CN107482747A - The method of work of spacecraft power supply system - Google Patents
The method of work of spacecraft power supply system Download PDFInfo
- Publication number
- CN107482747A CN107482747A CN201710545361.8A CN201710545361A CN107482747A CN 107482747 A CN107482747 A CN 107482747A CN 201710545361 A CN201710545361 A CN 201710545361A CN 107482747 A CN107482747 A CN 107482747A
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- CN
- China
- Prior art keywords
- storage battery
- energy storage
- solar cell
- battery unit
- work
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
- H02J7/0013—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries acting upon several batteries simultaneously or sequentially
- H02J7/0014—Circuits for equalisation of charge between batteries
-
- 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
-
- 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
Abstract
A kind of method of work of spacecraft power supply system, the power-supply system have two solar cell wings, the energy storage battery unit of multiple grid-connected work, and wherein at least one energy storage battery unit receives the charging current of two solar panels, including：When solar cell wing failure occurs, cut off the energy storage battery unit being connected with the fail battery wing, and the discharge current ratio of the energy storage battery unit of the solar cell wing charging current to receiving normal work is adjusted, to cause the rechargeable energy of the energy storage battery of the reception normal work solar cell wing charging current and discharge energy to realize individual pen charge and discharge electric equilibrium.
Description
Technical field
The present invention relates to space technology field, more particularly to the method for work of spacecraft power supply system.
Background technology
Photovoltaic power supply system is the main power source system of spacecraft, and it is all to be widely used in satellite, manned spaceship, space station etc.
The spacecraft of more in-orbit longtime running.Photovoltaic power supply system typically (is filled by the solar cell wing (generating equipment), power supply unit
Electricity, electric discharge and voltage stabilizing adjustment equipment), the group such as energy storage battery unit (energy storage device) and emergency cell group (emergency service equipment)
Into.
Spacecraft Launch is entered the orbit after the normal expansion of the solar cell wing, and the power source of power-supply system just fully relies on sun electricity
Chi Yi is to the photovoltaic conversion ability of solar irradiation, and in area of illumination, the solar cell wing converts light energy into electric energy, a part of electric energy warp
Power supply unit to energy storage battery unit carry out charging energy-storing, while another part electric energy through power supply unit export to
Spacecraft power supply for electrical equipment；In shadow region, by energy storage battery unit by the electric discharge output of power supply unit to spacecraft
Power supply for electrical equipment.
Generally in typical power system design, solar cell wing generating path → power supply unit controls to adjust logical
Road → energy storage battery unit charge and discharge electric pathway has corresponding relation, i.e., in 2 solar cell wings, the spacecraft electricity of multiple units
In the system of source, one of wing fills by (or multiple) power supply unit to multiple energy storage battery units
Electricity, another solar cell wing charge by other power supply units to other energy storage battery units.
The a certain solar cell wing failure under conditions of, using a certain not deployed failure of the solar cell wing after entering the orbit as
Example, the generating source loss half of power-supply system and the characteristics of be not easily repaired with on-orbit fault after the failure occurs, power supply system
When system must account for on-orbit fault generation in design, the failure reconfiguration ability of power-supply system.The sun that residue is normally deployed
Cell wing should be able to realize the normal charge and discharge regulation to energy storage battery unit, and be aided with by the reconstruct of power supply unit
Spacecraft electrical power consumed is reduced to platform lowest power consumption demand to maintain in-orbit long-term normal operation.
The content of the invention
It is an object of the invention to provide a kind of method of work of spacecraft power supply system, solar panel can occur
During on-orbit fault, power supply unit reconstruct is carried out, realizes the charge and discharge electric equilibrium of energy storage battery.
In order to solve the above problems, the present invention provides a kind of method of work of spacecraft power supply system, the power-supply system
With two solar cell wings, the energy storage battery unit of multiple grid-connected work, wherein at least one energy storage battery unit connects
The charging current of two solar cell wings is received, including：
When solar cell wing failure occurs, the energy storage battery unit being connected with the fail battery wing is cut off, and it is right
The discharge current ratio for receiving the energy storage battery unit of normal work solar cell wing charging current is adjusted, to cause
The rechargeable energy and discharge energy for stating the energy storage battery unit for receiving normal work solar cell wing charging current realize individual pen
Charge and discharge electric equilibrium.
Alternatively, the energy storage battery unit number is 3, and one of energy storage battery unit receives two sun
The charging current of cell wing, the method for work also include：
In the normal mode of operation, when two solar cell wings are normal, the charging currents of three energy storage battery units it
Than for 1:1:1, the ratio between discharge current of three energy storage battery units is 1:1:1；Each energy storage battery unit individual pen energy
Balance.
Alternatively, for the energy storage battery unit for the charging current for receiving two solar cell wings, it is from two sun
The ratio between charging current that cell wing receives is 1：1.
Alternatively, the discharge current ratio is adjusted to, will be from two solar cells in a solar cell wing failure
The discharge energy that the wing receives the energy storage battery unit of charging current is reduced to suitable with rechargeable energy, i.e., discharge current is normal
The 1/2 of discharge current under mode of operation.
