CN113086252B - High-reliability solar cell array shunt regulation system and method - Google Patents
High-reliability solar cell array shunt regulation system and method Download PDFInfo
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- CN113086252B CN113086252B CN202110358810.4A CN202110358810A CN113086252B CN 113086252 B CN113086252 B CN 113086252B CN 202110358810 A CN202110358810 A CN 202110358810A CN 113086252 B CN113086252 B CN 113086252B
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Abstract
The invention provides a high-reliability solar cell array shunt regulation system which comprises a forced shunt signal shielding circuit, a forced shunt signal generating circuit, a shunt driving circuit and a shunt circuit, wherein the output end of the forced shunt signal shielding circuit is respectively connected with the input ends of the forced shunt signal generating circuit and the shunt driving circuit, and the output ends of the forced shunt signal generating circuit and the shunt driving circuit are respectively connected with the input end of the shunt circuit. The invention also provides a high-reliability solar cell array shunt regulation method. The invention has the beneficial effects that: under the condition that a solar cell array shunt regulation electric control circuit breaks down, the stability of bus voltage can still be ensured, the storage battery pack can not be overcharged, and the safety of the spacecraft is further ensured.
Description
Technical Field
The invention relates to a solar cell array, in particular to a high-reliability solar cell array shunt regulation system and method.
Background
The solar cell array is a main power supply of the spacecraft, under the condition of sunlight irradiation, power is output, power is supplied to an electric load used by the spacecraft on one hand, the storage battery pack is charged on the other hand, and when the storage battery pack is fully charged, the solar cell array enters a shunt regulation state, so that the stability of a primary power supply bus is ensured.
However, due to the timing requirement of the control logic, a certain single-point condition exists in the shunt regulation circuit, once a single-point fault occurs, the stability of a primary power bus cannot be guaranteed, and even the safety of the whole satellite can be affected, so that the solar cell array is generally divided into a plurality of sub-arrays to reduce the influence caused by the single-point fault, and the risk of overcharge of the storage battery pack still exists for the spacecraft with low long-term power consumption; for a spacecraft with insufficient output power margin of the solar cell array, task safety may be affected.
Therefore, how to still ensure the stability of the bus voltage under the condition that the solar cell array shunt regulation electric control circuit fails, which does not result in the overcharge of the storage battery pack, and further ensures the safety of the spacecraft is a technical problem to be solved urgently by technical personnel in the field.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a high-reliability solar cell array shunt regulation system and method.
The invention provides a high-reliability solar cell array shunt regulation system, which comprises:
a shunt circuit: when the voltage of the power supply bus is increased to a set value, the output power of the solar cell array is subjected to shunt regulation;
shunt drive circuit: providing a drive signal for shunt regulation of the shunt circuit;
forced shunt signal shielding circuit: when the satellite does not need the output power of the solar cell array to supply power to the satellite bus, the satellite is in an enabling state, and the execution of the shunt driving circuit is forbidden; when the satellite needs the solar cell array output power to supply power to the satellite bus, the satellite is in a forbidden state, and the execution of the shunt driving circuit is enabled;
forced shunt signal generating circuit: outputting a forced shunting signal and enabling a shunting circuit to be in a full shunting state;
the output end of the forced shunt signal shielding circuit is respectively connected with the input ends of the forced shunt signal generating circuit and the shunt driving circuit, and the output ends of the forced shunt signal generating circuit and the shunt driving circuit are respectively connected with the input end of the shunt circuit.
As a further improvement of the present invention, the forced shunting signal shielding circuit includes a relay K7, the shunting driving circuit includes a comparator U1, a transistor V1, a transistor V2, a transistor V3 and a transistor V4, the transistor V1 and the transistor V2 form a push-pull circuit, a positive input terminal of the comparator U1 is connected to a divided voltage VBUS-F of a bus voltage, a negative input terminal of the comparator U1 is connected to a shunting reference Vref, an output terminal of the comparator U1 is connected to the push-pull circuit, a base of the transistor V3 is connected to the relay K7, a collector of the transistor V3 is grounded, an emitter of the transistor V3 is connected to a collector of the transistor V2, a base of the transistor V4 is connected to a shunting enable/disable command signal terminal, a collector of the transistor V4 is connected between the comparator U1 and the push-pull circuit, the emitter of the transistor V4 is grounded.
