CN111525545B - Two-cabin grid-connected power supply system and method - Google Patents
Two-cabin grid-connected power supply system and method Download PDFInfo
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Abstract
The invention discloses a two-cabin grid-connected power supply system and a method, wherein the system comprises a first cabin and a second cabin, wherein the first cabin comprises a first storage battery pack, the second cabin comprises a second storage battery pack, the second cabin further comprises a grid-connected control unit, and a first storage battery pack bus and a second storage battery pack bus are connected through the grid-connected control unit. According to the invention, the optimal configuration and fault reconstruction of the electric energy of the two cabin sections are realized through a grid-connected power supply technology, the management capability and the intelligent level of the power supply mode between the two cabin sections are improved, and the adaptability and the reliability of a spacecraft power supply system are improved.
Description
Technical Field
The invention relates to the technical field of spacecraft power supply, in particular to a two-cabin grid-connected power supply system and a two-cabin grid-connected power supply method.
Background
With the development of aerospace technology, multi-cabin combined spacecrafts become common technical solutions for spacecrafts with complex tasks such as space stations, manned spacecrafts, deep space exploration and the like. Usually, each cabin section has an independent power supply system to supply power to a load, and the cabin section can be operated independently or in a grid-connected mode. The flexibility and reliability of a spacecraft power supply system are enhanced due to the introduction of the grid-connected power supply technology, and the design of a multi-cabin grid-connected power supply system and an electric energy management strategy become a new research direction gradually.
At present, a multi-cabin spacecraft grid-connected power supply system at home and abroad is connected in series with a grid-connected controller between full-regulating buses to realize grid-connected power supply, and does not have the function of supplementing and charging a storage battery; the electric energy management strategy is still in an exploration stage, and the electric energy management strategy has the characteristics of single power supply mode, weak self-service management capability and low intelligent level. Bidirectional grid-connected power supply between a 120V bus and a 28V bus can be realized by grid-connected controllers ARCU and RACU between a USOS cabin section of the United states part of the international space station and a FGB cabin section bus of the Russian part, and the USOS is mainly supplied with power by FGB through RACU at the initial construction stage of the space station; after the USOS is assembled, the output power of the FGB battery array is reduced due to shielding, and the USOS supplies power to the FGB through the ARCU. No matter illumination or ground shadow, the electric energy provided by the grid-connected controller is preferentially used, and the energy scheduling scheme is single; the service cabin of the CE-5T1 supplies power for the returner in one way through the control switch and the cable between the units in the combined mode, and the returner is switched into internal power through a ground remote control command before the two units are separated; a unidirectional grid-connected controller is designed between a load bus and a platform bus inside a GF-3 satellite, and the load bus supplies power to the platform bus through the grid-connected controller only when the platform bus fails. For a spacecraft with equivalent power supply capacity, how to autonomously realize optimal configuration and fault reconstruction of electric energy of two cabin sections by a grid-connected power supply technology can be used for reference without any successful case.
Disclosure of Invention
The invention provides a two-cabin grid-connected power supply system and a two-cabin grid-connected power supply method, aiming at autonomously realizing optimal configuration and fault reconstruction of electric energy of two cabins by a grid-connected power supply technology, improving the management capability and intelligent level of a power supply mode between the two cabins and increasing the adaptability and reliability of a spacecraft power supply system.
In order to achieve the above object, the present invention provides a two-bay grid-connected power supply system, which comprises a first bay and a second bay, wherein the first cabin section comprises a first solar cell array, a first power supply/charge shunt regulation module connected with the first solar cell array, a first discharge regulation module connected with the first power supply/charge shunt regulation module, and a first storage battery pack, the second cabin section comprises a second solar cell array, a second power supply/charging shunt regulation module connected with the second solar cell array, a second discharging regulation module connected with the second power supply/charging shunt regulation module and a second storage battery pack, the second cabin section also comprises a grid-connected control unit, and the first storage battery group bus and the second storage battery group bus are connected through the grid-connected control unit;
the grid-connected control unit comprises a one-way isolation type buck-boost converter DC/DC1 and a one-way isolation type buck-boost converter DC/DC2, wherein a fuse F1 and a switch C1 are arranged at the input end of the converter DC/DC1, an isolation diode D1 is arranged at the output end of the converter DC/DC1 and used for supplying power to the first cabin section through the second cabin section, a fuse F2 and a switch C2 are arranged at the input end of the converter DC/DC2, and an isolation diode D2 is arranged at the output end of the converter DC/DC2 and used for supplying power to the second cabin section through the first cabin section.
