CN111697681A - Multi-path charging shunt control system and method for spacecraft - Google Patents
Multi-path charging shunt control system and method for spacecraft Download PDFInfo
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- CN111697681A CN111697681A CN202010633613.4A CN202010633613A CN111697681A CN 111697681 A CN111697681 A CN 111697681A CN 202010633613 A CN202010633613 A CN 202010633613A CN 111697681 A CN111697681 A CN 111697681A
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0068—Battery or charger load switching, e.g. concurrent charging and load supply
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
- Y02E10/56—Power conversion systems, e.g. maximum power point trackers
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- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses a multi-path charging shunt control system for a spacecraft, which comprises: charging a solar array; the first end of the charging switch is connected with the positive electrode of the charging solar array; the first end of the load is connected with the second end of the charging change-over switch, and the second end of the load is connected with the negative electrode of the charging solar array; the positive electrode of the storage battery pack is connected with the third end of the charging switch, and the negative electrode of the storage battery pack is connected with the negative electrode of the charging solar array; the first end of the discharging circuit is connected with the positive electrode of the storage battery pack, and the second end of the discharging circuit is connected with the first end of the load; and the first end of the charging shunt control circuit is connected with the positive electrode of the charging solar array, the second end of the charging shunt control circuit is connected with the negative electrode of the charging solar array, the third end of the charging shunt control circuit is connected with a load, and the fourth end of the charging shunt control circuit is connected with the storage battery pack. The invention solves the problems of complex structure and high discharge loss of the traditional circuit, and the cost is reduced, the discharge utilization rate is ensured, the loss is reduced, and the energy utilization rate and the performance of the spacecraft are improved by jointly charging the load through the charging solar array and the storage battery.
Description
Technical Field
The invention relates to the technical field of space power supplies, in particular to a multi-path charging shunt control system and a multi-path charging shunt control method for a spacecraft.
Background
The advanced idea of space power supply system design is miniaturization and integration. Meanwhile, in recent years, sequential switch shunt series regulator (S) is mostly adopted in power supply system of spacecraft4R) type circuits, which are complex in structure, numerous in devices, large in size, heavy in weight, and high in cost.
At the same time, conventional S4The R-type circuit has high discharge efficiency loss, poor technical performance and poor flexibility, the solar cell array has low energy utilization rate, and the performance and the benefit of the spacecraft of the R-type circuit are required to be improved.
Disclosure of Invention
The invention aims to provide a multi-path charging shunt control system for a spacecraft. The system is aimed at solving the conventional S4The R-type circuit has the advantages that the structure is complex, the discharging efficiency loss is high, the charging is carried out by the aid of the charging solar array and the storage battery pack through the multi-path charging shunt control circuit and the charging switch, devices are saved, cost is reduced, discharging utilization rate is guaranteed, discharging loss is reduced, and energy utilization rate and performance of the spacecraft are improved.
In order to achieve the purpose, the invention provides a multi-path charging shunt control system for a spacecraft, which comprises a charging solar array, a charging selector switch, a load, a storage battery pack, a discharging circuit and a charging shunt control circuit, wherein the charging solar array is connected with the charging selector switch; the charging solar array converts solar energy into electric energy; the first end of the charging switch is connected with the positive electrode of the charging solar array; the first end of the load is connected with the second end of the charging change-over switch, and the second end of the load is connected with the negative electrode of the charging solar array to form a first loop; the first loop is connected through switching the charging switch, and the charging solar array supplies power to the load; the positive electrode of the storage battery pack is connected with the third end of the charging switch, and the negative electrode of the storage battery pack is connected with the negative electrode of the charging solar array to form a second loop; the second loop is switched on by switching the charging selector switch, and the charging solar array supplies power to the storage battery pack; the first end of the discharge circuit is connected with the positive electrode of the storage battery pack, the second end of the discharge circuit is connected with the first end of the load, the storage battery pack, the discharge circuit and the load form a third loop, and the storage battery pack supplies power to the load through the discharge circuit; the first end of the charging shunt control circuit is connected with the anode of the charging solar array, the second end of the charging shunt control circuit is connected with the cathode of the charging solar array, and the charging shunt control circuit and the charging solar array form a fourth loop; and the third end of the charging shunt control circuit is connected with the load, the fourth end of the charging shunt control circuit is connected with the storage battery pack, and the power supply loop of the charging solar array is judged according to the voltage division of the load and the storage battery pack to output the electric energy of the charging solar array.
