CN112803572B - Satellite power supply system with fault reconstruction function - Google Patents

Satellite power supply system with fault reconstruction function Download PDF

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Publication number
CN112803572B
CN112803572B CN202110003964.1A CN202110003964A CN112803572B CN 112803572 B CN112803572 B CN 112803572B CN 202110003964 A CN202110003964 A CN 202110003964A CN 112803572 B CN112803572 B CN 112803572B
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switches
switch
solar
power
load
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CN112803572A (en
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叶泽雨
尹靖元
韦统振
师长立
韩立博
彭祥华
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Institute of Electrical Engineering of CAS
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Institute of Electrical Engineering of CAS
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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
    • 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
    • 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
    • H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
    • H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
    • H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
    • H02J9/061—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems for DC powered loads
    • 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
    • Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
    • Y02B10/00—Integration of renewable energy sources in buildings
    • Y02B10/70—Hybrid systems, e.g. uninterruptible or back-up power supplies integrating renewable energies
    • 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
    • Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
    • Y02B70/00—Technologies for an efficient end-user side electric power management and consumption
    • Y02B70/30—Systems integrating technologies related to power network operation and communication or information technologies for improving the carbon footprint of the management of residential or tertiary loads, i.e. smart grids as climate change mitigation technology in the buildings sector, including also the last stages of power distribution and the control, monitoring or operating management systems at local level
    • 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
    • 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
    • Y04—INFORMATION OR COMMUNICATION TECHNOLOGIES HAVING AN IMPACT ON OTHER TECHNOLOGY AREAS
    • Y04S—SYSTEMS INTEGRATING TECHNOLOGIES RELATED TO POWER NETWORK OPERATION, COMMUNICATION OR INFORMATION TECHNOLOGIES FOR IMPROVING THE ELECTRICAL POWER GENERATION, TRANSMISSION, DISTRIBUTION, MANAGEMENT OR USAGE, i.e. SMART GRIDS
    • Y04S20/00—Management or operation of end-user stationary applications or the last stages of power distribution; Controlling, monitoring or operating thereof
    • Y04S20/20—End-user application control systems

Abstract

The invention belongs to the technical field of satellite power supplies, particularly relates to a satellite power supply system with a fault reconstruction function, and aims to solve the problems that an existing satellite power supply system is complex in structure and difficult to recover after a fault. The invention comprises the following steps: the N solar arrays convert the acquired light energy into electric energy; the N solar controllers correspond to the solar array one by one and are used for carrying out load power supply and lithium battery charging under different illumination conditions; the M power modules correspond to the loads one by one and convert the bus voltage into rated power supply voltage corresponding to the loads; the lithium battery switch matrix is used for storing electric energy and supplying power to a load through a lithium battery; and the switch group is integrated, and the normal work, reconstruction and fault adjustment of the circuit are realized by controlling the on-off of each switch. The system has simple structure and easy control, and is provided with the standby circuit for the solar controller, the power module and the lithium battery module, thereby having high recovery efficiency in failure, strong steady-state operation capability of the system and high safety and reliability.

Description

Satellite power supply system with fault reconstruction function
Technical Field
The invention belongs to the technical field of satellite power supplies, and particularly relates to a satellite power supply system with a fault reconstruction function.
Background
With the development of space technology and the increasing frequency of human exploration space activities, the number of satellites in space increases in geometric progression. At present, small satellites are rapidly developed, have small volumes and highly integrated electronic systems, especially power supplies carried by power supply systems.
The existing satellite power supply system mainly adopts an MPPT energy transmission mode, a single bus structure is not adjusted, and a lithium battery is connected with a bus through a relay. However, the system has the structures of a shunt regulator, a lithium battery charging and discharging circuit and the like, and is relatively complex and large in size. Moreover, the system structure is independent of each other, and the system cannot work when a fault occurs.
Generally speaking, the existing satellite power supply system is complex and large in size, and the system structures cannot be used for standby, so that the system cannot be quickly restored to normal when the system fails.