In order to achieve the above object, the present invention further provides a two-bay grid-connected power supply method, which is applied to the system described above, and the method includes the following steps:
acquiring a first battery pack voltage U1 and a second battery pack voltage U2 when the first bay and the second bay are in a combined flight mode;
comparing the first storage battery pack voltage U1 with a preset normal lower limit voltage K1, and comparing the second storage battery pack voltage U2 with a preset normal lower limit voltage K2;
and configuring a power supply strategy between the first cabin and the second cabin through the grid-connected control unit according to a comparison result, wherein the power supply strategy comprises a normal energy mode, a first fault energy mode and a second fault energy mode.
According to a further technical scheme of the invention, the step of configuring the power supply strategy between the first cabin and the second cabin through the grid-connected control unit according to the comparison result comprises the following steps:
if U1 > K1 and U2 > K2, entering a normal energy mode;
if the U1 is less than or equal to K1, entering a first fault energy mode;
and if the U2 is less than or equal to K2, entering a second failure energy supply mode.
The further technical scheme of the invention is that the step of entering the normal energy mode comprises the following steps:
if the first solar cell array is not shunted and the number of the shunts of the second solar cell array in the shunting state is more than 2, controlling the second cabin to supply power to the first cabin through the grid-connected control unit;
if the second solar cell array is not shunted and the number of the shunts of the first solar cell array in the shunting state is more than 2, controlling the first cabin section to supply power to the second cabin section through the grid-connected control unit;
if the SAm array of the first solar cell array is shunted or the second cell array is not shunted, the first cabin section and the second cabin section independently supply power;
and if the SAn array of the second solar cell array is shunted or the first cell array is not shunted, the second cabin section and the first cabin section independently supply power.
A further technical solution of the present invention is that the step of entering the first failure energy mode includes:
if the voltage U2 of the second storage battery pack is lower than a preset grid-connected starting voltage lower limit K4, closing a load connected with the first storage battery pack and the second storage battery pack;
if U2 is larger than K4, the second cabin is controlled by the grid-connected control unit to supply power to the first cabin;
and if the U1 is more than K1 or the U2 is less than or equal to K4, controlling the second cabin to stop supplying power to the first cabin through the grid-connected control unit.
A further technical solution of the present invention is that the step of entering the second failure energy mode includes:
if the voltage U1 of the first storage battery pack is lower than a preset grid-connected starting voltage lower limit K3, closing a load connected with the first storage battery pack and the second storage battery pack;
if U1 is larger than K3, the first cabin section is controlled by the grid-connected control unit to supply power to the second cabin section;
and if the U2 is more than K4 or the U1 is less than or equal to K3, controlling the first cabin to stop supplying power to the second cabin through the grid-connected control unit.
A further technical solution of the present invention is that, when the first bay and the second bay are in the combined flight mode, the step of obtaining the first battery pack voltage U1 and the second battery pack voltage U2 further includes:
judging whether the first cabin and the second cabin are in an independent flight mode or a combined flight mode;
if the first cabin and the second cabin are in independent flight modes, closing the grid-connected control unit;
and if the first cabin section and the second cabin section are in a combined flight mode, executing the step of acquiring the voltage of the first storage battery pack U1 and the voltage of the second storage battery pack U2.
The further technical scheme of the invention is that when the fusing C2 is closed and the fusing C1 is opened, the second cabin section supplies power to the first cabin section; when the fuse C1 is closed and the fuse C2 is open, the first bay section provides power to the second bay section.
According to a further technical scheme, the working states of all levels of the first solar cell array and the second solar cell array are judged by detecting the output voltage of all levels of the arrays, and when the output voltage of the arrays is lower than a preset threshold value K5, the arrays are judged to work in a shunting mode.
