Constant current drive control circuit for spaceborne thrusters suitable for wide input voltage

Abstract

The present invention provides a satellite-borne thruster constant current drive control circuit suitable for wide input voltage, comprising: a thruster control module, a PMOS tube drive module, a differential isolation amplifier module, a state acquisition module, a current feedback comparison module, and an NMOS tube drive module. The thruster drive current is input to the differential isolation amplifier circuit in the form of a voltage signal through a current sampling resistor, thereby converting the current signal into a voltage signal. The amplified voltage signal is compared with the reference voltage to control the real-time on-off of the NMOS tube, thereby achieving precise and stable control of the thruster load current. The present invention solves the problem that the satellite-borne thruster cannot adaptively operate normally under a wide input satellite bus voltage (28V~100V). The control and state acquisition of the satellite-borne thruster with a wide input satellite bus voltage (28V~100V) are realized, and the circuit application is flexible, the bus adaptability is strong, the response speed is fast, and the reliability is high.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite-borne thrusters, and in particular to a constant-current drive control circuit for satellite-borne thrusters suitable for a wide input voltage. Background Art

[0002] Thrusters are a crucial component of satellite platforms, used for main propulsion, orbit maintenance, and orbit maneuvers. With the rapid development of satellite applications, satellite load power demands are increasing, and satellite bus voltages have gradually increased from the original 28V to 42V or 100V. Current thruster drive control technologies struggle to meet the requirements of wide-voltage or high-voltage inputs. There is an urgent need to design a constant-current drive control circuit for onboard thrusters that can operate over a wide input voltage range.

[0003] Publication No. CN105135031A discloses a "Satellite Chemical Thruster Solenoid Valve Control and Status Acquisition Circuit." This patent uses weak current to precisely control strong current, but is only suitable for driving and controlling a satellite's 28V bus voltage. However, this patent suffers from poor bus adaptability and an inability to achieve constant current drive.

[0004] Publication number CN107809231A discloses "Circuit and Method for Power Field Effect Drive Control and State Acquisition of Satellite-Borne Heating Plates." This circuit includes, among other things, a first fuse connected in parallel with a second fuse, a first resistor connected in series with a second resistor, a first diode connected in parallel with a second diode, a third resistor connected in parallel with a fourth resistor and a fifth resistor, the first diode connected in series with the third resistor, and the third resistor connected to the base of a first transistor. The patent's disadvantages are that it cannot accommodate thruster drive circuits with voltages higher than 28V and cannot achieve constant current drive.

[0005] Publication number CN104267757A discloses the "Electronic Control System and Control Method for High-orbit Satellite Heaters", which includes an integrated instruction latch module, an instruction drive module and a control output module. The instruction latch module converts the instantaneous heater control instruction into a continuous control instruction. The continuous control instruction generates execution signals for controlling the positive and negative ends of the heater respectively after passing through the instruction drive module. Finally, the control output module outputs the execution signals simultaneously to both ends of the heater to achieve thermal control of the entire satellite.

[0006] Publication number CN107958802A discloses a "VMOS drive circuit for satellite-borne explosive devices and its control method." The circuit includes a first relay, connected to the drain of a first transistor, a first resistor connected in series with a second resistor, both connected to the gate of the first transistor, a sixth resistor connected in series with a seventh resistor, the sixth, eighth, ninth, tenth, and eleventh resistors connected to the source of the first transistor, the first, twelfth, and thirteenth resistors connected to the second relay, the seventh resistor connected to the drain of the second transistor, and the third relay connected to the source of the second transistor. However, this patent document suffers from poor busbar adaptability and inability to achieve constant current drive.

