WO2000074200A1 - Systeme de chargement et de dechargement de batterie - Google Patents

Systeme de chargement et de dechargement de batterie Download PDF

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Publication number
WO2000074200A1
WO2000074200A1 PCT/GB2000/002038 GB0002038W WO0074200A1 WO 2000074200 A1 WO2000074200 A1 WO 2000074200A1 GB 0002038 W GB0002038 W GB 0002038W WO 0074200 A1 WO0074200 A1 WO 0074200A1
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WO
WIPO (PCT)
Prior art keywords
battery
current
voltage
main bus
charge
Prior art date
Application number
PCT/GB2000/002038
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English (en)
Inventor
Alan Henry Weinberg
Original Assignee
Alan Henry Weinberg
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Alan Henry Weinberg filed Critical Alan Henry Weinberg
Publication of WO2000074200A1 publication Critical patent/WO2000074200A1/fr

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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

Definitions

  • This invention concerns the interface of a rechargeable battery to a current source such as a solar cell array (SA) .
  • SA solar cell array
  • the invention particularly envisages the use of a Sequential Switching Shunt Regulator (S 3 R) as described by US 4186336 (Weinberg) (Reference 1) and the applicant's earlier application WO 99/28801 (Reference 2) but it can be used to improve the design of any application that uses a SA and rechargeable battery.
  • S 3 R Sequential Switching Shunt Regulator
  • Such circuits are used, for instance, m providing electrical power to apparatus which is dependent on solar power but which also includes a battery to store energy. This stored energy provides power when the solar power is not available or during a peak power demand, when the solar-generated power alone is not sufficient.
  • a prime example is satellites which of course require power all the time, even when in shadow (eclipse) .
  • the switching between the two sources necessitates additional components, resulting m an additional mass for the system; moreover it entails inherent inefficiencies m the charging and discharging process, which m turn means that the battery ana SA have to be larger than they would have been without: these losses.
  • the background of systems of the type in question will now be described.
  • I SA I SC ⁇ to a point D
  • MPP Maximum Power Point
  • One prior-art method used to charge the battery from the SA is to connect the SA directly across the battery as in Fig. 2.
  • a single dedicated SA section 400 charges the battery 203 as required.
  • the open-circuit voltage of the SA at point G (V oc ) must always be greater than that of the battery to maintain battery charge.
  • V oc the open-circuit voltage of the SA at point G
  • the battery and SA are highly variable in voltage when in use the battery voltage must be designed to be well below that of the SA open- circuit voltage V oc .
  • Working on this part of the SA characteristic also has the advantage that, with the current constant, it is easier to control the state of charge of the battery.
  • the disadvantage of this simple method of battery charge is that the voltage of the SA is always fixed (clamped) to that of the battery, as shown by line 31 of Fig. 1 which might be considerably less than the open-circuit voltage V oc .
  • This wastes the potential power (power I SA *V SA ) that the SA can supply since it could work at a higher voltage and supply the same current.
  • the maximum power (V MPP *I MPP ) that the SA can supply is somewhere between the points D and F on the SA characteristic (point E) .
  • the power wasted will be approximately the ratio of the voltage of the battery to the voltage at the maximum power point V ⁇ pp (since the currents at V B and V MPP are approximately the same) . For example, if V B is one half of V MPP then approximately half the maximum potential power of the SA is wasted .
  • Fig. 3 shows a more complex single SA section used to charge the battery as before but now with a series switch 207 between the SA and the battery and a diode 205 between the SA and the bus.
  • This series switch 207 is used to switch the battery charging current on and off .
  • the diode provides a path for the SA current not used for battery charge to supply the main bus which has the load connected to it . The path from the battery to the bus is not shown.
  • the switch is ON the SA voltage is clamped, as previously, to that of the battery (line 31 in Fig. 1) and the diode 205 is reverse-biased.
  • the invention aims to provide a still more efficient, less complex and lower-mass solution for the electronic power equipment needed to charge and discharge the battery.