The invention further adopts the technical scheme that the adoption points of the output voltage of each level of the array are arranged at the access positions of the positive and negative terminals of the power supply of the array at the inlet end of the corresponding power supply/charging shunt regulation module.
The two-cabin grid-connected power supply system and the method have the beneficial effects that:
1. a grid-connected control unit is arranged between a first storage battery pack bus and a second storage battery pack bus, so that power can be supplied to a load and the storage battery pack can be charged;
2. the normal energy mode and the fault energy mode can be identified and autonomous control is carried out, the sharing and optimization of energy among the cabin sections are realized, and the adaptability and the reliability of a spacecraft power supply system are improved;
3. under a normal energy mode, grid-connected power supply is allowed to be carried out on other cabin sections only when the solar cell array in the cabin section has redundant energy for shunting, so that the utilization rate of the electric energy of the solar cell array is increased, and unnecessary discharge of a storage battery pack in the cabin section is avoided;
4. under the failure energy mode, as long as the storage battery pack of the cabin section has the capacity, the grid-connected control unit supplies power to the failure cabin section, so that the troubleshooting time is won as far as possible on the premise of ensuring the load power requirement, and the reliability of the whole power supply system is improved;
5. the invention does not need to distinguish the illumination area from the shadow area, and has simple control method and strong adaptability.
Drawings
FIG. 1 is a diagram of the energy system architecture of a preferred embodiment of the two bay grid tie power system of the present invention;
FIG. 2 is a schematic flow chart of a preferred embodiment of a two-bay grid-connected power supply method of the present invention;
FIG. 3 is a normal/fault energy mode switching flow diagram;
FIG. 4 is a flow chart of energy scheduling in normal energy mode;
FIG. 5 is a flow chart of energy scheduling in a first failed energy mode;
FIG. 6 is a flow chart of energy scheduling in a second failed energy mode;
the implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The invention provides a two-cabin grid-connected power supply system and method, and particularly relates to a two-cabin grid-connected power supply system and an autonomous energy scheduling method.
The technical scheme adopted by the invention is mainly as follows: under the combined flight mode, the storage battery buses are connected with a grid-connected control unit to realize grid-connected power supply between two cabin sections; by detecting the voltage of each cabin storage battery pack and the number of shunt circuits of the solar cell array, a normal energy mode (the voltage of the storage battery pack is higher than the lower voltage limit) and a fault energy mode (the voltage of the storage battery pack is lower than the lower voltage limit) can be identified and autonomous control is carried out; in the normal energy mode, the buses of the cabin with sufficient energy (the number of the shunt arrays is more than 2) can automatically supply power to the buses of the cabin with insufficient energy (the whole partial array is not shunted), so that the utilization rate of the solar cell array is improved; the fault energy mode can supply power to the fault cabin section from the normal cabin section on the premise that the voltage of the storage battery pack is higher than the grid-connected starting voltage, and therefore fault elimination time is won for emergency power supply. Therefore, sharing and optimization of energy among the cabin sections are realized, and the adaptability and reliability of the spacecraft power supply system are improved.
Specifically, referring to fig. 1, fig. 1 is a structural diagram of an energy system of a preferred embodiment of the two-bay grid-connected power supply system of the present invention.
As shown in fig. 1, in this embodiment, the two-bay grid-connected power supply system includes a first bay and a second bay, where the first bay includes a first solar cell array, a first power supply/charge shunt regulation module connected to the first solar cell array, a first discharge regulation module connected to the first power supply/charge shunt regulation module, and a first battery pack, and supplies power to a fully-regulated bus load1_1 and a battery bus load2_ 1.
The second cabin section comprises a second solar cell array, a second power supply/charging shunt regulation module connected with the second solar cell array, a second discharging regulation module connected with the second power supply/charging shunt regulation module and a second storage battery pack, and the second power supply/charging shunt regulation module supplies power for a fully-regulated bus load1_2 and a storage battery bus load2_ 2.