[0007] Publication number CN109545621A discloses a drive circuit for aerospace high-power contactors, comprising: a closing drive circuit and a machine closing drive circuit, wherein the closing drive circuit comprises a power relay closing drive circuit, a contactor closing drive circuit, and a machine state relay closing drive circuit; and a closing drive circuit comprises a power relay closing drive circuit, a contactor closing drive circuit, and a machine state relay closing drive circuit. However, the patent document has the following drawbacks: the drive circuit requires a reverse peak elimination circuit to suppress back electromotive force, requires electromagnetic interference resistance design, and cannot achieve constant current drive. Summary of the Invention

[0008] In view of the defects in the prior art, the object of the present invention is to provide a constant current drive control circuit for a satellite-borne thruster suitable for a wide input voltage.

[0009] According to the present invention, a constant current drive control circuit for a space-borne thruster suitable for a wide input voltage is provided, comprising: a thruster control module, a PMOS tube drive module, a differential isolation amplifier module, a state acquisition module, a current feedback comparison module, and an NMOS tube drive module;

[0010] The signal input end of the thruster control module is connected to the current feedback comparison module, and the signal output end of the thruster control module is connected to the PMOS tube driving module;

[0011] The PMOS tube driving module is connected to the positive terminal of the onboard thruster load, and the PMOS tube driving module receives the bus input voltage;

[0012] The NMOS tube driving module is respectively connected to the negative terminal of the onboard thruster load and the differential isolation amplifier module, and the control terminal of the NMOS tube driving module is connected to the current feedback module;

[0013] The differential isolation amplification module acquires the current signal in real time and converts it into a voltage signal, and then outputs it to the current feedback comparison module and the state acquisition module. The differential isolation amplification module is connected to the main loop;

[0014] The current feedback comparison module controls the switch of the NMOS tube driving module in real time, thereby controlling the negative end output of the onboard thruster load.

[0015] Preferably, the thruster control module includes a diode V1, a resistor R3, a resistor R4, a transistor Q1, and a resistor R2. The anode of the diode V1 receives the thruster control signal, the cathode of the diode V1 is respectively connected to one end of the resistor R3 and the current feedback comparison module, the other end of the resistor R3 is respectively connected to one end of the resistor R4 and the base of the transistor Q1, the emitter of the transistor Q1 is connected to the other end of the resistor R4 and then connected to 12VGND, the collector of the transistor Q1 is connected to one end of the resistor R2, and the other end of the resistor R2 is connected to the PMOS tube drive module.

[0016] Preferably, the PMOS tube driving module includes a resistor R1, a Zener diode V2, a PMOS tube S1, a diode V3 and a resistor R6, one end of the resistor R1 is respectively connected to the other end of the resistor R2, the positive electrode of the Zener diode V2 and the gate of the PMOS tube S1, the other end of the resistor R1 is connected to the negative electrode of the Zener diode V2 and the drain of the PMOS tube S1, and receives the bus input voltage, the source of the PMOS tube S1 is respectively connected to the positive electrode of the diode V3 and one end of the resistor R6, the negative electrode of the diode V3 is connected to the other end of the resistor R6 and the positive end of the satellite thruster load.

[0017] Preferably, the NMOS transistor driving module includes a resistor R17 and an NMOS transistor S2, the drain of the NMOS transistor S2 is connected to the negative end of the satellite thruster load, the gate of the NMOS transistor S2 is connected to one end of the resistor R17, the other end of the resistor R17 is connected to the current feedback comparison module, the source of the NMOS transistor S2 is connected to the differential isolation amplification module, and a diode V5 is connected in series between the drain of the NMOS transistor S2 and the other end of the resistor R6, the cathode of the diode V5 is connected to the other end of the resistor R6, and the anode of the diode V5 is connected to the drain of the NMOS transistor S2.

[0018] Preferably, the differential isolation amplification module includes a resistor R7, a resistor R8, a resistor R9, a resistor R10, a sampling resistor R18 and an operational amplifier U1A, one end of the resistor R7 is respectively connected to the source of the NMOS tube S2 and one end of the sampling resistor R18, the other end of the sampling resistor R18 is respectively connected to one end of the resistor R8 and the main loop, the other end of the resistor R7 is respectively connected to one end of the resistor R9 and the non-inverting input terminal of the operational amplifier U1A, the other end of the resistor R9 is connected to PGNDA, the other end of the resistor R8 is respectively connected to the inverting input terminal of the operational amplifier U1A and one end of the resistor R10, the other end of the resistor R10 is connected to the output terminal of the operational amplifier U1A; the output terminal of the operational amplifier U1A is respectively connected to the state acquisition module and the current feedback comparison module.