As a further improvement of the present invention, the forced shunt signal shielding circuit further includes a resistor R12, a resistor R13, and a capacitor C3, the pin 1 and the pin 2 of the relay K7 are respectively connected to the base of the triode V3, the pin 3 of the relay K7 is connected to one end of the resistor R12, the other end of the resistor R12 is respectively connected to one ends of the resistor R13 and the capacitor C3, the other ends of the resistor R13 and the capacitor C3 are grounded, the other end of the resistor R12 is connected to a relay state signal end collected on the satellite, the pin 7 and the pin 9 of the relay K7 are respectively connected to the bus voltage VBUS, and the pin 8 of the relay K7 is connected to a forced shunt enable signal end.
As a further improvement of the present invention, the base of the transistor V1 and the base of the transistor V2 are respectively connected to the output terminal of the comparator U1, the emitter of the transistor V1 and the emitter of the transistor V2 are respectively connected to the input terminal of the shunting circuit, and the collector of the transistor V1 is connected to the bus voltage VBUS.
As a further improvement of the present invention, the shunt circuit includes a resistor R5, a resistor R6, a shunt transistor V5, and a shunt transistor V6, a gate of the shunt transistor V6 is connected to one end of the resistor R6, the other end of the resistor R6 is connected to an emitter of the transistor V1 and an emitter of the transistor V2, a source of the shunt transistor V6 is grounded, a drain of the shunt transistor V6 is connected to a source of the shunt transistor V5, a gate of the shunt transistor V5 is connected to one end of the resistor R5, the other end of the resistor R5 is connected to an emitter of the transistor V1 and an emitter of the transistor V2, and a drain of the shunt transistor V5 is connected to the solar cell array SAS.
As a further improvement of the invention, the solar cell array SAS supplies the bus voltage VBUS via an isolation diode D2.
As a further improvement of the present invention, the forced shunting signal generating circuit includes a transistor V7, a resistor R10, and a diode D1, a base of the transistor V7 is connected to a shunting enable/disable command signal terminal, a collector of the transistor V7 is grounded, an emitter of the transistor V7 is connected to the pin 1 and the pin 2 of the relay K7, an emitter of the transistor V7 is connected to one end of the resistor R10, the other end of the resistor R10 is connected to a battery VBAT, an emitter of the transistor V7 is connected to an anode of the diode D1, and a cathode of the diode D1 is connected to an emitter of the transistor V1 and an emitter of the transistor V2, respectively.
As a further improvement of the present invention, the forced shunting signal generating circuit further includes a resistor R15, a capacitor C4, a resistor R14, a capacitor C2, and a resistor R11, wherein one end of the resistor R15 is connected to the base of the transistor V7, the other end of the resistor R15 is grounded, one end of the capacitor C4 is connected to the base of the transistor V7, the other end of the capacitor C4 is grounded, one end of the resistor R14 is connected to the base of the transistor V7, the other end of the resistor R14 is connected to the emitter of the transistor V7, one end of the capacitor C4 is connected to the emitter of the transistor V7, the other end of the capacitor C4 is grounded, one end of the resistor R11 is connected to the emitter of the transistor V7, and the other end of the resistor R11 is grounded.
The invention also provides a high-reliability solar cell array shunt regulation method, which adopts the high-reliability solar cell array shunt regulation system to carry out the following processes: s1, during the on-orbit normal operation of the spacecraft, the shunt control circuit works normally, the relay K7 is in a forced shunt prohibition state, a forced shunt signal is shielded, an input signal K7_ TM of the relay K7 is in a relay state acquired on the satellite, an output signal of the relay K7 is V14_ B, at the moment, the V14_ B signal is low level, the triode V3 is in a conducting state, the triode V4 is in a disconnected state in a normal state, the V4A _ Q signal is an output signal of a push-pull circuit composed of the triode V1 and the triode V2, the positive input end of the comparator U1 is connected to the divided voltage VBUS-F of the bus voltage, the negative input end of the comparator U1 is connected to the shunt reference Vref, the signals of the positive input end and the negative input end are compared to output a high/low signal to control the push-pull circuit, the V4A _ Q signal controls the shunt transistor V5 and the shunt transistor V6 to be connected or disconnected, and the solar cell array SAS supplies power to the bus voltage VBUS through the isolation diode D2.