The second cabin section further comprises a grid-connected control unit, and the first storage battery pack bus and the second storage battery pack bus are connected through the grid-connected control unit.
The grid-connected control unit comprises a one-way isolation type buck-boost converter DC/DC1 and a one-way isolation type buck-boost converter DC/DC2, wherein a fuse F1 and a switch C1 are arranged at the input end of the converter DC/DC1, an isolation diode D1 is arranged at the output end of the converter DC/DC1 and used for supplying power to the first cabin section through the second cabin section, a fuse F2 and a switch C2 are arranged at the input end of the converter DC/DC2, and an isolation diode D2 is arranged at the output end of the converter DC/DC2 and used for supplying power to the second cabin section through the first cabin section.
When flying alone, the first cabin section and the second cabin section can work under the track condition of alternate illumination and shadow, the power supply requirements of different types of loads can be met, and the grid-connected control unit is closed. Each subarray of the first cabin section is gradually shunted from the mth stage (SAm) to the 1 st stage, and each subarray of the second cabin section is gradually shunted from the nth stage (SAn) to the 1 st stage.
And under the combined flight mode, the first cabin section and the second cabin section are connected with a grid-connected control unit between the first storage battery group bus and the second storage battery group bus, so that grid-connected power supply between the two cabin sections is realized. The working modes of grid-connected power supply comprise the following three modes: the first cabin section supplies power to the second cabin section (C2 is closed, C1 is opened, and DC/DC2 works), the second cabin section supplies power to the first cabin section (C1 is closed, C2 is opened, and DC/DC1 works), and the first cabin section and the second cabin section are independently supplied with power (C1 and C2 are both opened, and DC/DC1 and DC/DC2 do not work).
The two-cabin grid-connected power supply system has the beneficial effects that:
1. a grid-connected control unit is arranged between a first storage battery pack bus and a second storage battery pack bus, so that power can be supplied to a load and the storage battery pack can be charged;
2. the normal energy mode and the fault energy mode can be identified and autonomous control is carried out, the sharing and optimization of energy among the cabin sections are realized, and the adaptability and the reliability of a spacecraft power supply system are improved;
3. under a normal energy mode, grid-connected power supply is allowed to be carried out on other cabin sections only when the solar cell array in the cabin section has redundant energy for shunting, so that the utilization rate of the electric energy of the solar cell array is increased, and unnecessary discharge of a storage battery pack in the cabin section is avoided;
4. under the failure energy mode, as long as the storage battery pack of the cabin section has the capacity, the grid-connected control unit supplies power to the failure cabin section, so that the troubleshooting time is won as far as possible on the premise of ensuring the load power requirement, and the reliability of the whole power supply system is improved;
5. the invention does not need to distinguish the illumination area from the shadow area, and has simple control method and strong adaptability.
Referring to fig. 2, in order to achieve the above object, the present invention further provides a two-bay grid-connected power supply method, and fig. 2 is a schematic flow chart of a preferred embodiment of the two-bay grid-connected power supply method according to the present invention, which is applied to the two-bay grid-connected power supply system shown in fig. 1.
As shown in fig. 2, in this embodiment, the two-bay grid-connected power supply method includes the following steps:
step S10, acquiring a first battery pack voltage U1 and a second battery pack voltage U2 when the first bay and the second bay are in a combined flight mode.
In this embodiment, a grid-connected control unit is connected between the first storage battery pack bus and the second storage battery pack bus to implement grid-connected power supply between the first cabin section and the second cabin section.
Step S20, comparing the first storage battery pack voltage U1 with a preset normal lower limit voltage K1, and comparing the second storage battery pack voltage U2 with a preset normal lower limit voltage K2.
Referring to table 1, a preset normal lower limit voltage K1 and a preset normal lower limit voltage K2 refer to a threshold value of a normal voltage lower limit, a grid-connected starting voltage lower limit and a shunt value upper limit of a lithium ion storage battery (7 single-cell series connection) for a 30V bus, which is shown in table 1.
Step S30, configuring a power supply strategy between the first cabin and the second cabin through the grid-connected control unit according to the comparison result, wherein the power supply strategy comprises a normal energy mode, a first fault energy mode and a second fault energy mode.