  • a battery charge and discharge regulator including: a battery charge section for providing a connection between a current source and a rechargeable battery in order to recharge the battery; and a power supply section for connecting the current source to a load via a main bus in such a way that the current source is constrained to supply current substantially at the voltage of the main bus; characterised in that the charging section incorporates a voltage converter capable of allowing the current source to charge the battery at a voltage independent of that of the battery; and in that the charge and discharge regulator further comprises a current controller to ensure that the current source when supplying current always supplies some of this current to the main bus.
  • the power supply section can advantageously include a diode in the connection line from the current source to the load.
  • the presence of this diode means that the current source can operate substantially at the main bus voltage when supplying power to the main bus, and hence at the maximum available efficiency, even when it is also charging the battery, but is isolated from the bus as regards reverse currents, thus preventing failure propagation if a short-circuit occurs in the voltage converter, for instance.
  • the voltage converter can be any suitable kind, though it is preferably a switching converter; it can be either of the buck or of the boost type.
  • DC/DC converters reference may be made to The Electronics Handbook, ed. J C Whitaker, CRC Press/ IEEE Press 1996, pages 991-1002.
  • the controller for ensuring that the current source always supplies current to the mam bus can use a sensor that detects a predetermined condition, and on its detection disconnects the current source from the battery.
  • a suitable condition would be that the current I MB from the source to the main bus approaches zero. This ensures that the current source cannot become clamped to the battery.
  • the sensor can be simply a voltage detector connected across an element in the power supply section, advantageously across the diode as mentioned above, and can be appropriately amplified.
  • the aim is to operate the SA section essentially at the mam bus voltage, when supplying a low impedance voltage source like a battery; to this end one controls the charge current into the battery so that it is less than that of the output current of the current source. This means that some current always flows through the diode and therefore the current source is voltage- clamped to the ma bus voltage V MB (less 1 diode drop)
  • Fig. 1 shows a typical solar array (SA) characteristic
  • Fig. 2 shows a prior-art method of battery charging using a SA
  • Fig. 3 shows a battery charge method used m reference 2
  • Fig. 4 illustrates the first embodiment of the invention
  • Fig. 5 shows a second embodiment of the invention ,-
  • Fig. 6 illustrates a third embodiment of the invention:
  • Fig. 7 shows the third embodiment m more detail
  • Fig. 8 shows a variant of the third embodiment of the invention for the case where the voltage of the SA (V SA ) is less than the voltage of the battery (V B ) ;
  • Fig. 9 shows a further variant of the third embodiment for the case of V SA ⁇ or > V B ;
  • Fig. 10 shows a complete power system using the third embodiment
  • Fig. 11 shows a prior art system for an unregulated (battery) ma bus
  • Fig. 12 shows a complete power system applying the invention to the case of an unregulated (battery) ma bus .
  • the invention aims to overcome the battery voltage clamp problem by making the battery charge sections operate at a voltage independent of the battery voltage, even for the battery charge case. This will require fewer SAs , which m turn reduces mass and cost.
  • Fig. 4 schematically illustrates tne first principle involved.
  • the SA 200 (again, crly one section is considered for simplicity) is operated on the constant -current part of its characteristic .
  • a DC-to-DC (switching) converter 206 s placed series between the SA section and the battery, m a charging section Ch of the circuit, to isolate the SA from the constant voltage of the battery.
  • the input current to this converter (I B ) can now be controlled, m such a way that it is essentially always less than the SA current (I SA ) .
  • a simple DC-to-DC (battery charge) converter 206 of the buck type (step- down) is shown, but many other converter topologies can be used.
  • This converter consists essentially of a switch 207, a diode 201 and an inductor 204.
  • the switch 207 When the switch 207 is OFF, current flows though the diode 205 to supply the main bus voltage and the voltage of the SA at point S is one diode drop above that of the main bus.
  • the switch 207 is closed the current I B increases at a rate (V SA -V B )/ ' !_ , where L is the inductance 204, until it is equal to I SA . At this point the current through the diode 205 is equal to zero and therefore the voltage across the diode drops to zero.
  • This zero-voltage condition is detected by the comparator 208 which changes state at its output to switch OFF the switch 207; when this happens all the SA current I SA flows through the diode 205.