As a further improvement of the invention, the method also comprises the following processes:
s2, if the output of the comparator U1 is continuously high-level fault, the push-pull circuit continuously outputs high level, the shunt transistor V5 and the shunt transistor V6 are in a normally-on state, if the output power of the solar cell array SAS is limited, when the bus voltage VBUS monitored on the satellite is abnormally increased, the shunt driving circuit enters a shunt state by sending a shunt enabling instruction to the triode V4 and conducting the triode V4, and when the bus voltage VBUS is lower than a set value, the shunt prohibiting instruction is sent to the triode V4 and the triode V4 is disconnected, so that the shunt driving circuit enters a non-shunt state;
s3, if the comparator U1 has a fault of continuously being at a low level, or the push-pull circuit has a fault of continuously outputting the low level, the shunt transistor V5 and the shunt transistor V6 are in a normally-off state, the bus voltage VBUS will continuously rise, a forced shunt enabling instruction is sent to the relay K7 firstly, so that the relay K7 relieves the shielding effect on forced shunt signals, the V14_ B signal is changed from the low level to the high level, the triode V3 is in an off state, the V14A _ Q signal is also changed from the low level to the high level, the shunt transistor V5 and the shunt transistor V6 are both in an on state, and the output power of the solar cell array SAS is shunted; when the bus voltage VBUS is lower than the set value, by sending a shunt prohibition instruction to the transistor V7, the transistor V7 is in a conducting state, and the V14_ B signal and the V14A _ Q signal change from a high level to a low level, so that the shunt transistor V5 and the shunt transistor V6 are both in a disconnected state; when the bus voltage VBUS rises to the set value again, the shunt transistor V5 and the shunt transistor V6 are both in an on state by sending a shunt enable instruction to the transistor V7, so that the V14_ B signal and the V14A _ Q signal change from a low level to a high level;
s4, if the spacecraft is launched in a power-off state, the forced shunt signal generating circuit obtains power from the storage battery pack VBAT, the relay K7 is set to be in a forced shunt enabling state before launching, the V14_ B signal and the V14A _ Q signal are both high-level, the triode V3 is in a disconnected state, and when the power of the solar cell array SAS is output, the power is shunted through the shunt transistor V5 and the shunt transistor V6.
The invention has the beneficial effects that: the high-reliability solar cell array shunt regulation system can still ensure the stability of bus voltage under the condition that a solar cell array shunt regulation electric control circuit has a fault, can not cause the overcharge of a storage battery pack, and further ensures the safety of a spacecraft.
Drawings
FIG. 1 is a schematic diagram of a high-reliability solar array shunt regulation system of the present invention;
fig. 2 is a circuit diagram of a forced shunt signal shielding circuit of a high-reliability solar cell array shunt regulation system of the invention;
fig. 3 is a circuit diagram of a forced shunt signal generating circuit of a high-reliability solar cell array shunt regulating system according to the present invention;
fig. 4 is a circuit diagram of a shunt driving circuit of a high-reliability solar cell array shunt regulation system of the invention;
fig. 5 is a circuit diagram of a shunt circuit of a high-reliability solar cell array shunt regulation system of the invention.
Detailed Description
The invention is further described with reference to the following description and embodiments in conjunction with the accompanying drawings.
As shown in fig. 1 to 5, a high-reliability solar cell array shunt regulation system includes a forced shunt signal shielding circuit 101, a forced shunt signal generating circuit 102, a shunt driving circuit 103, and a shunt circuit 104, wherein an output end of the forced shunt signal shielding circuit 101 is connected to input ends of the forced shunt signal generating circuit 102 and the shunt driving circuit 103, and output ends of the forced shunt signal generating circuit 102 and the shunt driving circuit 103 are connected to an input end of the shunt circuit 104.
The shunt circuit 104 is used for shunting and adjusting the output power of the solar cell array when the bus voltage rises to a set value, so as to ensure the stability of the bus voltage.
The shunt drive circuit 103 provides a drive signal for shunt regulation of the shunt circuit.
When the satellite does not need the output power of the solar cell array to supply power to the satellite bus, the forced shunt signal shielding circuit 101 is in an enabling state, the shunt driving circuit 103 is disabled, and the forced shunt signal generating circuit 102 outputs a forced shunt signal, so that the shunt circuit 104 is in a full shunt state.
When the satellite needs to output power from the solar cell array to supply power to the satellite bus, the forced shunt signal shielding circuit 101 is in a disabled state, the shunt driving circuit 103 is enabled, and the forced shunt signal generating circuit 102 is shielded.