Specifically, the step of configuring the power supply strategy between the first cabin section and the second cabin section through the grid-connected control unit according to the comparison result includes:
in step S301, if U1 > K1 and U2 > K2, enter the normal energy mode.
And if the first solar cell array is not shunted and the number of the shunts of the second solar cell array in the shunting state is more than 2, controlling the second cabin section to supply power to the first cabin section through the grid-connected control unit.
And if the second solar cell array is not shunted and the number of the shunts of the first solar cell array in the shunting state is more than 2, controlling the first cabin section to supply power to the second cabin section through the grid-connected control unit.
And if the SAm array of the first solar cell array is shunted or the second cell array is not shunted, the first cabin section and the second cabin section independently supply power.
And if the SAn array of the second solar cell array is shunted or the first cell array is not shunted, the second cabin section and the first cabin section independently supply power.
In step S302, if U1 is not greater than K1, the method enters a first failure energy mode.
And if the voltage U2 of the second storage battery pack is lower than a preset grid-connected starting voltage lower limit K4, closing a load connected with the first storage battery pack and the second storage battery pack.
And if the U2 is more than K4, the second cabin is controlled by the grid-connected control unit to supply power to the first cabin.
And if the U1 is more than K1 or the U2 is less than or equal to K4, controlling the second cabin to stop supplying power to the first cabin through the grid-connected control unit.
In step S303, if U2 is not greater than K2, the power supply mode for the second failure can be performed.
If the voltage U1 of the first storage battery pack is lower than a preset grid-connected starting voltage lower limit K3, a load connected with the first storage battery pack and the second storage battery pack is closed.
And if the U1 is more than K3, the first cabin section is controlled by the grid-connected control unit to supply power to the second cabin section.
And if the U2 is more than K4 or the U1 is less than or equal to K3, controlling the first cabin to stop supplying power to the second cabin through the grid-connected control unit.
Please refer to table 1 for the lower grid-connected start-up voltage limit K3 and the lower grid-connected start-up voltage limit K4.
It is understood that in this embodiment, the step of obtaining the first battery pack voltage U1 and the second battery pack voltage U2 when the first bay and the second bay are in the combined flight mode further includes the following steps:
determining whether the first and second bays are in individual flight mode or combined flight mode.
And if the first cabin and the second cabin are in independent flight modes, closing the grid-connected control unit.
And if the first cabin section and the second cabin section are in a combined flight mode, executing the step of acquiring the voltage of the first storage battery pack U1 and the voltage of the second storage battery pack U2.
It is worth proposing that, in this embodiment, the grid-connected control unit includes a unidirectional isolation type buck-boost converter DC/DC1 and a unidirectional isolation type buck-boost converter DC/DC2, the input end of the converter DC/DC1 is provided with a fuse F1 and a switch C1, the output end is provided with an isolation diode D1, the fuse F2 and the switch C2 are used for supplying power to the first bay section from the second bay section, the input end of the converter DC/DC2 is provided with a fuse F2 and a switch C2, and the output end is provided with an isolation diode D2, which is used for supplying power to the second bay section from the first bay section. When the fuse C2 is closed and the fuse C1 is open, the second bay section supplies power to the first bay section; when the fuse C1 is closed and the fuse C2 is open, the first bay section provides power to the second bay section.
In this embodiment, the working states of the respective stage arrays of the first solar cell array and the second solar cell array are determined by detecting the output voltages of the respective stage arrays, and when the output voltages of the stage arrays are lower than a preset threshold value K5, it is determined that the stage array works in the shunting mode.
And the adoption point of the output voltage of each stage of the array is arranged at the access position of the positive and negative power supply terminals of the corresponding power supply/charging shunt regulation module inlet end.
The two-bay grid-connected power supply method according to the embodiment is further described in detail with reference to fig. 1 to 6.