Most preferably, the charging shunt control circuit comprises a switching tube, an operational amplifier, a triangular wave transmitter and a PI (proportional integral) signal device; the first end of the switch tube is connected with the anode of the charging solar array, and the second end of the switch tube is connected with the cathode of the charging solar array; the first end of the operational amplifier is connected with the third end of the switching tube, and the second end of the operational amplifier is connected with the triangular wave transmitter; the triangular wave transmitter is used for transmitting a reference signal; the first end of the PI annunciator is connected with the third end of the operational amplifier, the second end of the PI annunciator is connected with the load, and the third end of the PI annunciator is connected with the storage battery pack and used for respectively acquiring the divided voltage of the load and the divided voltage of the storage battery pack so as to obtain a PI signal of the charging solar array; the operational amplifier compares the PI signal with a reference signal to control the on-off of the switching tube.
Most preferably, the PI signal device comprises a signal switch, a bus reference signal device and a charging reference signal device; the first end of the signal selector switch is connected with the third end of the operational amplifier; the first end of the bus reference signal device is connected with the second end of the signal switch, and the second end of the bus reference signal device is connected with the load and used for acquiring the divided voltage of the load; the first end of the charging reference signal device is connected with the third end of the signal transfer switch, and the second end of the charging reference signal device is connected with the storage battery pack and used for acquiring the divided voltage of the storage battery pack; the signal switch switches the bus reference signal device and the charging reference signal device respectively according to the voltage division of the load and the voltage division of the storage battery pack, and therefore the PI signal of the charging solar array is obtained.
Most preferably, a diode is further arranged between the charging solar array and the charging change-over switch.
Most preferably, the number of the charging solar arrays is several, and the number of the charging shunt control circuits and the number of the diodes are several correspondingly.
Most preferably, a charging switch is further arranged between the charging switch and the storage battery pack and used for controlling the on-off of the second loop.
Most preferably, a discharge switch is further arranged between the storage battery pack and the discharge circuit and used for controlling the on-off of the third loop.
Most preferably, the charge changeover switch is provided in plurality.
The invention also provides a multipath charging and shunting control method for the spacecraft, which is realized based on a multipath charging and shunting control system for the spacecraft, and comprises the following steps:
step 1: the charging shunt control circuit respectively acquires the partial voltage of the load and the storage battery pack and judges whether the partial voltage of the load is smaller than a reference signal of the charging solar array for the first time;
step 2: if the voltage of the load is lower than the reference signal, the signal transfer switch is switched to the bus reference signal device, the fourth loop is disconnected, the first loop and the third loop are connected, and the charging solar array and the storage battery pack supply power to the load at the same time;
and step 3: if not, namely the divided voltage of the load is greater than the rated voltage, the signal switch is switched to the charging reference signal device, and whether the divided voltage of the storage battery pack is less than the reference signal or not is judged for the second time;
and 4, step 4: if yes, namely the divided voltage of the load is greater than the rated voltage, and the divided voltage of the storage battery pack is smaller than the reference signal, the fourth loop is disconnected, the second loop is connected, and the charging solar array supplies power to the storage battery pack;
and 5: if not, namely the divided voltage of the load and the storage battery pack is larger than the reference signal, the fourth loop is conducted, and the electric energy of the charging solar array is directly shunted.
Most preferably, the charging shunt control circuit respectively obtains the voltage division of the load and the storage battery pack through a bus reference signal device and a charging reference signal device.
By applying the invention, the problem of the traditional S is solved4The R-type circuit has the advantages that the structure is complex, the discharging efficiency loss is high, the charging is carried out by adopting a charging solar array and a storage battery group together through arranging a multi-path charging shunt control circuit and a charging switch, devices are saved, the cost is reduced, the discharging utilization rate is ensured, the discharging loss is reduced, and the energy utilization rate and the performance of a spacecraft are improved.
Compared with the prior art, the invention has the following beneficial effects:
1. the multi-path charging shunt control system provided by the invention has the advantages of simple structure, easiness in implementation, high technical performance, strong flexibility, device saving, volume reduction and cost reduction.
2. Compared with the traditional S, the multi-path charging shunt control system provided by the invention4The R-type circuit avoids the loss of discharge efficiency and improves the energy utilization rate and the performance of the spacecraft.
Drawings
Fig. 1 is a schematic structural diagram of a multi-path charging shunt control system provided by the present invention.
Detailed Description
The invention will be further described by the following specific examples in conjunction with the drawings, which are provided for illustration only and are not intended to limit the scope of the invention.