Compared with prior art, the present invention has advantages below：
The method of the present invention can carry out power supply unit reconstruct when solar cell wing on-orbit fault occurs, and realize
Remaining energy storage battery unit charge and discharge are balanced, and individual pen energy balance can be achieved, and (electric energy that i.e. shadow region releases is in illumination
Area can supplement completely, without charge less electricity), spacecraft can under single-blade fault mode in-orbit long-term normal operation.This
Invention implementation process need not intervene the normal operation of spacecraft, the Supply Security of spacecraft power supply system not impacted.
Brief description of the drawings
Fig. 1 is the structural representation of spacecraft power supply system under normal mode of operation.
Fig. 2 is structure of the spacecraft power supply system after failure reconfiguration under a solar cell wing fault mode in Fig. 1
Schematic diagram.
Embodiment
The present invention provides a kind of method of work of spacecraft power supply system, and the power-supply system has two solar cells
The wing, the energy storage battery unit of multiple grid-connected work, wherein at least one energy storage battery unit receive two solar cell wings
Charging current, including：
When solar cell wing failure occurs, the energy storage battery unit being connected with the fail battery wing is cut off, and it is right
The charging current and discharge current for receiving the energy storage battery unit of normal work solar cell wing charging current carry out balanced tune
It is whole, to cause the rechargeable energy of the energy storage battery unit of the reception normal work solar cell wing charging current and electric discharge energy
Amount realizes individual pen charge and discharge electric equilibrium.
Technical scheme is specifically described with reference to embodiment.Incorporated by reference to Fig. 1 and Fig. 2, Fig. 1 is normal
The structural representation of spacecraft power supply system under mode of operation.Fig. 2 is spacecraft under a solar cell wing fault mode in Fig. 1
Structural representation of the power-supply system after failure reconfiguration.
As shown in figure 1, spacecraft power supply system has two solar cell wings, the i.e. first solar cell wing and second sun
Cell wing, the first solar cell wing and the second solar cell wing are used for three energy storage battery unit charging (the first storages
Energy storage device unit, the second energy storage battery unit and the 3rd energy storage battery unit).Wherein, the 3rd energy storage battery unit
The charging current of two solar cell wings is received, the first solar panel stores to the first energy storage battery unit and the 3rd energy storage
Battery unit charges, and the second solar cell wing charges to the second energy storage battery unit and the 3rd energy storage battery unit.As
One embodiment, the first solar cell wing are controlled by the first power supply unit and the first energy storage battery unit and the 3rd are stored up
Energy storage device unit charges, the second solar cell wing by second source control unit allocation to the second energy storage battery unit and
3rd energy storage battery unit charges.
Because energy storage battery group unit quantity can be sized so as to multiple units, this implementation according to spacecraft electrical power consumed
Example carries out use-case explanation, including but not limited to 3 units with 3 units.
In the normal mode of operation, when two solar cell wings are normal, the charging currents of three energy storage battery units it
Than for 1:1:1, the ratio between discharge current of three energy storage battery units is 1:1:1；Each energy storage battery unit individual pen energy
Balance.
For the energy storage battery unit for the charging current for receiving two solar cell wings, it connects from two solar cell wings
The ratio between charging current of receipts is 1：1.
As shown in figure 1, the charging received as one embodiment, the first energy storage battery unit from the first solar cell wing
Electric current is IFill, the charging current that the 3rd energy storage battery unit receives from the first solar cell wing is 0.5IFill, the 3rd energy storage electric power storage
The charging current that pond unit receives from the second solar cell wing is 0.5IFill, the second energy storage battery unit is from the second solar cell
The charging current that the wing receives is IFill。
As one embodiment, in the second solar cell wing failure, first by second source control unit cut-out with
The energy storage battery unit (the second energy storage battery units are isolated) that the fail battery wing is connected, and pass through power supply
Control unit to adjust the discharge current ratio of the 3rd energy storage battery unit, make discharge energy and received rechargeable energy phase
When；Also i.e. by under normal mode of operation between the first energy storage battery unit and the 3rd energy storage battery unit 1：1 electric discharge ratio
2 be adjusted to after failure reconfiguration：Filling between 1 electric discharge ratio, with the first energy storage battery unit and the 3rd energy storage battery unit
Electric current ratio is identical.Power-supply system after failure reconfiguration, the energy storage battery group unit rechargeable energies of remaining 2 work and
Discharge energy is balanced, and individual pen energy balance can be achieved.
The failure reconfiguration adjustment ratio of above-mentioned discharge current can be designed according to the quantity and needs of unit, including but
It is not limited to the 2 of the present embodiment：1 ratio.Through the validation test of ground experiment room, simulated solar is distinguished using sun square formation simulator
Cell wing normal power generation mode and single-blade fault mode, the reply in-orbit single-blade failure solution of spacecraft power supply system of the present invention
Certainly scheme reasonable, test data show that power system failure reconstruct measure is effective, it is possible to achieve residue can under fault mode
Full charge of energy storage battery group unit is balanced with the rechargeable energy and discharge energy of the energy storage battery group of part charging,
Individual pen energy balance can be achieved.