The two-cabin grid-connected power supply method of the embodiment is applied to the two-cabin grid-connected power supply system shown in fig. 1. The spacecraft comprises a cabin section 1 and a cabin section 2, wherein a power supply system of the cabin section 1 comprises a solar cell array, a power supply/charging shunt regulation module, a discharging regulation module and a storage battery pack, and the power supply system supplies power for a fully-regulated bus load1_1 and a storage battery bus load2_ 1. The cabin 2 power supply system comprises a solar cell array, a power supply/charge shunt regulation module, a discharge regulation module, a storage battery pack and a grid-connected control unit, and supplies power for a fully-regulated bus load1_2 and a storage battery bus load2_ 2. Under the combined flight mode of the two cabin sections, the storage battery group buses are connected with a grid-connected control unit, so that grid-connected power supply between the two cabin sections is realized. The grid-connected power supply unit is internally composed of 2 independent unidirectional isolated buck-boost DC/DC converters, the input section of the DC/DC1 converter is provided with a fuse F1 and a switch C1, and the output end of the DC/DC1 converter is provided with an isolating diode D1 for supplying power to the cabin section 1 from the cabin section 2; the input section of the DC/DC2 converter is provided with a fuse F2 and a switch C2, and the output end of the DC/DC2 converter is provided with an isolation diode D2 for supplying power to the cabin section 2 from the cabin section 1.
The control flow chart of the energy scheduling method is shown in fig. 2-6, and the thresholds of the lower limit of the normal voltage value, the lower limit of the grid-connected starting voltage and the upper limit of the shunt value of the lithium ion storage battery (7 single batteries connected in series) for the 30V bus are shown in table 1.
The two cabin sections can work under the condition of an orbit with alternate illumination and shadow in an independent flight mode, the power supply requirements of loads of different types can be met, and the grid-connected control unit is closed. Each subarray of the cabin section 1 is gradually shunted from the mth stage (SAm) to the 1 st stage, and each subarray of the cabin section 2 is gradually shunted from the nth stage (SAn) to the 1 st stage.
Under the combined flight mode of the two cabin sections, the storage battery group buses are connected with a grid-connected control unit, and grid-connected power supply between the two cabin sections is realized. The working modes of grid-connected power supply comprise the following three modes: cabin section 1 supplies power to cabin section 2 (C2 is closed, C1 is open, DC/DC2 works), cabin section 2 supplies power to cabin section 1 (C1 is closed, C2 is open, DC/DC1 works), and cabin section 1 and cabin section 2 independently supply power (C1 and C2 are both open, DC/DC1 and DC/DC2 do not work).
A normal/fault energy mode switching flow chart is shown in fig. 3, when the grid-connected power supply function is forbidden, the grid-connected control unit is closed, and the cabin section 1 and the cabin section 2 independently supply power; when the grid-connected power supply function is enabled, detecting the voltage U1 of the storage battery pack in the cabin section 1, detecting the voltage U2 of the storage battery pack in the cabin section 2 when the voltage U1 is higher than the lower limit voltage K1 of a normal value, and judging that the combined body works in a normal energy mode when the voltage U2 is higher than the lower limit voltage K2 of the normal value; when the U1 is less than or equal to K1, entering a fault energy mode 1; and entering a fault energy mode 2 when the U2 is less than or equal to K2.
As shown in fig. 4, in the energy scheduling method in the normal energy mode, when none of the solar cell arrays SA 1-SAm in the bay section 1 is shunted and the number of shunts of the solar cell array in the bay section 2 in the shunt state is greater than 2, the C1 is automatically closed, the DC/DC1 starts to operate, the bay section 2 supplies power to the bay section 1, and the DC/DC1 is in the constant current mode; when the SAm array of the solar cell array of the cabin section 1 is shunted or none of the solar cell arrays SA 1-SAn of the cabin section 2 is shunted, the C1 is automatically disconnected, the DC/DC1 stops working, and the cabin section 1 and the cabin section 2 independently supply power. When the solar cell arrays SA 1-SAn of the cabin section 2 are not shunted and the number of the shunts of the solar cell array of the cabin section 1 in the shunting state is more than 2, the C2 is automatically closed, the DC/DC2 starts to work, the cabin section 1 supplies power to the cabin section 2, and the DC/DC2 is in a constant current mode; when the SAn sub-array of the solar cell array of the cabin section 2 is shunted or none of the solar cell arrays SA 1-SAm of the cabin section 1 is shunted, the C2 is automatically disconnected, the DC/DC2 stops working, and the cabin section 1 and the cabin section 2 independently supply power.
