PWM7, and the eighth signal port PWM8 to 1, that is, turns on the eighth field-effect transistor Q8, the ninth field-effect transistor Q9, the twelfth field-effect transistor Q12, and the thirteenth field-effect transistor Q13, releasing the residual energy on the first inductor L1 and the second inductor L2; the control module sets the duty cycle of the third signal port PWM3 and the seventh signal port PWM7 to 0, that is, turns off the eighth field-effect transistor Q8 and the twelfth field-effect transistor Q12; sets the duty cycle of the second signal port PWM2 and the sixth signal port PWM6 to 1, that is, turns on the seventh field-effect transistor Q7 and the eleventh field-effect transistor Q11, at this time the ignition charge electrodes are shorted to ground; After ignition is complete, return to step 2 and re-evaluate whether an ignition command has been received.

7. The ignition control strategy of the arc ignition circuit for the micro / nano satellite solid-liquid hybrid thruster according to claim 5, characterized in that, In step 4, when an ignition command is received, the control module is in ignition mode and has two ignition control strategies, as follows: Step 4-1: After the aircraft sends the ignition command and enters the ignition state, the control module first sets the first signal port PWM1, the second signal port PWM2, the third signal port PWM3, the fourth signal port PWM4, the fifth signal port PWM5, the sixth signal port PWM6, the seventh signal port PWM7, and the eighth signal port PWM8, that is, turns off the sixth field-effect transistor Q6, the seventh field-effect transistor Q7, the eighth field-effect transistor Q8, the ninth field-effect transistor Q9, the tenth field-effect transistor Q10, the eleventh field-effect transistor Q11, the twelfth field-effect transistor Q12, and the thirteenth field-effect transistor Q13, and releases the common ground state of the ignition charge electrodes, and proceeds to step 4-2; Step 4-2: Select the ignition control strategy according to the ignition command. The ignition control strategy includes constant power ignition and constant voltage and constant current ignition. If constant power ignition is selected, proceed to step 4-3; if constant voltage and constant current ignition is selected, proceed to step 4-6. Step 4-3: When constant power ignition is selected, the control module adopts an inductor current single-loop PI control strategy. The control module sends a 10ms 3.3V high-level pulse to the first enable port EN1, and the first diode Q1 has a 10ms conduction time. During this time, the bus power supply port BUSOUT supplies power to the coil of the first magnetic latching relay J1 through the fifth resistor R5, ensuring that its switch is engaged with the power supply pin. At this time, the voltage of the bus power supply port BUSOUT is transmitted to the source of the third field-effect transistor Q3 and the source of the fourth field-effect transistor Q4, and the first-stage switching circuit is closed. Here, the fifth resistor R5 is used for voltage division of the coil, which is the line voltage. The coil is provided with a suitable operating voltage; the first diode D1 and the second diode D2 are freewheeling diodes, used to suppress back electromotive force and provide freewheeling current to the coil after the coil has finished working, dissipating its stored energy; the control module outputs 3.3V to the third enable port EN3, and the base potential of the fifth transistor Q5 is about 0.7V, which meets the conduction conditions of the NPN transistor; therefore, after voltage division by the eighth resistor R8 and the ninth resistor R9, the potentials of the gate of the third field-effect transistor Q3 and the gate of the fourth field-effect transistor Q4 are less than the potentials of the source of the third field-effect transistor Q3 and the source of the fourth field-effect transistor Q4, and the PMOS conduction conditions are met; The second-stage switching circuit is closed, and the ignition power supply port V... ignition When the voltage is close to the bus power supply port BUSOUT, proceed to step 4-4; Step 4-4: The control module processes the collected analog signals and determines whether the input voltage and current meet the requirements. If they do not meet the requirements, an emergency stop protection is activated; if they do meet the requirements, the control strategy is executed. Constant power ignition adopts a single-loop PI control strategy for inductor current. The control module only performs PI algorithm control on the collected inductor current value, with a control frequency of 200kHz. The control is adjusted according to the real-time collected values ​​to ensure a power distribution capability of 150W constant power output. The control module determines whether the output voltage and current exceed the limits. If they do, an emergency stop protection is activated; if they do not exceed the limits, ignition is executed, and the process proceeds to step 4-5. Steps 4-5: Disconnect the second-stage switching circuit and the first-stage switching circuit in sequence. Ignition ends. Return to step 2 and re-determine whether the ignition command has been received. In steps 4-6, when constant voltage and constant current ignition is selected, the control module adopts a dual-loop control strategy of inductor current inner loop and voltage and current outer loop. The control module sends a 10ms 3.3V high-level pulse to the first enable port EN1, and the first diode Q1 has a 10ms conduction time. During this time, the bus power supply port BUSOUT supplies power to the coil of the first magnetic latching relay J1 through the fifth resistor R5, ensuring that its switch is engaged with the power supply pin. At this time, the voltage of the bus power supply port BUSOUT is transmitted to the source of the third field-effect transistor Q3 and the source of the fourth field-effect transistor Q4, and the first-stage switching circuit is closed. The control module outputs 3.3V to the third enable port EN3, and the base potential of the fifth transistor Q5 is about 0.7V, which meets the conduction condition of the NPN transistor. Therefore, after voltage division by the eighth resistor R8 and the ninth resistor R9, the potential of the gate of the third field-effect transistor Q3 and the gate of the fourth field-effect transistor Q4 is less than the potential of the source of the third field-effect transistor Q3 and the source of the fourth field-effect transistor Q4, and the PMOS conduction condition is met. The second-stage switching circuit is closed, and the ignition power supply port V... ignition When the voltage is close to the bus power supply port BUSOUT, proceed to step 4-7; Steps 4-7: The control module processes the acquired analog signals and determines whether the input voltage and current meet the requirements. If not, an emergency stop protection is initiated; otherwise, the control strategy is executed. Constant voltage and constant current ignition employs an inner loop inductor current control strategy and an outer loop PI control strategy for output voltage and current. The control module performs outer loop PI algorithm control on the acquired output voltage and current values. The outer loop PI controller uses a dual-loop competition method for output voltage and current to obtain the target inductor current value, which is then subtracted from the acquired inductor current value to obtain the error value. This error value is then entered into the inner loop PI algorithm control at a frequency of 200kHz. Adjustments are made based on the real-time acquired values ​​to ensure a maximum output of 150W@50V3A with constant voltage followed by constant current distribution capability. The control module then determines whether the output voltage and current exceed the limits. If they do, an emergency stop protection is initiated; otherwise, ignition is executed, and the process proceeds to step 4-8. Steps 4-8: Disconnect the second-stage switching circuit and the first-stage switching circuit in sequence. Ignition ends. Return to step 2 and re-determine whether the ignition command has been received.

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