Disclosure of Invention
In order to solve the above problems in the prior art, that is, the existing satellite power supply system has a complex structure and is difficult to recover after a fault, the invention provides a satellite power supply system with a fault reconfiguration function, which comprises the following modules:
the N solar arrays are used for converting the acquired light energy into electric energy;
the solar energy controllers are in one-to-one correspondence with the N solar arrays, when the output power of the solar arrays is larger than a set threshold value, the solar energy controllers work in a boosting mode to supply power to the load and charge lithium batteries in the lithium battery switch matrix, when the output power of the solar arrays is not larger than the set threshold value, the solar energy controllers work in an MPPT mode and supply power to the load together with the lithium batteries in the lithium battery switch matrix, and when the output power of the solar arrays is 0, the solar energy controllers stop working and supply power to the load by the lithium batteries in the lithium battery switch matrix;
the M power modules correspond to the loads of the power supply system one by one and are used for converting the bus voltage into the rated power supply voltage of the corresponding load;
the lithium battery switch matrix is used for storing electric energy and supplying power to a load through a lithium battery;
the first switch group and the second switch group comprise N first switches and N second switches, and the first switch group and the second switch are respectively used for connecting the output positive electrode of each solar controller with the positive electrode of the bus and connecting the output negative electrode of each solar controller with the negative electrode of the bus;
and the third switch group comprises M third switches and is used for connecting the output positive electrode of each power module with the load positive electrode.
In some preferred embodiments, the system further comprises:
the fourth switch group comprises N-1 fourth switches, and the nth fourth switch is used for connecting the output cathode of the nth solar controller with the output anode of the (N + 1) th solar controller;
wherein N is more than or equal to 1 and less than N-1.
In some preferred embodiments, the system realizes the connection mode adjustment of the N solar controllers by controlling the on/off of the switches in the first switch group, the second switch group and the fourth switch group:
controlling the N first switches and the N second switches to be closed and controlling the N-1 fourth switches to be opened, so that the N solar controllers work in parallel;
and (3) controlling the (n + 1) th first switch and the (n) th second switch to be switched off, closing the rest first switches and the rest second switches, controlling the (n) th fourth switch to be switched on and off, and switching the rest fourth switches off, so that the (n) th solar controller is connected with the (n + 1) th solar controller in series and then connected with the other solar controllers in parallel to work.
In some preferred embodiments, the system performs the fault adjustment of the N solar controllers by controlling the on/off of the switches in the first switch group, the second switch group and the fourth switch group:
if the nth solar controller fails, the nth first switch and the nth second switch are controlled to be switched off, the rest first switches and the rest second switches are switched on, the N-1 fourth switches are controlled to be switched off, and the rest solar controllers except the failed nth solar controller work in parallel.
In some preferred embodiments, the system further comprises:
the fifth switch group comprises M-1 fifth switches, and the mth fifth switch is used for connecting the input positive electrode of the mth load with the input positive electrode of the (M + 1) th load;
wherein M is more than or equal to 1 and less than M-1.
In some preferred embodiments, the system adjusts the connection mode between the M power modules and the load by controlling the on/off of the switches in the third switch group and the fifth switch group:
controlling the M third switches to be closed and the M-1 fifth switches to be opened, so that the M power modules respectively supply power to the corresponding M loads;
and controlling the m-th third switch to be switched off, the rest of the third switches to be switched on, controlling the m-th fifth switch to be switched on, and the rest of the fifth switches to be switched off, so that the (m + 1) -th power module supplies power to the m-th load and the (m + 1) -th load, the m-th power module stops working, and the rest of the power modules respectively supply power to corresponding loads.
In some preferred embodiments, the system implements fault regulation of the M power modules and the load by controlling the on and off of the switches in the third switch group and the fifth switch group:
and if the mth power module or the load fails, controlling the mth third switch to be switched off, closing the rest of the third switches, and controlling the M-1 fifth switches to be switched on, wherein the failed mth power module or the rest of the power modules except the load respectively supply power to the corresponding loads.
In some preferred embodiments, the lithium battery switch matrix includes:
when the output power of the solar array is not greater than the set threshold value or is 0, the electric energy is stored, and power is supplied to a load;
the sixth switch group is composed of X multiplied by Y sixth switches which are connected with the X multiplied by Y lithium batteries in series in a one-to-one correspondence mode, and the seventh switch group is composed of X seventh switches which are connected with the X row lithium batteries and the sixth switch combination circuit in parallel.