To sum up, method of the invention can carry out power supply unit weight when solar panel on-orbit fault occurs
Structure, realize that the rechargeable energy of remaining energy storage battery unit and discharge energy are balanced, it is (i.e. cloudy that individual pen energy balance can be achieved
The electric energy that shadow zone releases can supplement completely in area of illumination, without charge less electricity), being aided with reduces spacecraft electrical power consumed to flat
Platform lowest power consumption demand, spacecraft can under single-blade fault mode in-orbit long-term normal operation.Implementation process of the present invention need not
Intervene the normal operation of spacecraft, the Supply Security of spacecraft power supply system impacted.
Therefore, the technical concepts and features of above-mentioned preferred embodiment only to illustrate the invention, its object is to allow be familiar with this
The personage of item technology can understand present disclosure and implement according to this, and it is not intended to limit the scope of the present invention.It is all
The equivalent change or modification made according to spirit of the invention, it should all be included within the scope of the present invention.
Claims (4)
1. a kind of method of work of spacecraft power supply system, the power-supply system has two solar cell wings, multiple grid-connected works
The energy storage battery unit of work, wherein at least one energy storage battery unit receive the charging current of two solar panels,
It is characterised in that it includes：
When solar cell wing failure occurs, the energy storage battery unit being connected with the fail battery wing is cut off, and to receiving
The discharge current ratio of the energy storage battery unit of the solar cell wing charging current of normal work is adjusted, described to cause
The rechargeable energy and discharge energy for receiving the energy storage battery of normal work solar cell wing charging current realize individual pen discharge and recharge
Balance.
2. the method for work of spacecraft power supply system as claimed in claim 1, it is characterised in that the energy storage battery unit
Number is 3, and one of energy storage battery unit receives the charging current of two solar cell wings, and the method for work is also wrapped
Include：
In the normal mode of operation, when two solar cell wings are normal, the ratio between charging current of three energy storage battery units is
1:1:1, the ratio between discharge current of three energy storage battery units is 1:1:1；Each energy storage battery unit individual pen energy balance.
3. the method for work of spacecraft power supply system as claimed in claim 2, it is characterised in that for receiving two sun electricity
The ratio between the energy storage battery unit of Chi Yi charging current, its charging current received from two solar cell wings are 1：1.
4. the method for work of spacecraft power supply system as claimed in claim 3, it is characterised in that the discharge current ratio is adjusted
It is whole to be, in a solar cell wing failure, the energy storage battery unit of charging current will be received from two solar cell wings
Discharge energy be reduced to it is suitable with rechargeable energy, i.e., discharge current be normal mode of operation under discharge current 1/2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201710545361.8A CN107482747A (en) | 2017-07-06 | 2017-07-06 | The method of work of spacecraft power supply system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710545361.8A CN107482747A (en) | 2017-07-06 | 2017-07-06 | The method of work of spacecraft power supply system |
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| CN107482747A true CN107482747A (en) | 2017-12-15 |
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| CN201710545361.8A Pending CN107482747A (en) | 2017-07-06 | 2017-07-06 | The method of work of spacecraft power supply system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112636444A (en) * | 2020-12-07 | 2021-04-09 | 上海卫星工程研究所 | Double-star combined spacecraft grid-connected power supply and distribution system with fully-regulated unified bus |
| CN113071717A (en) * | 2021-03-29 | 2021-07-06 | 上海空间电源研究所 | Space low-rail high-voltage power supply system supporting on-rail maintenance |
| US20230027611A1 (en) * | 2021-07-26 | 2023-01-26 | Realtek Semiconductor Corporation | Power supply device, power supply system and non-transitory computer-readable recording medium |
| TWI818593B (en) * | 2022-06-20 | 2023-10-11 | 新盛力科技股份有限公司 | Discharge balancing method for battery equipment |
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| CN104335694B (en) * | 2008-12-16 | 2013-03-13 | 上海宇航系统工程研究所 | One can back up formula solar cell array actuating device |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112636444A (en) * | 2020-12-07 | 2021-04-09 | 上海卫星工程研究所 | Double-star combined spacecraft grid-connected power supply and distribution system with fully-regulated unified bus |
| CN112636444B (en) * | 2020-12-07 | 2022-06-03 | 上海卫星工程研究所 | Double-star combined spacecraft grid-connected power supply and distribution system with fully-regulated unified bus |
| CN113071717A (en) * | 2021-03-29 | 2021-07-06 | 上海空间电源研究所 | Space low-rail high-voltage power supply system supporting on-rail maintenance |
| US20230027611A1 (en) * | 2021-07-26 | 2023-01-26 | Realtek Semiconductor Corporation | Power supply device, power supply system and non-transitory computer-readable recording medium |
| TWI818593B (en) * | 2022-06-20 | 2023-10-11 | 新盛力科技股份有限公司 | Discharge balancing method for battery equipment |
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Application publication date: 20171215 |