WO2009007591A2 - Procede et systeme de gestion de coupures d'alimentation electrique a bord d'un aeronef - Google Patents
Procede et systeme de gestion de coupures d'alimentation electrique a bord d'un aeronef Download PDFInfo
- Publication number
- WO2009007591A2 WO2009007591A2 PCT/FR2008/051140 FR2008051140W WO2009007591A2 WO 2009007591 A2 WO2009007591 A2 WO 2009007591A2 FR 2008051140 W FR2008051140 W FR 2008051140W WO 2009007591 A2 WO2009007591 A2 WO 2009007591A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- duration
- capacitor
- signal
- circuit
- power supply
- Prior art date
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F1/00—Details not covered by groups G06F3/00 - G06F13/00 and G06F21/00
- G06F1/26—Power supply means, e.g. regulation thereof
- G06F1/28—Supervision thereof, e.g. detecting power-supply failure by out of limits supervision
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F1/00—Details not covered by groups G06F3/00 - G06F13/00 and G06F21/00
- G06F1/26—Power supply means, e.g. regulation thereof
- G06F1/30—Means for acting in the event of power-supply failure or interruption, e.g. power-supply fluctuations
Definitions
- the invention relates to a system for managing the cuts in the power supply network of avionic equipment. This system is used to determine if the power cuts are short-lived or long-lasting and to turn off the on-board computer when the cut is long-lasting. The invention also relates to a method implemented by this system.
- the invention has applications in the field of aeronautics and, in particular, in the field of management of the electrical power on board an aircraft.
- short power cuts There are short power cuts. These short cuts have a duration of less than 5 seconds. Like the transparent cuts, these short cuts are related to the behavior of the power supply network. They are detected in flight. - There are also long cuts, whose duration is greater than 5 seconds. These long cuts occur on the ground when the aircraft is in the maintenance phase. These long cuts are used by the maintenance agents to repair, check or test certain equipment of the aircraft.
- the on-board computer turns off during the moment when it is not powered electrically.
- the computer must be restarted very quickly, that is to say, it must be able to perform as soon as the power is restored.
- the onboard computer also turns off during the moment when it is not powered electrically.
- the onboard computer must perform a series of tests, when it is back on, to check the general operation of the equipment.
- the aircraft is on the ground, in the maintenance phase, the computer can restart slowly by performing a series of tests, called self-tests.
- the timer (or timer, in English terms) must be electrically powered by the internal battery for the duration of a short break, about 5 seconds. If the power supply reappears before the end of the 5 seconds, then the computer restarts according to the fast procedure (without self-tests), the avionics equipment recommences on the power supply network, the time counter is reset and the internal battery is recharged.
- a long cutoff information is saved in a non-volatile memory.
- This memorization of the long cutoff information makes it possible to switch off the computer permanently for the duration of the long break, which makes it possible to reduce somewhat the power consumption of the equipment.
- this storage of the information in the non-volatile memory requires a permanent supply of said non-volatile memory as well as a programmable electronic component that manages this storage.
- the programmable component is relatively energy-intensive.
- the invention proposes a system and a method for measuring the duration of the break. supply through the discharge of a capacitor. During this discharge, the capacitor does not need to be electrically powered, which makes it possible to turn off the computer during the entire duration of the power failure. This measurement of the duration by discharge of a capacitor makes it possible to dispense with any internal power source.
- the invention relates to a method for managing an electrical power failure on board an aircraft, characterized in that it comprises the following operations:
- the method of the invention may also include one or more of the following characteristics:
- the capacitor is recharged as soon as an active switching signal is received at the input of a switch connected in series with the capacitor.
- the active switching signal is issued almost immediately when the duration of the cut is less than the threshold time.
- the active switching signal is emitted upon receipt of an end of backup signal.
- the measurement of the discharge time is obtained by comparing a value of the voltage at the terminals of the capacitor with the value of a reference voltage.
- the invention also relates to a system for managing a power cut on board an aircraft
- Management system for an electrical power failure on board an aircraft characterized in that it comprises:
- the system of the invention may comprise one or more of the characteristics following:
- the measuring circuit comprises a capacitor connected, on the one hand, to an input of a comparator and, on the other hand, to an auxiliary supply source via a switch.
- the management circuit comprises a programmable component able to receive an output signal from the measuring circuit, to transmit a backup signal to a central unit, to receive a signal for the end of the backup of the central unit, and to transmit a switching signal to the measuring circuit, the transmitted signals depending on the received signals.
- the measurement circuit and the management circuit are mounted on an electrical supply card of an on-board computer, the management circuit being able to communicate with a central unit.