[0019] Preferably, the status acquisition module includes an operational amplifier U1B, a resistor R12 and a resistor R13, the non-inverting input terminal of the operational amplifier U1B is connected to the output terminal of the operational amplifier U1A, the inverting input terminal of the operational amplifier U1B is connected to the output terminal of the operational amplifier U1B and one end of the resistor R12, the other end of the resistor R12 is connected to one end of the resistor R13, the other end of the resistor R13 is connected to AGND, and one end of the resistor R13 receives the thruster status signal.

[0020] Preferably, the current feedback comparison module includes a resistor R14, a resistor R15, a resistor R16, an operational amplifier U1C and an AND gate U2A, the inverting input terminal of the operational amplifier U1C is connected to the output terminal of the operational amplifier U1A, the non-inverting input terminal of the operational amplifier U1C is connected to a 5V reference voltage, the output terminal of the operational amplifier U1C is respectively connected to one end of the resistor R14 and one end of the resistor R15, the other end of the resistor R14 is connected to P12VA, the other end of the resistor R15 is connected to the input terminal of the AND gate U2A, one end of the resistor R16 is connected to the input terminal of the AND gate U2A, the output terminal of the AND gate U2A is connected to the other end of the resistor R17, and the other end of the resistor R16 is connected to the cathode of the diode V1.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] This invention solves the problem of satellite-borne thrusters being unable to adapt and operate normally under a wide input satellite bus voltage range (28V to 100V). It achieves control and status acquisition of satellite-borne thrusters under a wide input satellite bus voltage range (28V to 100V), featuring flexible circuit application, strong bus adaptability, fast response, and high reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0024] Figure 1 The present invention is a constant current drive control circuit diagram of a satellite-borne thruster suitable for wide input voltage. DETAILED DESCRIPTION

[0025] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0026] The present invention discloses a satellite-borne thruster constant-current drive control circuit suitable for a wide input voltage. The satellite-borne thruster constant-current drive control circuit suitable for a wide input voltage can effectively achieve precise control of strong electricity through weak current drive, and can be applied to satellite bus voltages of 28V to 100V through a closed-loop constant-current drive control method, while having working current and status acquisition functions.

[0027] Specifically, refer to Figure 1 The constant current drive control circuit includes: thruster control module, PMOS tube drive module, differential isolation amplifier module, state acquisition module, current feedback comparison module and NMOS tube drive module. The functions implemented by each module are as follows:

[0028] The signal input end of the thruster control module is connected to the current feedback comparison module, and the signal output end of the thruster control module is connected to the PMOS tube driving module.

[0029] The PMOS tube driver module is connected to the positive terminal of the onboard thruster load. The PMOS tube driver module receives the bus input voltage and controls the real-time output of the thruster load positive terminal through the PMOS tube driver module.

[0030] The NMOS tube driving module is connected to the negative end of the satellite thruster load and the differential isolation amplifier module respectively, and the control end of the NMOS tube driving module is connected to the current feedback module.

[0031] The differential isolation amplifier module amplifies the thruster drive current in the form of a voltage signal after passing through the current sampling resistor R18, and then outputs it to the current feedback comparison module and the status acquisition module and has an isolation function. The differential isolation amplifier module is connected to the main loop.

[0032] The current feedback comparison module controls the switch of the NMOS tube driver module in real time by comparing the voltage signal with the reference voltage in real time. After the comparator output signal and the control signal are input to the AND gate, the AND gate output signal is output to the NMOS tube driver module to control the switch of the NMOS tube S2 in real time, thereby controlling the negative end output of the onboard thruster load.