  • the SA voltage is kept essentially at the voltage of the main bus for any positive value of SA current.
  • the SA current therefore does not have to be measured or predicted.
  • the stored energy in the inductor 204 causes the diode 201 to conduct and the inductor current to continue to charge the battery, but now with a current that decreases approximately at a rate of (V B /L) . After some delay, the converter control signal will switch 207 ON again in order to repeat the cycle .
  • Another advantageous feature, used in a third embodiment of the invention, is to make the DC/DC converter, placed between the SA section and the battery, a reversible one; that is, it has to be capable of supplying power to charge the battery from the SA in one direction and of supplying power from the battery to the main bus in the other direction. Th s enables the converter that would otherwise be needed tc provide power from the battery to the main bus to b ⁇ omitted.
  • the SA sections charge the battery until a peak power load demand occurs; by the action of the main error amplifier (MEA) for the main bus voltage regulation and the domain control (see reference 2 for details) the battery charge current is decreased in order to supply extra main bus power.
  • MEA main error amplifier
  • Fig. 6 shows the topology of Fig. 5 in its reversible form, including the active switch 501.
  • Fig. 7 shows (schematically) in more detail the reversible DC/DC converter 701. The current magnitude and direction are controlled by the amplitude and sign of the MEA signal 24, which tells the circuit what (total) current is needed.
  • the converter current is controlled by the current feedback loop, consisting of a comparator 90 that compares a proportion of the MEA signal with the voltage across a current sense resistor 81, in series with the inductor 204.
  • the comparator senses when the inductor current is equal to the target value demanded by the MEA signal and controls the active switches, i.e. the power FETs 207 and 501, in order to maintain the MEA target current.
  • This operation is interrupted by the comparator 208 to switch off the FET 207, if its current demand exceeds the current produced by the SA.
  • the Nand gates 80 having opposite outputs are to make sure that when 207 is ON 507 is OFF, and when 507 is ON 207 is OFF.
  • the comparator 208 could be replaced by any suitable amplifier such as a transistor. It acts to override the MEA feedback loop by limiting the current supplied to the battery from the SA.
  • the advantage of this design is the following: a) The battery charge and discharge regulator is combined in one reversible DC/DC converter, which means fewer components than if two separate converters were used; b) This reversible DC/DC converter operates from a single section of the SA isolated by a diode 205 as shown m Figs. 6 and 7. This allows the design to be much simpler than one that has to operate from the mam bus. This is because failure modes when operating m this way are less critical to the mam bus.
  • the converter can fail by a short circuit to the battery (short circuit failure of 207) and this will result m one charge section being permanently connected to the battery, whereas, for a DC/DC converter that is connected directly to the mam bus or to the total SA, such a short would cause a total loss of the satellite unless some over-current protection is used at its input, which requirement complicates the design considerably.
  • Another example of a fault is a short-circuit to ground at the input to the charge converter, which the example shown would cause a loss of one section of the total SA (typically 7% of the total power) whereas with the prior art this failure would cause total loss of the SA power and therefore the spacecraft.
  • the charge section current can be diverted from battery charge to the ma bus and if this current is not sufficient to satisfy the load demand the battery can supply extra current by operating the DC/DC converter m battery discharge mode
  • the battery voltage is above that of the mam bus.
  • the above discussion has been for the case where the battery voltage is below tnat of the mam bus.
  • Fig. 8 shows one well known type of converter that has a higher battery voltage.
  • switches 601 and 607 are m antiphase, controlled by the comparator 208, and the inductor 604 is on the SA side of both switches.
  • the technique is applied to the case where the battery voltage can be below or above the ma bus voltage as its voltage varies .
  • the advantages of using a DC/DC converter that can interface with a battery whose voltage can be above or below the main bus voltage is that an independent choice can now be made of the main bus and battery voltages which can give a more efficient and lighter design.