In some preferred embodiments, the system adjusts the fault of the X × Y lithium batteries by turning on and off the switches in the sixth switch group and the seventh switch group:
when the lithium batteries in the x-th row and the y-th column need to work, the corresponding sixth switches are controlled to be closed, the rest sixth switches are switched off, the seventh switch in the x-th row is controlled to be switched off, and the rest seventh switches are switched on;
wherein X is more than or equal to 1 and less than or equal to X, and Y is more than or equal to 1 and less than or equal to Y.
In some preferred embodiments, the switches are solid state switches.
The invention has the beneficial effects that:
(1) The satellite power supply system with the fault reconstruction function abandons a shunt regulator and a lithium battery charging and discharging circuit of the traditional satellite power supply system, has a simple system structure, is easy to control and overhaul, reduces the cost and the volume, and further improves the power supply duration of the satellite power supply system.
(2) The satellite power supply system with the fault reconstruction function, provided by the invention, is provided with the standby circuit for the solar controller, the power module and the lithium battery module, and circuit reconstruction and fault adjustment are carried out by controlling the corresponding solid-state switches, so that the recovery efficiency is high during fault, and the steady-state operation capability of the satellite power supply system and the safety and reliability of the system are further improved.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
FIG. 1 is a schematic structural diagram of a satellite power system with a fault reconfiguration function according to the present invention;
FIG. 2 is a schematic diagram of a solar controller connected in parallel for an embodiment of the satellite power system with fault reconfiguration function according to the present invention;
FIG. 3 is a schematic diagram of a solar controller series connection of an embodiment of a satellite power system with fault reconfiguration of the present invention;
FIG. 4 is a schematic cut-away view of a solar controller 1 of an embodiment of the satellite power system with fault reconfiguration of the present invention;
fig. 5 is a schematic diagram illustrating that the power module 1 of an embodiment of the satellite power system with fault reconfiguration function of the present invention supplies power to the load 1;
fig. 6 is a schematic diagram of a power module 2 of an embodiment of the satellite power system with a fault reconfiguration function according to the present invention for supplying power to a load 1 and a load 2;
FIG. 7 is a schematic diagram of a load 1 being removed in one embodiment of the satellite power system with fault reconstruction functionality of the present invention;
FIG. 8 is a schematic diagram of the operation of the column 1 and the row 1 lithium battery of an embodiment of the satellite power system with the fault reconfiguration function according to the invention;
FIG. 9 is a schematic diagram of the operation of a row 1 and column 2 lithium battery of an embodiment of the satellite power system with fault reconfiguration function according to the present invention;
FIG. 10 is a schematic diagram of the operation of the row 2 and column 1 lithium battery of an embodiment of the satellite power system with fault reconfiguration function according to the invention;
fig. 11 is a schematic diagram of a prior art satellite power system.
Detailed Description
The present application will be described in further detail with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention. It should be noted that, for convenience of description, only the portions related to the related invention are shown in the drawings.
It should be noted that, in the present application, the embodiments and features of the embodiments may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
The invention relates to a satellite power supply system with a fault reconstruction function, which comprises the following modules:
the N solar arrays are used for converting the acquired light energy into electric energy;
the solar energy controllers are in one-to-one correspondence with the N solar arrays, when the output power of the solar arrays is greater than a set threshold value, the solar energy controllers work in a boosting mode to supply power to the load and charge lithium batteries in the lithium battery switch matrix, when the output power of the solar arrays is not greater than the set threshold value, the solar energy controllers work in an MPPT mode and supply power to the load together with the lithium batteries in the lithium battery switch matrix, and when the output power of the solar arrays is 0, the solar energy controllers stop working and supply power to the load by the lithium batteries in the lithium battery switch matrix;
the M power modules correspond to the loads of the power supply system one by one and are used for converting the bus voltage into the rated power supply voltage of the corresponding load;
the lithium battery switch matrix is used for storing electric energy and supplying power to a load through a lithium battery;
the first switch group and the second switch group comprise N first switches and N second switches, and the first switch group and the second switch are respectively used for connecting the output positive electrode of each solar controller with the positive electrode of the bus and connecting the output negative electrode of each solar controller with the negative electrode of the bus;
and the third switch group comprises M third switches and is used for connecting the output positive electrode of each power module with the load positive electrode.
In order to more clearly describe the satellite power system with fault reconfiguration function according to the present invention, details of the modules in the embodiment of the present invention are described below with reference to fig. 1.