[0033] The status acquisition module realizes the acquisition of the thruster working status.

[0034] Specifically, the circuit structure of each component module and its connection relationship are as follows.

[0035] The thruster control module includes a diode V1, a resistor R3, a resistor R4, a transistor Q1 and a resistor R2. The anode of the diode V1 receives the thruster control signal, the cathode of the diode V1 is respectively connected to one end of the resistor R3 and the current feedback comparison module, the other end of the resistor R3 is respectively connected to one end of the resistor R4 and the base of the transistor Q1, the emitter of the transistor Q1 is connected to the other end of the resistor R4 and then to 12VGND, the collector of the transistor Q1 is connected to one end of the resistor R2, and the other end of the resistor R2 is connected to the PMOS tube drive module.

[0036] The PMOS transistor drive module includes a resistor R1, a Zener diode V2, a PMOS transistor S1, a diode V3, and a resistor R6. One end of the resistor R1 is respectively connected to the other end of the resistor R2, the positive electrode of the Zener diode V2, and the gate of the PMOS transistor S1. The other end of the resistor R1 is connected to the negative electrode of the Zener diode V2 and the drain of the PMOS transistor S1, and receives the bus input voltage. The source of the PMOS transistor S1 is respectively connected to the positive electrode of the diode V3 and one end of the resistor R6. The negative electrode of the diode V3 is connected to the other end of the resistor R6 and the positive end of the onboard thruster load.

[0037] The NMOS transistor drive module includes a resistor R17 and an NMOS transistor S2. The drain of the NMOS transistor S2 is connected to the negative end of the satellite thruster load. The gate of the NMOS transistor S2 is connected to one end of the resistor R17. The other end of the resistor R17 is connected to the current feedback comparison module. The source of the NMOS transistor is connected to the differential isolation amplifier module. A diode V5 is connected in series between the drain of the NMOS transistor S2 and the other end of the resistor R6. The cathode of the diode V5 is connected to the other end of the resistor R6. The anode of the diode V5 is connected to the drain of the NMOS transistor S2.

[0038] The differential isolation amplifier module includes resistor R7, resistor R8, resistor R9, resistor R10, sampling resistor R18 and operational amplifier U1A. One end of resistor R7 is respectively connected to the source of the NMOS tube and one end of the sampling resistor R18, the other end of the sampling resistor R18 is respectively connected to one end of the resistor R8 and the main loop, the other end of the resistor R7 is respectively connected to one end of the resistor R9 and the non-inverting input end of the operational amplifier U1A, the other end of the resistor R9 is connected to PGNDA, the other end of the resistor R8 is respectively connected to the inverting input end of the operational amplifier U1A and one end of the resistor R10, and the other end of the resistor R10 is connected to the output end of the operational amplifier U1A; the output end of the operational amplifier U1A is respectively connected to the state acquisition module and the current feedback comparison module.

[0039] The status acquisition module includes an operational amplifier U1B, a resistor R12 and a resistor R13. The non-inverting input terminal of the operational amplifier U1B is connected to the output terminal of the operational amplifier U1A, the inverting input terminal of the operational amplifier U1B is connected to the output terminal of the operational amplifier U1B and one end of the resistor R12, the other end of the resistor R12 is connected to one end of the resistor R13, the other end of the resistor R13 is connected to AGND, and one end of the resistor R13 receives the thruster status signal.

[0040] The current feedback comparison module includes resistor R14, resistor R15, resistor R16, operational amplifier U1C and AND gate U2A. The inverting input terminal of operational amplifier U1C is connected to the output terminal of operational amplifier U1A, the non-inverting input terminal of operational amplifier U1C is connected to the 5V reference voltage, the output terminal of operational amplifier U1C is respectively connected to one end of resistor R14 and one end of resistor R15, the other end of resistor R14 is connected to P12VA, the other end of resistor R15 is connected to the input terminal of AND gate U2A, one end of resistor R16 is connected to the input terminal of AND gate U2A, the output terminal of AND gate U2A is connected to the other end of resistor R17, and the other end of resistor R16 is connected to the cathode of diode V1.