Referring to fig. 2, the forced shunt signal shielding circuit 101 includes a relay K7, referring to fig. 4, the shunt driving circuit includes 103 a comparator U1, a transistor V1, a transistor V2, a transistor V3, and a transistor V4, the transistor V1 and the transistor V2 form a push-pull circuit, a positive input terminal of the comparator U1 is connected to a divided voltage VBUS-F of the bus voltage, a negative input terminal of the comparator U1 is connected to a shunt reference Vref, an output terminal of the comparator U1 is connected to the push-pull circuit, a base of the transistor V3 is connected to the relay K7, a collector of the transistor V3 is grounded, an emitter of the transistor V3 is connected to a collector of the transistor V2, a base of the transistor V4 is connected to a shunt enable/disable command signal terminal, a collector of the transistor V4 is connected between the comparator U1 and the push-pull circuit, and an emitter of the transistor V4 is grounded.
As shown in fig. 2, the forced shunt signal shielding circuit 101 further includes a resistor R12, a resistor R13, and a capacitor C3, the pin 1 and the pin 2 of the relay K7 are respectively connected to the base of the transistor V3, the pin 3 of the relay K7 is connected to one end of the resistor R12, the other end of the resistor R12 is respectively connected to one ends of the resistor R13 and the capacitor C3, the other ends of the resistor R13 and the capacitor C3 are grounded, the other end of the resistor R12 is connected to a relay state signal terminal collected on the satellite, the pin 7 and the pin 9 of the relay K7 are respectively connected to the bus voltage VBUS, and the pin 8 of the relay K7 is connected to a forced shunt enable command signal terminal.
As shown in fig. 4, the base of the transistor V1 and the base of the transistor V2 are respectively connected to the output terminal of the comparator U1, the emitter of the transistor V1 and the emitter of the transistor V2 are respectively connected to the input terminal of the shunt circuit 104, and the collector of the transistor V1 is connected to the bus voltage VBUS.
As shown in fig. 5, the shunt circuit 104 includes a resistor R5, a resistor R6, a shunt transistor V5, and a shunt transistor V6, a gate of the shunt transistor V6 is connected to one end of the resistor R6, another end of the resistor R6 is connected to an emitter of the transistor V1 and an emitter of the transistor V2, a source of the shunt transistor V6 is grounded, a drain of the shunt transistor V6 is connected to a source of the shunt transistor V5, a gate of the shunt transistor V5 is connected to one end of the resistor R5, another end of the resistor R5 is connected to an emitter of the transistor V1 and an emitter of the transistor V2, and a drain of the shunt transistor V5 is connected to the solar cell array SAS. The solar cell array SAS supplies the bus voltage VBUS via the isolation diode D2.
As shown in fig. 3, the forced shunting signal generating circuit 102 includes a transistor V7, a resistor R10, and a diode D1, wherein a base of the transistor V7 is connected to a shunting enable/disable command signal terminal, a collector of the transistor V7 is grounded, an emitter of the transistor V7 is connected to pin 1 and pin 2 of the relay K7, an emitter of the transistor V7 is connected to one end of the resistor R10, the other end of the resistor R10 is connected to the battery VBAT, an emitter of the transistor V7 is connected to an anode of the diode D1, and a cathode of the diode D1 is connected to an emitter of the transistor V1 and an emitter of the transistor V2, respectively.
As shown in fig. 3, the forced shunting signal generating circuit 102 further includes a resistor R15, a capacitor C4, a resistor R14, a capacitor C2, and a resistor R11, wherein one end of the resistor R15 is connected to the base of the transistor V7, the other end of the resistor R15 is grounded, one end of the capacitor C4 is connected to the base of the transistor V7, the other end of the capacitor C4 is grounded, one end of the resistor R14 is connected to the base of the transistor V7, the other end of the resistor R14 is connected to the emitter of the transistor V7, one end of the capacitor C4 is connected to the emitter of the transistor V7, the other end of the capacitor C4 is grounded, one end of the resistor R11 is connected to the emitter of the transistor V7, and the other end of the resistor R11 is grounded.