The satellite power supply system with the fault reconfiguration function according to the first embodiment of the present invention includes N solar arrays, N solar controllers corresponding to the N solar arrays one to one, M power modules corresponding to power supply system loads one to one, a lithium battery switch matrix, a first switch group, a second switch group, and a third switch group, where each module is described in detail as follows:
and the N solar arrays are used for converting the acquired light energy into electric energy.
And when the output power of the solar array is not greater than the set threshold value, the solar controller works in the MPPT mode and supplies power to the load together with the lithium battery in the lithium battery switch matrix, and when the output power of the solar array is 0, the solar controller stops working and supplies power to the load by the lithium battery in the lithium battery switch matrix.
During steady state operation, according to the difference of solar array output power, solar controller has three kinds of mode, two kinds of mode corresponding to the lithium cell:
(1) Under the condition that the solar power is sufficient, namely the output power of the solar array is greater than a set threshold value, the load is completely powered by the solar energy. The solar controller is regulated to operate in a normal boost mode to charge the lithium battery while supplying power to the load. The output power of the solar battery is determined by the load power and the charging information of the lithium battery. And after the lithium battery is fully charged, keeping the output power of the solar controller balanced with the load.
(2) Under the condition that the solar power is insufficient, namely the output power of the solar array is not larger than a set threshold value, the load is powered by solar energy and a lithium battery at the same time. The solar controller operates in the MPPT mode.
(3) Under the condition that the solar energy cannot output power, namely when the output power of the solar array is 0, the load is completely powered by the lithium battery.
And the M power modules correspond to the power system loads one to one and are used for converting the bus voltage into the rated power supply voltage of the corresponding load.
And the lithium battery switch matrix is used for storing electric energy and supplying power to a load through a lithium battery.
The first switch group and the second switch group comprise N first switches and N second switches, and the first switch group and the second switch groups are respectively used for connecting the output positive pole of each solar controller with the positive pole of the bus and connecting the output negative pole of each solar controller with the negative pole of the bus.
And the third switch group comprises M third switches and is used for connecting the output positive electrode of each power module with the positive electrode of the load.
The power supply voltage is determined by a lithium battery switch matrix, and the solar battery can work in an MPPT mode or a common boosting mode by adjusting the solar controller. The voltage of the distribution bus is determined by the power modules, which can convert the bus voltage to the actual operating voltage of the load. The satellite power supply controller controls the solar controller, the power module and the solid-state switch, and can realize the functions of adjusting the working condition of the satellite power supply under the steady-state operation, reconstructing the circuit under the fault condition and the like.
The system further comprises:
the fourth switch group comprises N-1 fourth switches, and the nth fourth switch is used for connecting the output cathode of the nth solar controller with the output anode of the (N + 1) th solar controller;
wherein N is more than or equal to 1 and less than N-1.
The system realizes the adjustment of the connection modes of the N solar controllers by controlling the on-off of the switches in the first switch group, the second switch group and the fourth switch group:
controlling the N first switches and the N second switches to be closed, and controlling the N-1 fourth switches to be opened, so that the N solar controllers work in parallel;
and controlling the nth first switch and the nth second switch to be switched off, closing the rest first switches and the rest second switches, controlling the nth fourth switch to be switched on and the rest fourth switches to be switched off, and connecting the nth solar controller and the (n + 1) th solar controller in series and then connecting the nth solar controller and the (n + 1) th solar controller in parallel to work.
As shown in fig. 2, which is a schematic diagram of parallel connection of solar controllers according to an embodiment of the satellite power system with the fault reconfiguration function of the present invention, a solar array 1 is connected to the solar controller 1, a solar array 2 is connected to the solar controller 2, two switches between the solar controller 1 and a power supply bus are closed, and are disconnected from the solar controller 2, two switches between the solar controller 2 and the power supply bus are closed, and are disconnected from the solar controller 3, \8230 \, at this time, the solar controllers 1,2, \8230 \ 8230, and the parallel operation are performed.
As shown in fig. 3, which is a schematic diagram of a series connection of a solar controller according to an embodiment of the satellite power system with a fault reconfiguration function of the present invention, a solar array 1 is connected to the solar controller 1, a solar array 2 is connected to the solar controller 2, an anode switch between the solar controller 1 and a power supply bus is turned on, a cathode switch is turned off, a switch between the solar controller 2 and the power supply bus is turned on, an anode switch between the solar controller 2 and the power supply bus is turned off, a cathode switch between the solar controller 2 and the power supply bus is turned on, and a switch between the solar controller 3 is turned off, \8230 \\ 8230;, where the solar controller 1 and the solar controller 2 are connected in series and then operated in parallel with other solar controllers.