[0041] The working principle of the thruster constant current drive control circuit of the present invention is as follows:

[0042] Step 1: When the control command input voltage is 10V to 12V, transistor Q1 operates in the saturation region. Resistors R1, R2, and transistor Q1 form a path. The voltage drop across resistor R1 is applied to the gate and source of the PMOS transistor, causing the PMOS transistor S1 to turn on, achieving control output at the positive output of the thruster. At the same time, the 10V to 12V voltage passes through resistor R16 and the output of operational amplifier U1C (due to the +5V input voltage at the positive terminal of operational amplifier U1C, the output is set to a high level by default when the negative terminal voltage is lower than 5V due to the open-loop principle of operational amplifier U1C). After passing through the AND gate U2A comparator, it passes through the current-limiting resistor R17, driving the NMOS transistor S2 to turn on, achieving control output at the negative output of the thruster.

[0043] In step 2, the current sampling resistor R18, connected in series with the thruster power circuit, converts the current signal into a voltage signal and inputs it into the differential amplifier U1A for signal amplification. When the thruster circuit current exceeds the set value, the voltage output signal of the differential amplifier U1A exceeds 5V. This signal is compared with the reference 5V voltage, causing the output of the operational amplifier U1C to be low. This low-level signal, along with the 10-12V control command input, enters the AND gate U2A simultaneously. The output of the AND gate U2A is low, turning off its NMOS transistor S2.

[0044] In step three, after the NMOS tube S2 is turned off, since the thruster is an inductive device, the current cannot change suddenly. The output signal of the negative end of the thruster slowly decreases, and the current passing through the current sampling resistor R18 gradually becomes less than the set value. The output voltage of the differential amplifier U1A is less than 5V, and the positive end voltage of the operational amplifier U1C is higher than the negative end. The output of the operational amplifier U1C is high. After the high-level signal and the 10~12V input of the control instruction enter the AND gate U2A at the same time, the output of the AND gate U2A is high, turning on its NMOS tube S2. When the control instruction input is 10~12V, steps two and three are repeated to realize the opening and closing of the NMOS tube S2, thereby realizing the current closed-loop control of the thruster main circuit and making the thruster work normally.

[0045] Step 4: The thruster working status is collected. The output signal of the differential amplifier U1A is used to collect the current status through the voltage follower circuit to indicate the working status of the circuit.