The operation process of the solar cell array shunt regulation system comprises the following steps:
s1, during the normal operation of the spacecraft on the rail, a shunt control circuit works normally, a relay K7 is in a forced shunt forbidden state, forced shunt signals are shielded, K7_ TM is a relay state collected on the satellite, V14_ B is low level, a PNP triode V3 is in a conducting state, a triode V4 is in a disconnected state normally, V4A _ Q is generated by a push-pull circuit, the push-pull circuit is composed of a triode V1 and a triode V2, the positive input end of a comparator U1 is connected to the divided voltage of bus voltage, the negative input end of the comparator U1 is connected to a shunt reference Vref, signals of the positive input end and the negative input end of the comparator are compared, and the high/low signals are output to control the push-pull circuit. The shunt transistor V5 and the shunt transistor V6 are controlled to be switched on or switched off by the V4A _ Q signal, so that a shunt regulation function is realized, the solar cell array SAS supplies power to the bus voltage VBUS through the isolation diode D2, and the stability of the bus voltage is ensured.
S2, if the output of the comparator circuit is continuously high level fault, the push-pull circuit continuously outputs high level, the shunt transistor V5 and the shunt transistor V6 are in a normally-on state, if the output power of the solar cell array is limited, the task safety of the whole satellite can be influenced, when the voltage of a bus is monitored to be abnormally increased on the satellite, a shunt enable 1 instruction can be sent, the triode V4 is switched on, the circuit enters a shunt state, when the voltage of the bus is lower than a certain value, a shunt forbid 1 instruction is sent, the triode V4 is switched off, the circuit enters a non-shunt state, and therefore the voltage stability of the bus is guaranteed.
S3, if the comparator circuit has a fault of continuously being at a low level, or the push-pull circuit has a fault of continuously outputting the low level, the shunt transistor V5 and the shunt transistor V6 are in a normally-off state, the bus voltage will continuously rise, the safety of the whole satellite is affected, a forced shunt enabling instruction can be sent firstly, so that the relay K7 removes the shielding effect on forced shunt signals, the V14_ B is changed from the low level to the high level, the PNP triode V3 is in an off state, and the V14A _ Q is also changed from the low level to the high level, so that the shunt transistor V5 and the shunt transistor V6 are both in an on state, and the output power of the solar cell array is shunted. When the bus voltage is lower than a certain value, the PNP triode V7 can be in a conducting state by sending a 'shunt forbidding 2' instruction, and the V14_ B and the V14A _ Q are changed from a high level to a low level, so that the shunt transistor V5 and the shunt transistor V6 are in a disconnected state; when the bus voltage rises to a certain value again, by sending a "shunt enable 2" command, V14_ B and V14A _ Q will change from low level to high level, so that both shunt transistor V5 and shunt transistor V6 are in an on state. Thereby ensuring the stability of the bus voltage.
S4, in the design, the forced shunt signal generating circuit obtains electricity from the storage battery pack, the reliability of the circuit is guaranteed, meanwhile, if the spacecraft has the power-off launching requirement, the relay K7 can be set to be in a forced shunt enabling state before launching, V14_ B and V14A _ Q are both high levels, the triode V3 is in a disconnection state, and when the power of the solar cell array is output, the current can be shunted through the shunt transistor V5 and the shunt transistor V6, and the power cannot be supplied to the bus voltage VBUS.
The invention is simple and reliable, has flexible configuration, eliminates the influence of short-circuit fault and open-circuit fault on the bus, and can be set into a charged emission mode and a non-charged emission mode according to the task requirement of the spacecraft. The solar cell array shunt regulation system is simple in circuit and flexible in configuration, can be suitable for any solar cell array output power regulation topological structure, enhances the reliability of the solar cell array shunt regulation circuit, and solves the influence of short circuit and open circuit faults; for the spacecraft without electric launch, the problem of electromagnetic compatibility does not exist between the spacecraft and the carrier rocket, so that the electromagnetic compatibility test between the satellite and the rocket is not required to be carried out, the development period is shortened, and the test cost is reduced.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (10)
1. The utility model provides a high reliable solar cell array reposition of redundant personnel governing system which characterized in that: the method comprises the following steps:
a shunt circuit: when the voltage of the power supply bus is increased to a set value, the output power of the solar cell array is subjected to shunt regulation;
shunt drive circuit: providing a drive signal for shunt regulation of the shunt circuit;
forced shunt signal shielding circuit: when the satellite does not need the output power of the solar cell array to supply power to the satellite bus, the satellite is in an enabling state, and the execution of the shunt driving circuit is forbidden; when the satellite needs the solar cell array output power to supply power to the satellite bus, the satellite is in a forbidden state, and the execution of the shunt driving circuit is enabled;
forced shunt signal generating circuit: outputting a forced shunting signal and enabling a shunting circuit to be in a full shunting state;
the output end of the forced shunt signal shielding circuit is respectively connected with the input ends of the forced shunt signal generating circuit and the shunt driving circuit, and the output ends of the forced shunt signal generating circuit and the shunt driving circuit are respectively connected with the input end of the shunt circuit.