The system realizes the fault adjustment of the N solar controllers by controlling the on-off of the switches in the first switch group, the second switch group and the fourth switch group:
if the nth solar controller fails, the nth first switch and the nth second switch are controlled to be switched off, the rest first switches and the rest second switches are switched on, the N-1 fourth switches are controlled to be switched off, and the rest solar controllers except the failed nth solar controller work in parallel.
As shown in fig. 4, a schematic diagram of a solar controller 1 according to an embodiment of the satellite power system with a fault reconfiguration function of the present invention is shown in a cut-out mode, wherein a solar array 1 is connected to the solar controller 1, a solar array 2 is connected to the solar controller 2, two switches between the solar controller 1 and a power supply bus are disconnected, a switch between the solar controller 2 and the power supply bus is disconnected, two switches between the solar controller 2 and the power supply bus are closed, and a switch between the solar controller 3 is disconnected, \8230, an \8230, a failed solar controller 1 is cut off at this time, and the solar controllers 2,3, \8230, an \8230anda parallel operation are performed.
The system further comprises:
a fifth switch group comprising M-1 fifth switches, wherein the mth fifth switch is used for connecting the input positive electrode of the mth load with the input positive electrode of the (M + 1) th load;
wherein M is more than or equal to 1 and less than M-1.
The system realizes the adjustment of the connection modes of the M power modules and the load by controlling the on-off of the switches in the third switch group and the fifth switch group:
controlling the M third switches to be closed and the M-1 fifth switches to be opened, so that the M power modules respectively supply power to the corresponding M loads;
and controlling the mth third switch to be switched off, the rest of the third switches to be switched on, controlling the mth fifth switch to be switched on, and the rest of the fifth switches to be switched off, so that the (m + 1) th power module supplies power to the mth load and the (m + 1) th load, the mth power module stops working, and the rest of the power modules respectively supply power to the corresponding loads.
As shown in fig. 5, a schematic diagram of a power module 1 supplying power to a load 1 according to an embodiment of the satellite power system with a fault reconfiguration function of the present invention is shown, where a switch between the power module 1 and the load 1 is closed, a switch between the power module 1 and the load 2 is opened, a switch between the power module 2 and the load 2 is closed, and a switch between the power module 2 and the load 3 is opened, \8230 \ 8230;, where the power module 1 supplies power to the load 1, and the power module 2 supplies power to the load 2, \8230;.
As shown in fig. 6, a power module 2 of an embodiment of the satellite power system with a fault reconfiguration function according to the present invention supplies power to a load 1 and a load 2, a switch between the power module 1 and the load 1 is opened, a switch between the power module 1 and the load 2 is closed, a switch between the power module 2 and the load 2 is closed, and a switch between the power module 2 and the load 3 is opened, \8230 \ 8230;, the power module 1 supplies power to the load 1 and the load 2, and the power module 3 supplies power to the load 3, \8230;.
The system realizes the fault adjustment of the M power modules and the load by controlling the on-off of the switches in the third switch group and the fifth switch group:
and if the mth power module or the load fails, controlling the mth third switch to be switched off, closing the rest of the third switches, and controlling the M-1 fifth switches to be switched on, wherein the failed mth power module or the rest of the power modules except the load respectively supply power to the corresponding load.
As shown in fig. 7, a schematic diagram of load 1 cutting-off in an embodiment of the satellite power system with fault reconfiguration function according to the present invention is shown, where a switch between the power module 1 and the load 1 is opened, a switch between the power module 2 and the load 2 is closed, and a switch between the power module 2 and the load 3 is opened, \8230; \8230, where the fault power module 1 is cut off, the power module 2 supplies power to the load 2, and the power module 3 supplies power to the load 3, \8230; \.
The lithium battery switch matrix includes:
when the output power of the solar array is not greater than the set threshold value or is 0, the electric energy is stored, and power is supplied to a load;
the sixth switch group is composed of X multiplied by Y sixth switches which are connected with the X multiplied by Y lithium batteries in series in a one-to-one correspondence mode, and the seventh switch group is composed of X seventh switches which are connected with the X row lithium batteries and the sixth switch combination circuit in parallel.