  • Fig. 10 shows a complete power system showing the set of SA sections 200 charging the battery and the set of sections 200a used only for supplying the main bus.
  • a typical satellite might require a 6 KW array, perhaps ten sections of 600 W each, with perhaps four of them charging the battery.
  • the battery 203 is charged from the charge SA sections 200 through the DC/DC converters 701, connected in parallel, with a current determined by the battery control logic 124 and the signal of the MEA (Am, 57) .
  • These battery charge SA sections are also used to satisfy transient peak power demands, by the use of domain control comparators 121 and 122 as explained previously and in Reference 2.
  • the DC/DC converters 701 are of the type given in Fig.
  • the main SA sections, 703, are regulated by a S 3 R controller 501 and a feedback amplifier, the MEA amplifier 57 (as explained in reference 1 and 2) , to control a main bus voltage supplying the load 89 and a main bus capacitor 53.
  • the sixth embodiment of the invention is to cover the case when it is an advantage to operate the load directly across the battery.
  • This configuration is normally used when there is high transient peak power demand by the load.
  • the voltage supplied to the load depends upon the charge or discharge state of the battery and gives a voltage variation of about 50%.
  • the advantage of the technique is that no DC/DC converters with their efficiency and mass penalty are required between the battery and the load. This penalty can be very high for the case of high peak power demand, even if the duration of that power demand is short, because the converters must be sized for the peak power.
  • the prior-art power system configuration is normally known as the unregulated bus and is shown m Fig. 11.
  • the total SA 400 is connected together (i.e. no discrete SA sections) and all the DC-to-DC converters 151 are connected m parallel to supply power to the battery 203 and the load 301 during sunlight.
  • the battery provides the power for transient peak power demand and eclipse operation.
  • the input current to the DC- to-DC converters is adjusted by the logic control circuit 156 m such a way that the SA operates at its maximum power point.
  • the DC-to-DC converters have to be designed so that any failure of their electronic components cannot present an overcurrent to the SA This failure case would take the SA away from its maximum power point and could result m the SA having not enough power to supply the load and charge the battery. This failure could cause a total loss of the spacecraft and must be avoided To provide protection against this failure it is normal for each DC-to-DC converter to have a current limiter connected to its input.
  • this current limiter operates, to protect the SA from going under voltage, by limiting that current or switching OFF the failed DC-to-DC converter.
  • This input current limiter complicates the design somewhat. Since the mass and cost of these converters is already high any possibility of reducing them is important .
  • the sixth embodiment of the invention avoids the use of this input current limiter for these DC-to-DC converters.
  • This is illustrated by Fig. 12.
  • the total SA is split up into sections, 200, and each section charges the battery through a DC/DC converter 701 of the type illustrated in Fig. 5 (buck) .
  • the buck converter is chosen for the case of the SA voltage always being above that of the battery. If it is below it, or can be either side of it, the appropriate converter should be used.
  • the diodes 205 provide a path for the current not used for charging the battery and for supplying load current, to charge a capacitance 104.
  • a converter 704 Connected to this capacitance is a converter 704 of the same type as the charging converters 701, but with the addition of input current protection 703 and redundant components, so that the failure of any one single component does not affect its operation significantly.
  • An amplifier 801 is used in a feedback loop to vary the input current of this converter at the point 802 where the diodes 205 are connected to it, so as to control the SA voltage to be at its maximum power point, plus one diode drop due to the diode 205.
  • the converter 704 also charges the battery.
  • the SA will operate at its MPP if the load and battery charge power demand is high- enough. If this power demand is less than the maximum power the SA can produce then the current in the diodes 205 increases. This increase is absorbed by the converter 704 until its current limit operates, at which point it can absorb no more current . This forces the SA to operate above its maximum power point voltage on the SA characteristic (line E to G in Fig.l) . This reduces the output current of the SA until a balance is achieved where the SA power is equal to that demanded by the load. The only system impact is a slightly higher SA voltage (about 10%) .