As shown in fig. 5 and 6, in the energy scheduling method in the failure energy mode, in the first failure energy mode, when the voltage U2 of the storage battery pack in the cabin section 2 is lower than the lower limit K4 of the grid-connected starting voltage, the fault removal time can be won only by reducing the energy demand of each cabin section by closing the load; when U2 is larger than K4, C1 is automatically closed, DC/DC1 starts to work, power is supplied to the cabin section 1 from the cabin section 2, and the DC/DC1 is in a constant current mode; and when the U1 is more than K1 or the U2 is less than or equal to K4, the C1 is automatically disconnected, the DC/DC1 does not work, and the fault mode is exited. In the second failure energy mode, when the voltage U1 of the storage battery pack in the cabin section 1 is lower than the lower limit K3 of the grid-connected starting voltage, the troubleshooting time can be won only by reducing the energy requirement of each cabin section by closing the load; when U1 is larger than K3, C2 is automatically closed, DC/DC2 starts to work, power is supplied to a cabin section 2 from a cabin section 1, and DC/DC2 is in a constant current mode; and when the U2 is more than K2 or the U1 is less than or equal to K3, the C2 is automatically disconnected, the DC/DC2 does not work, and the fault mode is exited.
It should be noted that in the solar cell array, the operating state of each stage of the array may be determined by detecting the output voltage of the array, and when the output voltage of a certain stage of the array is lower than the threshold value K5, it is determined that the stage of the array operates in the shunting mode.
TABLE 1 threshold settings
The two-cabin grid-connected power supply method has the beneficial effects that:
1. a grid-connected control unit is arranged between a first storage battery pack bus and a second storage battery pack bus, so that power can be supplied to a load and the storage battery pack can be charged;
2. the normal energy mode and the fault energy mode can be identified and autonomous control is carried out, the sharing and optimization of energy among the cabin sections are realized, and the adaptability and the reliability of a spacecraft power supply system are improved;
3. under a normal energy mode, grid-connected power supply is allowed to be carried out on other cabin sections only when the solar cell array in the cabin section has redundant energy for shunting, so that the utilization rate of the electric energy of the solar cell array is increased, and unnecessary discharge of a storage battery pack in the cabin section is avoided;
4. under the failure energy mode, as long as the storage battery pack of the cabin section has the capacity, the grid-connected control unit supplies power to the failure cabin section, so that the troubleshooting time is won as far as possible on the premise of ensuring the load power requirement, and the reliability of the whole power supply system is improved;
5. the invention does not need to distinguish the illumination area from the shadow area, and has simple control method and strong adaptability.
The above description is only for the preferred embodiment of the present invention and is not intended to limit the scope of the present invention, and all equivalent structures or flow transformations made by the present specification and drawings, or applied directly or indirectly to other related arts, are included in the scope of the present invention.