The invention relates to a multi-path charging shunt control system for a spacecraft, which comprises a charging solar array 1, a charging selector switch K, a load 2, a storage battery pack 3, a discharging circuit 4 and a charging shunt control circuit 5 as shown in figure 1.
Wherein, the charging solar array 1 converts solar energy into electric energy; the first end of the charging change-over switch K is connected with the positive electrode of the charging solar array 1; the first end of the load 2 is connected with the second end of the charging change-over switch K, and the second end of the load is connected with the negative electrode of the charging sun array 1 to form a first loop; the first loop is switched on by switching the charging change-over switch K, and the charging solar array 1 supplies power to the load 2.
The positive electrode of the storage battery pack 3 is connected with the third end of the charging selector switch K, and the negative electrode of the storage battery pack is connected with the negative electrode of the charging solar array 1 to form a second loop; the second loop is switched on by switching the charging change-over switch K, and the charging solar array 1 supplies power to the storage battery pack 3.
The first end of the discharge circuit 4 is connected with the anode of the storage battery pack 3, the second end is connected with the first end of the load 1, the storage battery pack 3, the discharge circuit 4 and the load 2 form a third loop, and the storage battery pack 3 supplies power to the load 2 through the discharge circuit 4.
The first end of the charging shunt control circuit 5 is connected with the anode of the charging solar array 1, the second end of the charging shunt control circuit is connected with the cathode of the charging solar array 1, and then the charging shunt control circuit 5 and the charging solar array 1 form a fourth loop; and the third end of the charging shunt control circuit 5 is connected with the load 2, the fourth end is connected with the storage battery 3, and the power supply loop of the charging solar array 1 is judged according to the voltage division of the load 2 and the storage battery 3 so as to output the electric energy of the charging solar array 1.
In the present embodiment, the charge shunt control circuit 5 includes a switching tube M, an operational amplifier C, a triangular wave transmitter 6, and a PI signal device.
The first end of the switching tube M is connected with the anode of the charging solar array 1, and the second end of the switching tube M is connected with the cathode of the charging solar array 1; the first end of the operational amplifier C is connected with the third end of the switching tube M, and the second end of the operational amplifier C is connected with the triangular wave transmitter 6; the triangular wave transmitter is used for transmitting a reference signal; the first end of the PI annunciator is connected with the third end of the operational amplifier C, the second end of the PI annunciator is connected with the load 2, and the third end of the PI annunciator is connected with the storage battery 3 and used for respectively obtaining the divided voltage of the load 2 and the divided voltage of the storage battery 3 so as to obtain the PI signal of the charging solar array 1.
The PI signal device comprises a signal switch S, a bus reference signal device 7 and a charging reference signal device 8; the first end of the signal switch S is connected with the third end of the operational amplifier C; the first end of the bus reference signal device 7 is connected with the second end of the signal switch S, and the second end is connected with the load 2, and is used for acquiring the divided voltage of the load 2; the first end of the charging reference signal device 8 is connected with the third end of the signal switch S, and the second end is connected with the storage battery 3 and used for acquiring the divided voltage of the storage battery 3; the signal switch S respectively switches the bus reference signal device 7 and the charging reference signal device 8 according to the divided voltage of the load 2 and the divided voltage of the storage battery pack 3, so as to obtain a PI signal of the charging solar array 1; the operational amplifier C compares the PI signal with a reference signal to control the on-off of the switch tube M.
A diode D is also arranged between the charging solar array 1 and the charging change-over switch K; a charging switch K is arranged between the charging switch K and the storage battery 3CThe second loop is used for controlling the on-off of the second loop; a discharge switch K is also arranged between the storage battery 3 and the discharge circuit 4FAnd the control circuit is used for controlling the on-off of the third loop.
In the present embodiment, the charge switch KCThe two parallel relay switches control the on-off of the second loop; discharge switch KFThe on-off of the third loop is controlled by two parallel relay switches.
If the number of the charging solar arrays 1 is n, the number of the charging shunt control circuits 5 and the number of the diodes D are n.
M charging change-over switches K are provided; in this embodiment, when the number of the charging shunt circuits 5 is large, one charging switch K may be shared by two paths to save the number, that is, when the number of the charging shunt control circuits 5 is n, the number of the charging switches m is n/2.
The storage battery 3 is a lithium ion storage battery with single bodies connected in series.