2. The high-reliability solar cell array shunt regulation system according to claim 1, wherein: the forced shunting signal shielding circuit comprises a relay K7, the shunting driving circuit comprises a comparator U1, a triode V1, a triode V2, a triode V3 and a triode V4, the triode V1 and the triode V2 form a push-pull circuit, the positive input end of the comparator U1 is connected to the divided voltage VBUS-F of the bus voltage, the negative input end of the comparator U1 is connected to a shunt reference Vref, the output end of the comparator U1 is connected with the push-pull circuit, the base electrode of the triode V3 is connected with the relay K7, the collector electrode of the triode V3 is grounded, the emitter of the triode V3 is connected with the collector of the triode V2, the base of the triode V4 is connected with a shunt enable/disable command signal end, the collector of the triode V4 is connected between the comparator U1 and the push-pull circuit, and the emitter of the triode V4 is grounded.
3. The high-reliability solar cell array shunt regulation system according to claim 2, wherein: force reposition of redundant personnel signal shield circuit still includes resistance R12, resistance R13 and electric capacity C3, relay K7's pin 1 and pin 2 respectively with triode V3's base is connected, relay K7's pin 3 with resistance R12's one end is connected, resistance R12's the other end respectively with resistance R13, electric capacity C3's one end are connected, resistance R13, electric capacity C3's other end ground connection, resistance R12's the other end inserts the relay state signal end of gathering on the star, relay K7's pin 7 and pin 9 connect bus voltage VBUS respectively, relay K7's pin 8 connects into forces reposition of redundant personnel to enable the command signal end.
4. The high-reliability solar cell array shunt regulation system according to claim 2, wherein: the base electrode of the triode V1 and the base electrode of the triode V2 are respectively connected with the output end of the comparator U1, the emitter electrode of the triode V1 and the emitter electrode of the triode V2 are respectively connected with the input end of the shunt circuit, and the collector electrode of the triode V1 is connected with the bus voltage VBUS.
5. The high-reliability solar cell array shunt regulation system according to claim 2, wherein: the shunt circuit comprises a resistor R5, a resistor R6, a shunt transistor V5 and a shunt transistor V6, the gate of the shunt transistor V6 is connected with one end of a resistor R6, the other end of the resistor R6 is connected with the emitter of the triode V1 and the emitter of the triode V2 respectively, the source of the shunt transistor V6 is grounded, the drain of the shunt transistor V6 is connected with the source of the shunt transistor V5, the gate of the shunt transistor V5 is connected with one end of the resistor R5, the other end of the resistor R5 is connected with the emitter of the triode V1 and the emitter of the triode V2 respectively, and the drain of the shunt transistor V5 is connected to the solar cell array SAS.
6. The high-reliability solar cell array shunt regulation system according to claim 5, wherein: the solar cell array SAS supplies the bus voltage VBUS via the isolation diode D2.
7. The high-reliability solar cell array shunt regulation system according to claim 2, wherein: the forced shunting signal generating circuit comprises a triode V7, a resistor R10 and a diode D1, wherein the base electrode of the triode V7 is connected to a shunting enable/disable command signal end, the collector electrode of the triode V7 is grounded, the emitter electrode of the triode V7 is connected with a pin 1 and a pin 2 of the relay K7, the emitter electrode of the triode V7 is connected with one end of the resistor R10, the other end of the resistor R10 is connected with a storage battery pack VBAT, the emitter electrode of the triode V7 is connected with the anode of the diode D1, and the cathode of the diode D1 is respectively connected with the emitter electrode of the triode V1 and the emitter electrode of the triode V2.
8. The high reliability solar array shunt regulation system of claim 7, wherein: the forced shunting signal generating circuit further comprises a resistor R15, a capacitor C4, a resistor R14, a capacitor C2 and a resistor R11, wherein one end of the resistor R15 is connected with the base of the triode V7, the other end of the resistor R15 is grounded, one end of the capacitor C4 is connected with the base of the triode V7, the other end of the capacitor C4 is grounded, one end of the resistor R14 is connected with the base of the triode V7, the other end of the resistor R14 is connected with the emitter of the triode V7, one end of the capacitor C4 is connected with the emitter of the triode V7, the other end of the capacitor C4 is grounded, one end of the resistor R11 is connected with the emitter of the triode V7, and the other end of the resistor R11 is grounded.