Claims (5)
1. A two-cabin grid-connected power supply method is characterized in that the method is applied to a two-cabin grid-connected power supply system, the system comprises a first cabin and a second cabin, wherein the first cabin section comprises a first solar cell array, a first power supply/charge shunt regulation module connected with the first solar cell array, a first discharge regulation module connected with the first power supply/charge shunt regulation module, and a first storage battery pack, the second cabin section comprises a second solar cell array, a second power supply/charging shunt regulation module connected with the second solar cell array, a second discharging regulation module connected with the second power supply/charging shunt regulation module and a second storage battery pack, the second cabin section also comprises a grid-connected control unit, and the first storage battery group bus and the second storage battery group bus are connected through the grid-connected control unit; the grid-connected control unit comprises a one-way isolation type buck-boost converter DC/DC1 and a one-way isolation type buck-boost converter DC/DC2, wherein a fuse F1 and a switch C1 are arranged at the input end of the converter DC/DC1, an isolation diode D1 is arranged at the output end of the converter DC/DC1 and used for supplying power to the first cabin section through the second cabin section, a fuse F2 and a switch C2 are arranged at the input end of the converter DC/DC2, and an isolation diode D2 is arranged at the output end of the converter DC/DC2 and used for supplying power to the second cabin section through the first cabin section; the working state of each stage of the first solar cell array and the second solar cell array is judged by detecting the output voltage of each stage of the array, and when the output voltage of the array is lower than a preset threshold value K5, the stage of the array is judged to work in a shunting mode, and the method comprises the following steps:
acquiring a first battery pack voltage U1 and a second battery pack voltage U2 when the first bay and the second bay are in a combined flight mode;
comparing the first storage battery pack voltage U1 with a preset normal lower limit voltage K1, and comparing the second storage battery pack voltage U2 with a preset normal lower limit voltage K2;
according to the comparison result, configuring a power supply strategy between the first cabin and the second cabin through the grid-connected control unit, wherein the power supply strategy comprises a normal energy mode, a first fault energy mode and a second fault energy mode;
the step of obtaining a first battery pack voltage U1 and a second battery pack voltage U2 while the first bay and the second bay are in a combined flight mode further comprises:
judging whether the first cabin and the second cabin are in an independent flight mode or a combined flight mode;
if the first cabin and the second cabin are in independent flight modes, closing the grid-connected control unit;
if the first cabin section and the second cabin section are in a combined flight mode, executing the step of acquiring a first storage battery pack voltage U1 and a second storage battery pack voltage U2;
the step of configuring a power supply strategy between the first cabin and the second cabin through the grid-connected control unit according to the comparison result comprises the following steps:
if U1 > K1 and U2 > K2, entering a normal energy mode;
if the U1 is less than or equal to K1, entering a first fault energy mode;
if the U2 is not more than K2, entering a second fault energy power supply mode;
the step of entering a normal energy mode comprises:
if the first solar cell array is not shunted and the number of the shunts of the second solar cell array in the shunting state is more than 2, controlling the second cabin to supply power to the first cabin through the grid-connected control unit;
if the second solar cell array is not shunted and the number of the shunts of the first solar cell array in the shunting state is more than 2, controlling the first cabin section to supply power to the second cabin section through the grid-connected control unit;
if the SAm array of the first solar cell array is shunted or the second solar cell array is not shunted, the first cabin section and the second cabin section independently supply power;
and if the SAn array of the second solar cell array is shunted or the first solar cell array is not shunted, the second cabin section and the first cabin section independently supply power.
2. The two bay grid-connected power supply method according to claim 1, wherein the step of entering the first failure energy mode comprises:
if the voltage U2 of the second storage battery pack is lower than a preset grid-connected starting voltage lower limit K4, closing a load connected with the first storage battery pack and the second storage battery pack;
if U2 is larger than K4, the second cabin is controlled by the grid-connected control unit to supply power to the first cabin;
and if the U1 is more than K1 or the U2 is less than or equal to K4, controlling the second cabin to stop supplying power to the first cabin through the grid-connected control unit.
3. The two bay grid-connected power supply method according to claim 1, wherein the step of entering the second failure energy mode comprises:
if the voltage U1 of the first storage battery pack is lower than a preset grid-connected starting voltage lower limit K3, closing a load connected with the first storage battery pack and the second storage battery pack;
if U1 is larger than K3, the first cabin section is controlled by the grid-connected control unit to supply power to the second cabin section;
and if the U2 is more than K4 or the U1 is less than or equal to K3, controlling the first cabin to stop supplying power to the second cabin through the grid-connected control unit.
4. The two-bay grid-connected power supply method according to any one of claims 1 to 3, wherein when the fused C2 is closed and the fused C1 is open, the second bay supplies power to the first bay; when the fuse C1 is closed and the fuse C2 is open, the first bay section provides power to the second bay section.
5. The two-bay grid-connected power supply method according to claim 1, wherein the sampling point of the output voltage of each stage of the array is set at the access point of the positive and negative terminals of the power supply of the array at the inlet end of the corresponding power supply/charging shunt regulation module.
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