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)

Abstract

L'invention concerne un régulateur de chargement et de déchargement de batterie, comprenant une section de chargement de batterie Ch, connectant une source de courant (200) et une batterie rechargeable (203) afin de recharger la batterie. L'invention comprend également une section d'alimentation de courant M servant à connecter la source de courant (200) à une charge (203) via un bus principal (302), d'une manière telle que la source de courant est contrainte de générer un courant dont la tension est sensiblement identique à celle du bus principal. De plus, la batterie peut également être chargée sans modifier la tension des sections de chargement. Pour cela, on incorpore dans la section de chargement un convertisseur (206) de tension qui permet à la source de courant de charger la batterie à une tension indépendante de celle de la batterie. L'invention est également pourvue d'un contrôleur de courant (298) servant à assurer que la source de courant, lorsqu'elle génère du courant, fournit toujours une quantité de ce courant au bus principal via une diode (205), maintenant ainsi la source de courant à la tension du bus principal, à l'exception de la baisse de la diode.
PCT/GB2000/002038 1999-05-27 2000-05-26 Systeme de chargement et de dechargement de batterie WO2000074200A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9912462.0 1999-05-27
GBGB9912462.0A GB9912462D0 (en) 1999-05-27 1999-05-27 Battery charging system

Publications (1)

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WO2000074200A1 true WO2000074200A1 (fr) 2000-12-07

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003107722A2 (fr) * 2002-06-13 2003-12-24 Koninklijke Philips Electronics N.V. Systeme d'eclairage autonome a l'etat solide
NL2004202C2 (nl) * 2010-02-05 2011-08-08 Marijn Bartold Berk Batterijlader.
WO2011096806A3 (fr) * 2010-02-05 2012-01-26 Marijn Bartold Berk Chargeur de batterie
WO2011098471A3 (fr) * 2010-02-10 2012-09-07 Futuree Fuel Cell Solutions Gmbh Système d'alimentation en énergie comprenant une source de courant à régénération et procédé pour faire fonctionner un système d'alimentation en énergie
US8563845B2 (en) 2006-04-06 2013-10-22 Carmanah Technologies Corp. Adaptive solar powered system
CN103472884A (zh) * 2013-08-14 2013-12-25 浙江工业大学 一种光伏阵列全局最大功率点跟踪方法
CN104142703A (zh) * 2014-08-18 2014-11-12 南京航空航天大学 一种适用于差异性光伏单元串联电路的输出功率获取方法
CN103955253B (zh) * 2014-05-05 2015-08-26 合肥工业大学 基于功率闭环扫描的光伏阵列多峰值最大功率点跟踪方法
CN105159389A (zh) * 2015-09-14 2015-12-16 潍坊学院 一种基于区间递减的光伏阵列最大功率点跟踪方法
WO2017177301A1 (fr) * 2016-04-15 2017-10-19 Dpl Science Inc. Module d'alimentation électrique pour engin spatial
US10910834B2 (en) 2003-05-28 2021-02-02 Solaredge Technologies Ltd. Power converter for a solar panel
CN112531648A (zh) * 2020-10-30 2021-03-19 国网山东省电力公司烟台供电公司 一种蓄电池组短路联切保护装置及其保护方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3419779A (en) * 1965-08-09 1968-12-31 Westinghouse Electric Corp System for removing a bad battery from charging circuit
US5233287A (en) * 1992-05-05 1993-08-03 Space Systems/Loral Current limiting bilateral converter having a ground referenced current sensor
US5327071A (en) * 1991-11-05 1994-07-05 The United States Of America As Represented By The Administrator Of The National Aeronautics & Space Administration Microprocessor control of multiple peak power tracking DC/DC converters for use with solar cell arrays
US5359280A (en) * 1992-01-10 1994-10-25 Space Systems/Loral Bilateral power converter for a satellite power system
US5869948A (en) * 1997-05-05 1999-02-09 Hughes Electronics Corporation Unidirectional battery charge/discharge controller for a regulated electrical bus system with a solar current source

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3419779A (en) * 1965-08-09 1968-12-31 Westinghouse Electric Corp System for removing a bad battery from charging circuit
US5327071A (en) * 1991-11-05 1994-07-05 The United States Of America As Represented By The Administrator Of The National Aeronautics & Space Administration Microprocessor control of multiple peak power tracking DC/DC converters for use with solar cell arrays
US5359280A (en) * 1992-01-10 1994-10-25 Space Systems/Loral Bilateral power converter for a satellite power system
US5233287A (en) * 1992-05-05 1993-08-03 Space Systems/Loral Current limiting bilateral converter having a ground referenced current sensor
US5869948A (en) * 1997-05-05 1999-02-09 Hughes Electronics Corporation Unidirectional battery charge/discharge controller for a regulated electrical bus system with a solar current source