9. A high-reliability solar cell array shunt regulation method is characterized by comprising the following steps: the highly reliable solar cell array shunt regulation system of any one of claims 1 to 8 is adopted to carry out the following processes:
s1, during the on-orbit normal operation of the spacecraft, a shunt driving circuit works normally, a relay K7 is in a forced shunt forbidden state, a forced shunt signal is shielded, an input signal K7_ TM of a relay K7 is in a relay state acquired on the satellite, an output signal of the relay K7 is V14_ B, at the moment, the V14_ B signal is low level, the triode V3 is in a conducting state, the triode V4 is in a disconnected state in a normal state, the V4A _ Q signal is an output signal of a push-pull circuit composed of the triode V1 and the triode V2, the positive input end of the comparator U1 is connected to the divided voltage VBUS-F of the bus voltage, the negative input end of the comparator U1 is connected to the shunt reference Vref, the signals of the positive input end and the negative input end are compared to output a high/low signal to control the push-pull circuit, the V4A _ Q signal controls the shunt transistor V5 and the shunt transistor V6 to be connected or disconnected, and the solar cell array SAS supplies power to the bus voltage VBUS through the isolation diode D2.
10. The high-reliability solar cell array shunt regulation method according to claim 9, wherein: the method also comprises the following steps:
s2, if the output of the comparator U1 is continuously high-level fault, the push-pull circuit continuously outputs high level, the shunt transistor V5 and the shunt transistor V6 are in a normally-on state, if the output power of the solar cell array SAS is limited, when the bus voltage VBUS monitored on the satellite is abnormally increased, the shunt driving circuit enters a shunt state by sending a shunt enabling instruction to the triode V4 and conducting the triode V4, and when the bus voltage VBUS is lower than a set value, the shunt prohibiting instruction is sent to the triode V4 and the triode V4 is disconnected, so that the shunt driving circuit enters a non-shunt state;
s3, if the comparator U1 has a fault of continuously being at a low level, or the push-pull circuit has a fault of continuously outputting the low level, the shunt transistor V5 and the shunt transistor V6 are in a normally-off state, the bus voltage VBUS will continuously rise, a forced shunt enabling instruction is sent to the relay K7 firstly, so that the relay K7 relieves the shielding effect on forced shunt signals, the V14_ B signal is changed from the low level to the high level, the triode V3 is in an off state, the V14A _ Q signal is also changed from the low level to the high level, the shunt transistor V5 and the shunt transistor V6 are both in an on state, and the output power of the solar cell array SAS is shunted; when the bus voltage VBUS is lower than the set value, by sending a shunt prohibition instruction to the transistor V7, the transistor V7 is in a conducting state, and the V14_ B signal and the V14A _ Q signal change from a high level to a low level, so that the shunt transistor V5 and the shunt transistor V6 are both in a disconnected state; when the bus voltage VBUS rises to the set value again, the shunt transistor V5 and the shunt transistor V6 are both in an on state by sending a shunt enable instruction to the transistor V7, so that the V14_ B signal and the V14A _ Q signal change from a low level to a high level;
s4, if the spacecraft is launched in a power-off state, the forced shunt signal generating circuit gets power from the storage battery pack VBAT, the relay K7 is set to be in a forced shunt enabling state before launching, the V14_ B signal and the V14A _ Q signal are both high-level, the triode V3 is in a disconnection state, and when the solar cell array SAS power is output, the power is shunted through the shunt transistor V5 and the shunt transistor V6.
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| JPH11150887A (en) * | 1997-11-18 | 1999-06-02 | Nec Corp | Bus power unit for mounting on artificial satellite and method for controlling shunt current |
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| CN106100096B (en) * | 2016-06-23 | 2018-08-21 | 航天东方红卫星有限公司 | A kind of micro-nano satellite low-voltage high-efficiency power-supply system |
| CN107959279B (en) * | 2017-11-29 | 2019-06-25 | 上海空间电源研究所 | A kind of solar battery array soft-start control system and its control method |
| CN109696925A (en) * | 2018-12-24 | 2019-04-30 | 航天东方红卫星有限公司 | A kind of closed loop control method of control solar battery array output energy balance |
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