The invention also provides a multipath charging and shunting control method for the spacecraft, which is realized based on a multipath charging and shunting control system for the spacecraft, and comprises the following steps:
step 1: the charging shunt control circuit 5 respectively obtains the divided voltage of the load 2 and the storage battery 3 through the bus reference signal device 7 and the charging reference signal device 8, and judges whether the divided voltage of the load 2 is smaller than the reference signal transmitted by the triangular wave transmitter 6 for the first time through the operational amplifier C.
Step 2: if the voltage of the load 2 is smaller than the reference signal transmitted by the triangular wave transmitter 6, the signal switch S switches the bus reference signal device 7 for acquiring the voltage of the load 2, the switch tube M is disconnected, the fourth loop is disconnected, the charging switch K is switched into the first loop, and the charging switch K is switched into the second loopCSwitch K for disconnection and dischargeFAnd when the circuit is closed, the first loop and the third loop are conducted, and the charging solar array 1 and the storage battery pack 3 supply power to the load 2 at the same time.
And step 3: if not, namely the divided voltage of the load 2 is greater than the reference signal transmitted by the triangular wave transmitter 6, at the moment, the load 2 does not need to charge the solar array 1 to provide electric energy, and the signal switch S is switched to a charging reference signal device 8 for acquiring the divided voltage of the storage battery 3; in order to avoid the waste of the electric energy for charging the solar array 1, whether the divided voltage of the storage battery 3 is smaller than the reference signal transmitted by the triangular wave transmitter 6 is judged for the second time through the operational amplifier C.
And 4, step 4: if the voltage is greater than the reference signal transmitted by the triangular wave transmitter 6, namely the divided voltage of the load 2 is greater than the reference signal transmitted by the triangular wave transmitter 6, and the divided voltage of the storage battery 3 is less than the reference signal transmitted by the triangular wave transmitter 6, the switch tube M is disconnected, the fourth loop is disconnected, the charging switch K is switched to the second loop, and the charging switch K is switched to the third loopCAnd when the circuit is closed, the second loop is conducted, and the charging solar array 1 transmits the electric energy to the storage battery pack 3 to supply power to the storage battery pack 3.
And 5: if not, namely the divided voltage of the load 2 and the storage battery 3 is greater than the reference signal transmitted by the triangular wave transmitter 6, at the moment, the load 2 and the storage battery 3 do not need to charge the solar array 1 to provide electric energy, the switch tube M is closed, the fourth loop is conducted, and the electric energy of the charging solar array 1 is directly divided.
The working principle of the invention is as follows:
the charging shunt control circuit respectively obtains the voltage division of the load and the storage battery pack, and judges whether the voltage division of the load is smaller than a reference signal transmitted by the triangular wave transmitter for the first time; if so, namely the divided voltage of the load is smaller than the reference signal, the fourth loop is disconnected, the first loop and the third loop are conducted, and the charging solar array and the storage battery pack supply power to the load at the same time; if not, namely the divided voltage of the load is greater than the reference signal, judging whether the divided voltage of the storage battery pack is less than the reference signal for the second time; if yes, namely the divided voltage of the load is greater than the reference signal, and the divided voltage of the storage battery pack is smaller than the reference signal, the fourth loop is disconnected, the second loop is connected, and the charging solar array supplies power to the storage battery pack; if not, namely the divided voltage of the load and the storage battery pack is larger than the reference signal, the fourth loop is conducted, and the electric energy of the charging solar array is directly shunted.
In conclusion, the multi-path charging and shunting control system for the spacecraft solves the problem of the traditional S4The R-type circuit has the advantages that the structure is complex, the discharging efficiency loss is high, the charging is carried out by the aid of the charging solar array and the storage battery pack through the multi-path charging shunt control circuit and the charging switch, devices are saved, cost is reduced, discharging utilization rate is guaranteed, discharging loss is reduced, and energy utilization rate and spacecraft performance are improved.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.
Claims (10)
1. A multi-path charging shunt control system for a spacecraft, comprising:
charging the solar array, and converting solar energy into electric energy;
a first end of the charging change-over switch is connected with the positive electrode of the charging solar array;
the first end of the load is connected with the second end of the charging change-over switch, and the second end of the load is connected with the negative electrode of the charging solar array to form a first loop; switching on the first loop by switching the charging switch, wherein the charging solar array supplies power to the load;
the anode of the storage battery pack is connected with the third end of the charging change-over switch, and the cathode of the storage battery pack is connected with the cathode of the charging solar array to form a second loop; the second loop is switched on by switching a charging selector switch, and the charging solar array supplies power to the storage battery pack;
the first end of the discharging circuit is connected with the anode of the storage battery pack, the second end of the discharging circuit is connected with the first end of the load, the storage battery pack, the discharging circuit and the load form a third loop, and the storage battery pack supplies power to the load through the discharging circuit;
the first end of the charging shunt control circuit is connected with the anode of the charging solar array, the second end of the charging shunt control circuit is connected with the cathode of the charging solar array, and the charging shunt control circuit and the charging solar array form a fourth loop; and the third end of the charging shunt control circuit is connected with the load, the fourth end of the charging shunt control circuit is connected with the storage battery pack, and the power supply loop of the charging solar array is judged according to the voltage division of the load and the storage battery pack so as to output the electric energy of the charging solar array.