[0046] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A constant current drive control circuit for a space-borne thruster suitable for a wide input voltage, characterized in that: include: Thruster control module, PMOS tube driver module, differential isolation amplifier module, state acquisition module, current feedback comparison module and NMOS tube driver module; The signal input end of the thruster control module is connected to the current feedback comparison module, and the signal output end of the thruster control module is connected to the PMOS tube driving module; The PMOS tube driving module is connected to the positive terminal of the onboard thruster load, and the PMOS tube driving module receives the bus input voltage; The NMOS tube driving module is respectively connected to the negative terminal of the onboard thruster load and the differential isolation amplifier module, and the control terminal of the NMOS tube driving module is connected to the current feedback module; The differential isolation amplification module acquires the current signal in real time and converts it into a voltage signal, and then outputs it to the current feedback comparison module and the state acquisition module. The differential isolation amplification module is connected to the main loop; The current feedback comparison module controls the switch of the NMOS tube driving module in real time, thereby controlling the negative terminal output of the onboard thruster load; The PMOS transistor driver module includes a resistor R1, a Zener diode V2, a PMOS transistor S1, a diode V3, and a resistor R6. One end of the resistor R1 is respectively connected to the other end of the resistor R2, the positive electrode of the Zener diode V2, and the gate of the PMOS transistor S1. The other end of the resistor R1 is connected to the negative electrode of the Zener diode V2 and the drain of the PMOS transistor S1, and receives the bus input voltage. The source of the PMOS transistor S1 is respectively connected to the positive electrode of the diode V3 and one end of the resistor R6. The negative electrode of the diode V3 is connected to the other end of the resistor R6 and the positive end of the onboard thruster load. The NMOS transistor driving module includes a resistor R17 and an NMOS transistor S2, the drain of the NMOS transistor S2 is connected to the negative end of the onboard thruster load, the gate of the NMOS transistor S2 is connected to one end of the resistor R17, the other end of the resistor R17 is connected to the current feedback comparison module, the source of the NMOS transistor S2 is connected to the differential isolation amplifier module, and a diode V5 is connected in series between the drain of the NMOS transistor S2 and the other end of the resistor R6, the cathode of the diode V5 is connected to the other end of the resistor R6, and the anode of the diode V5 is connected to the drain of the NMOS transistor S2; The differential isolation amplification module includes a resistor R7, a resistor R8, a resistor R9, a resistor R10, a sampling resistor R18 and an operational amplifier U1A, one end of the resistor R7 is respectively connected to the source of the NMOS tube S2 and one end of the sampling resistor R18, the other end of the sampling resistor R18 is respectively connected to one end of the resistor R8 and the main loop, the other end of the resistor R7 is respectively connected to one end of the resistor R9 and the non-inverting input terminal of the operational amplifier U1A, the other end of the resistor R9 is connected to PGNDA, the other end of the resistor R8 is respectively connected to the inverting input terminal of the operational amplifier U1A and one end of the resistor R10, the other end of the resistor R10 is connected to the output terminal of the operational amplifier U1A; the output terminal of the operational amplifier U1A is respectively connected to the state acquisition module and the current feedback comparison module.

2. The satellite-borne thruster constant current drive control circuit suitable for wide input voltage according to claim 1 is characterized in that: The thruster control module includes a diode V1, a resistor R3, a resistor R4, a transistor Q1, and a resistor R2. The anode of the diode V1 receives a thruster control signal, the cathode of the diode V1 is respectively connected to one end of the resistor R3 and the current feedback comparison module, the other end of the resistor R3 is respectively connected to one end of the resistor R4 and the base of the transistor Q1, the emitter of the transistor Q1 is connected to the other end of the resistor R4 and then to 12VGND, the collector of the transistor Q1 is connected to one end of the resistor R2, and the other end of the resistor R2 is connected to the PMOS transistor drive module.

3. The satellite-borne thruster constant current drive control circuit suitable for wide input voltage according to claim 1 is characterized in that: The status acquisition module includes an operational amplifier U1B, a resistor R12 and a resistor R13. The non-inverting input end of the operational amplifier U1B is connected to the output end of the operational amplifier U1A, the inverting input end of the operational amplifier U1B is connected to the output end of the operational amplifier U1B and one end of the resistor R12, the other end of the resistor R12 is connected to one end of the resistor R13, the other end of the resistor R13 is connected to AGND, and one end of the resistor R13 receives the thruster status signal.

4. The satellite-borne thruster constant current drive control circuit suitable for wide input voltage according to claim 1 is characterized in that: The current feedback comparison module includes a resistor R14, a resistor R15, a resistor R16, an operational amplifier U1C and an AND gate U2A. The inverting input terminal of the operational amplifier U1C is connected to the output terminal of the operational amplifier U1A, the non-inverting input terminal of the operational amplifier U1C is connected to a 5V reference voltage, the output terminal of the operational amplifier U1C is respectively connected to one end of the resistor R14 and one end of the resistor R15, the other end of the resistor R14 is connected to P12VA, the other end of the resistor R15 is connected to the input terminal of the AND gate U2A, one end of the resistor R16 is connected to the input terminal of the AND gate U2A, the output terminal of the AND gate U2A is connected to the other end of the resistor R17, and the other end of the resistor R16 is connected to the cathode of the diode V1.

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