The system realizes the fault adjustment of the X multiplied by Y lithium batteries through the on-off of the switches in the sixth switch group and the seventh switch group:
when the lithium batteries in the x-th row and the y-th column need to work, the corresponding sixth switches are controlled to be closed, the rest sixth switches are switched off, the seventh switch in the x-th row is controlled to be switched off, and the rest seventh switches are switched on;
wherein X is more than or equal to 1 and less than or equal to X, and Y is more than or equal to 1 and less than or equal to Y.
The lithium batteries are arranged in a matrix structure, each lithium battery is connected with one solid-state switch in series, and each row of lithium batteries is connected with one solid-state switch in parallel, so that sufficient standby batteries are provided for the system. The voltage of the power supply bus can be changed by changing the number of rows of lithium batteries.
As shown in fig. 8, which is an operation diagram of the 1 st column and 1 st column lithium battery of the satellite power system with the fault reconfiguration function according to an embodiment of the present invention, B11 in the first column battery is operated, B12 is in standby, and other columns are in standby. At this time, the row switch S10 is turned off, the other row switches are turned on, the switch S11 connected in series with the lithium battery B11 is turned on, and the other switches connected in series with the lithium battery are turned off.
As shown in fig. 9, which is a schematic diagram of the operation of the row 1 and column 2 lithium batteries of the satellite power system with the fault reconfiguration function according to an embodiment of the present invention, when a lithium battery B11 fails and needs to be activated, a row switch S10 is turned off, other row switches are turned on, a switch S12 connected in series with the lithium battery B12 is turned on, and other switches connected in series with the lithium battery are turned off.
As shown in fig. 10, which is a schematic diagram of the operation of the row 2 and column 1 lithium battery of the satellite power system with the fault reconfiguration function according to an embodiment of the present invention, when the row 1 lithium battery fails to operate, the lithium battery B21 in the second row needs to be started, at this time, the row switch S20 is opened, the other row switches are closed, the switch S21 connected in series with the lithium battery B21 is closed, and the other switches connected in series with the lithium battery are opened.
In the detailed process description of normal operation and fault switching of the lithium battery switch matrix in fig. 8-10, only one lithium battery is used, and in practical application, the number of the lithium batteries can be flexibly adjusted, and only the series switch of the lithium battery to be operated is turned on, the parallel switch of the lithium battery in the row is turned off, the series switches of the rest lithium batteries are turned off, and the parallel switches of the rest lithium batteries in the row are turned on. Therefore, the number of the lithium batteries accessed into the system can be selected according to the voltage requirement of the load, the satellite system can be applied to satellite systems with various voltage requirements, and the satellite system is flexible to control and wide in application.
The first switch, the second switch, the third switch, the fourth switch, the fifth switch, the sixth switch, and the seventh switch may be solid-state switches, or may be other controllable switches, which is not limited in the present invention.
As shown in fig. 11, which is a schematic structural diagram of a satellite power supply system in the prior art, it can be seen that a shunt regulator, a power distribution unit, a current limiting switch, and the like exist in the system, the system structure and the control process are complex, a vulnerable part is not used for standby, and the system fault recovery efficiency is low.
It can be clearly understood by those skilled in the art that, for convenience and brevity of description, the specific working process and related descriptions of the method described above may refer to the corresponding process in the foregoing system embodiment, and are not described herein again.
It should be noted that, the satellite power supply system and the method with the fault reconfiguration function provided in the foregoing embodiment are only illustrated by the division of the above functional modules, and in practical applications, the above functions may be distributed by different functional modules according to needs, that is, the modules or steps in the embodiments of the present invention are further decomposed or combined, for example, the modules in the foregoing embodiments may be combined into one module, or may be further split into multiple sub-modules, so as to complete all or part of the above described functions. Names of the modules and steps related in the embodiments of the present invention are only for distinguishing the modules or steps, and are not to be construed as unduly limiting the present invention.
The terms "first," "second," and the like are used for distinguishing between similar elements and not necessarily for describing or implying a particular order or sequence.
The terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
So far, the technical solutions of the present invention have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present invention is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the invention, and the technical scheme after the changes or substitutions can fall into the protection scope of the invention.