2. The multi-path charging shunt control system for a spacecraft of claim 1, wherein the charging shunt control circuitry comprises:
the first end of the switch tube is connected with the anode of the charging solar array, and the second end of the switch tube is connected with the cathode of the charging solar array;
the first end of the operational amplifier is connected with the third end of the switching tube, and the second end of the operational amplifier is connected with a triangular wave transmitter; the triangular wave transmitter is used for transmitting a reference signal;
a first end of the PI signal generator is connected with a third end of the operational amplifier, a second end of the PI signal generator is connected with the load, and a third end of the PI signal generator is connected with the storage battery pack and used for respectively obtaining the divided voltage of the load and the divided voltage of the storage battery pack so as to obtain a PI signal of the charging solar array;
and the operational amplifier compares the PI signal with the reference signal to calculate so as to control the opening and closing of the switching tube.
3. The multi-path charging shunt control system for a spacecraft of claim 2, wherein said PI signaler comprises:
a first end of the signal switch is connected with a third end of the operational amplifier;
a first end of the bus reference signal device is connected with a second end of the signal switch, and a second end of the bus reference signal device is connected with the load and is used for acquiring the divided voltage of the load;
a first end of the charging reference signal device is connected with a third end of the signal transfer switch, and a second end of the charging reference signal device is connected with the storage battery pack and used for acquiring the divided voltage of the storage battery pack;
and the signal switch switches the bus reference signal device and the charging reference signal device respectively according to the divided voltage of the load and the divided voltage of the storage battery pack, so that a PI signal of the charging solar array is obtained.
4. The multi-path charging shunt control system for a spacecraft of claim 1, wherein a diode is further disposed between the charging solar array and the charging diverter switch.
5. The multi-path charging shunt control system for a spacecraft of claim 4, wherein if the number of the charging solar arrays is several, the number of the charging shunt control circuits and the diodes is several.
6. The multi-path charging shunt control system for the spacecraft of claim 1, wherein a charging switch is further arranged between the charging switch and the storage battery pack and used for controlling the on-off of the second loop.
7. The multi-path charging shunt control system for the spacecraft of claim 1, wherein a discharging switch is further arranged between the storage battery pack and the discharging circuit and used for controlling the on-off of the third loop.
8. The multi-path charging shunt control system for a spacecraft of claim 1, wherein the charging switch is a plurality of switches.
9. A multipath charging and shunting control method for a spacecraft, which is implemented based on the multipath charging and shunting control system for the spacecraft according to any one of claims 1 to 8, and comprises the following steps:
step 1: the charging shunt control circuit respectively obtains the voltage division of the load and the storage battery pack and judges whether the voltage division of the load is smaller than the reference signal for the first time;
step 2: if so, namely the divided voltage of the load is smaller than the reference signal, the signal change-over switch is switched to the bus reference signal device, the fourth loop is disconnected, the first loop and the third loop are connected, and the charging solar array and the storage battery pack supply power to the load at the same time;
and step 3: if not, namely the divided voltage of the load is greater than the reference signal, and the signal switch is switched to the charging reference signal device, judging whether the divided voltage of the storage battery pack is less than the rated voltage for the second time;
and 4, step 4: if so, namely the divided voltage of the load is greater than the reference signal, and the divided voltage of the storage battery pack is less than the reference signal, the fourth loop is disconnected, the second loop is connected, and the charging solar array supplies power to the storage battery pack;
and 5: if not, namely the divided voltage of the load and the storage battery pack is greater than the reference signal, the fourth loop is conducted, and the electric energy of the charging solar array is directly divided.
10. A multi-path charging shunt control method for a spacecraft as claimed in claim 9, wherein said charging shunt control circuit obtains the divided voltages of said load and said battery pack through said bus bar reference signal device and said charging reference signal device, respectively.
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| CN114285132A (en) * | 2021-12-30 | 2022-04-05 | 中北大学 | Low-power consumption energy acquisition circuit |
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