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003107722A3 (fr) * 2002-06-13 2004-07-22 Koninkl Philips Electronics Nv Systeme d'eclairage autonome a l'etat solide
JP2005530325A (ja) * 2002-06-13 2005-10-06 コーニンクレッカ　フィリップス　エレクトロニクス　エヌ　ヴィ 独立型固体照明システム
WO2003107722A2 (fr) * 2002-06-13 2003-12-24 Koninklijke Philips Electronics N.V. Systeme d'eclairage autonome a l'etat solide
US10910834B2 (en) 2003-05-28 2021-02-02 Solaredge Technologies Ltd. Power converter for a solar panel
US11075518B2 (en) 2003-05-28 2021-07-27 Solaredge Technologies Ltd. Power converter for a solar panel
US11476663B2 (en) 2003-05-28 2022-10-18 Solaredge Technologies Ltd. Power converter for a solar panel
US11824398B2 (en) 2003-05-28 2023-11-21 Solaredge Technologies Ltd. Power converter for a solar panel
US11658508B2 (en) 2003-05-28 2023-05-23 Solaredge Technologies Ltd. Power converter for a solar panel
US11817699B2 (en) 2003-05-28 2023-11-14 Solaredge Technologies Ltd. Power converter for a solar panel
US8779625B2 (en) 2006-04-06 2014-07-15 Carmanah Technologies Corp. Adaptive solar powered system
US8563845B2 (en) 2006-04-06 2013-10-22 Carmanah Technologies Corp. Adaptive solar powered system
WO2011096806A3 (fr) * 2010-02-05 2012-01-26 Marijn Bartold Berk Chargeur de batterie
NL2004202C2 (nl) * 2010-02-05 2011-08-08 Marijn Bartold Berk Batterijlader.
CN102884698A (zh) * 2010-02-10 2013-01-16 未来燃料电池解决方案有限公司 有可再生电源的能量供应系统和操作能量供应系统的方法
WO2011098471A3 (fr) * 2010-02-10 2012-09-07 Futuree Fuel Cell Solutions Gmbh Système d'alimentation en énergie comprenant une source de courant à régénération et procédé pour faire fonctionner un système d'alimentation en énergie
CN103472884B (zh) * 2013-08-14 2015-10-07 浙江工业大学 一种光伏阵列全局最大功率点跟踪方法
CN103472884A (zh) * 2013-08-14 2013-12-25 浙江工业大学 一种光伏阵列全局最大功率点跟踪方法
CN103955253B (zh) * 2014-05-05 2015-08-26 合肥工业大学 基于功率闭环扫描的光伏阵列多峰值最大功率点跟踪方法
CN104142703B (zh) * 2014-08-18 2015-12-02 南京航空航天大学 一种适用于差异性光伏单元串联电路的输出功率获取方法
CN104142703A (zh) * 2014-08-18 2014-11-12 南京航空航天大学 一种适用于差异性光伏单元串联电路的输出功率获取方法
CN105159389A (zh) * 2015-09-14 2015-12-16 潍坊学院 一种基于区间递减的光伏阵列最大功率点跟踪方法
CN105159389B (zh) * 2015-09-14 2016-09-21 潍坊学院 一种基于区间递减的光伏阵列最大功率点跟踪方法
WO2017177301A1 (fr) * 2016-04-15 2017-10-19 Dpl Science Inc. Module d'alimentation électrique pour engin spatial
US10421561B2 (en) 2016-04-15 2019-09-24 Dpl Science Inc. Power supply module for spacecraft
CN112531648A (zh) * 2020-10-30 2021-03-19 国网山东省电力公司烟台供电公司 一种蓄电池组短路联切保护装置及其保护方法
CN112531648B (zh) * 2020-10-30 2023-01-13 国网山东省电力公司烟台供电公司 一种蓄电池组短路联切保护装置及其保护方法

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