Claims (2)

1. A satellite power supply system with a fault reconstruction function is characterized by comprising the following modules:
the N solar arrays are used for converting the acquired light energy into electric energy;
the solar energy controllers are in one-to-one correspondence with the N solar arrays, when the output power of the solar arrays is greater than a set threshold value, the solar energy controllers work in a boosting mode to supply power to the load and charge lithium batteries in the lithium battery switch matrix, when the output power of the solar arrays is not greater than the set threshold value, the solar energy controllers work in an MPPT mode and supply power to the load together with the lithium batteries in the lithium battery switch matrix, and when the output power of the solar arrays is 0, the solar energy controllers stop working and supply power to the load by the lithium batteries in the lithium battery switch matrix;
the M power modules correspond to the loads of the power supply system one by one and are used for converting the bus voltage into the rated power supply voltage of the corresponding load;
the lithium battery switch matrix comprises an X row and Y column lithium battery matrix consisting of X multiplied by Y lithium batteries, a sixth switch group consisting of X multiplied by Y sixth switches connected in series with the X multiplied by Y lithium batteries in a one-to-one correspondence manner, and a seventh switch group consisting of X seventh switches connected in parallel with the X row lithium batteries and the sixth switch combined circuit, wherein when the output power of the solar array is greater than a set threshold, the electric energy is stored, and when the output power of the solar array is not greater than the set threshold or is 0, the electric energy is supplied to a load;
the first switch group and the second switch group comprise N first switches and N second switches, and the first switch group and the second switch are respectively used for connecting the output positive electrode of each solar controller with the positive electrode of the bus and connecting the output negative electrode of each solar controller with the negative electrode of the bus;
the third switch group comprises M third switches and is used for connecting the output positive electrode of each power module with the positive electrode of the load;
the fourth switch group comprises N-1 fourth switches, and the nth fourth switch is used for connecting the output cathode of the nth solar controller with the output anode of the (N + 1) th solar controller; wherein N is more than or equal to 1 and less than N-1;
the fifth switch group comprises M-1 fifth switches, and the mth fifth switch is used for connecting the input positive electrode of the mth load with the input positive electrode of the (M + 1) th load; wherein M is more than or equal to 1 and less than M-1;
the system realizes the connection mode and fault adjustment of the N solar controllers by controlling the on-off of the switches in the first switch group, the second switch group and the fourth switch group:
controlling the N first switches and the N second switches to be closed and controlling the N-1 fourth switches to be opened, so that the N solar controllers work in parallel;
controlling the n +1 th first switch and the n second switch to be switched off, closing the rest first switches and second switches, controlling the n fourth switch to be switched on and off, and switching the rest fourth switches off, so that the n solar controller is connected with the n +1 th solar controller in series and then connected with the other solar controllers in parallel to work;
if the nth solar controller fails, controlling the nth first switch and the nth second switch to be switched off, closing the rest first switches and the rest second switches, controlling the N-1 fourth switches to be switched off, and connecting the rest solar controllers except the failed nth solar controller in parallel;
the system realizes the connection mode and fault adjustment of the M power modules and the load by controlling the on-off of the switches in the third switch group and the fifth switch group:
controlling the M third switches to be closed and the M-1 fifth switches to be opened, so that the M power modules respectively supply power to the corresponding M loads;
controlling the mth third switch to be switched off, the rest of the third switches to be switched on, controlling the mth fifth switch to be switched on, and switching the rest of the fifth switches to be switched off, so that the (m + 1) th power module supplies power to the mth load and the (m + 1) th load, the mth power module stops working, and the rest of the power modules respectively supply power to corresponding loads;
if the mth power module or the load fails, controlling the mth third switch to be switched off, closing the rest of the third switches, and controlling the M-1 fifth switches to be switched on, wherein the failed mth power module or the rest of the power modules except the load respectively supply power to the corresponding loads;
the system realizes the fault adjustment of the X multiplied by Y lithium batteries through the on-off of the switches in the sixth switch group and the seventh switch group:
when the lithium batteries in the x-th row and the y-th column need to work, the corresponding sixth switches are controlled to be closed, the rest sixth switches are controlled to be opened, the seventh switches in the x-th row are controlled to be opened, and the rest seventh switches are controlled to be closed; wherein X is more than or equal to 1 and less than or equal to X, and Y is more than or equal to 1 and less than or equal to Y.
2. The satellite power system with fault reconfiguration capability according to claim 1, wherein said switches are solid state switches.
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