- the invention also relates to an aircraft comprising a system as described above. Brief description of the drawings
- FIG. 1 diagrammatically represents the electronic circuit of the invention for managing a power supply interruption without an internal power supply.
- FIG. 2 represents a chronogram of the various signals encountered inside the electronic circuit of FIG. 1.
- the invention proposes a system and a method making it possible to manage power supply interruptions on board an aircraft so that the computer can be extinguished completely as soon as a power outage occurs. of the power supply network occurs, while allowing a measure of the duration of this power cut and, if necessary, a backup of the long cutoff information.
- the method of the invention proposes, when a power failure is detected, to measure the duration of the cut.
- the measurement of the duration of the break is obtained by measuring the discharge time of a capacitor.
- the discharge time of the capacitor is determined from the value of the voltage across this capacitor. This voltage value is compared with a reference voltage corresponding to a discharge duration of 5 seconds.
- the comparison of the voltages is equivalent to comparing the duration of the cutoff with a threshold duration, this threshold duration being for example 5 seconds.
- the capacitor voltage When the value of the capacitor voltage is greater than the reference voltage, it means that the cutoff is short. On the contrary, when the value of the capacitor voltage is lower than the reference voltage, it means that the cutoff is long. When a duration of less than 5 seconds is detected, the capacitor is recharged immediately in order to be able to measure the duration of a possible new break.
- the long cut information is saved as will be described later.
- the capacitor is only recharged after receiving an end of backup command.
- FIG. 1 An example of an electronic circuit for carrying out the method of the invention is shown in FIG. 1.
- This electronic circuit is mounted on a power supply card 1 of the aircraft's on-board computer.
- This electronic circuit comprises a circuit 2 for detecting a power failure.
- This detection circuit 2 is conventional, in accordance with the prior art. It will not be described in more detail in this application.
- This detection circuit 2 comprises an input 21 from the power supply network; it therefore receives the voltage of 28 Volts of the network.
- This detection circuit 2 also has an input 22 connected to ground.
- This circuit 2 is able to detect the presence, on its input 21, of a voltage of 28V. When no 28V voltage is detected, it means that there is a power failure in the network. In other words, the detection circuit 2 detects the power cuts. When the end of a break is detected, it sends a cutoff information to a circuit 3 information management.
- This information management circuit 3 comprises a programmable electronic component 31 incorporating a plurality of functionalities. This programmable component 31 is capable of receiving different information signals and transmitting signals of command, based on the signals received. This programmable component is a logical component that receives and transmits logic signals that can be active or inactive. The logic signals may have binary values 0 or 1. In the remainder of the description, it will be considered that an active logic signal has a binary value 1 and an inactive logic signal has a binary value 0, it being understood that the binary values can to be reversed.
- the programmable component 31 is connected by a switching output 32 to a circuit 4 for measuring the duration of the power failure.
- This measuring circuit 4 comprises a capacitor 41, able to charge energy and to discharge this energy later.
- the capacitor 41 is connected in series to a power source 44, for example an auxiliary source (Vaux).
- Vaux auxiliary source
- This auxiliary power source 44 has the role of charging under certain conditions the capacitor when the power network is not cut. The conditions of charge and discharge of the capacitor will be defined later.
- the capacitor 41 is connected to this auxiliary power source 44 via a switch 42 acting under the effect of the switching signal 32 (COM) transmitted by the programmable component 31. It is also connected, directly , to a voltage comparator 43.
- This voltage comparator 43 receives, on a first input 431, a reference voltage Vref and, on a second input 432, the discharge voltage of the capacitor 41, also called the residual voltage of the capacitor. It thus compares the voltage across the capacitor 41 with the reference voltage Vref.
- the comparator 43 has an output 433 connected to an input of the programmable component 31. This output 433 sends an information signal 33 (LEVEL) corresponding to the result of the comparison of the voltages.
- the signal transmitted at the output of the comparator 43 is a binary signal that can be active or inactive. When the capacitor voltage is higher than the reference voltage, the LEVEL signal is inactive (it is at 0). On the contrary, when the voltage of the capacitor is lower than the reference voltage, the signal LEVEL is active (it is at 1). This LEVEL signal 33 is transmitted to an input of the programmable component 31. As a function of this signal, the programmable component 31 transmits, immediately or later depending on the case, a switching signal COM active at the switch 42 of the measuring circuit 4.
- the programmable component 31 forces its output from switching 32 to 0.
- the switch 42 remains open. As long as the switch is open, the capacitor 41 discharges. The voltage across the capacitor 41 is then compared, by the comparator 43, with the reference voltage Vref.
- This reference voltage Vref can be, for example, 1 volt.
- the LEVEL signal obtained at the output 433 of the comparator 43 is at 0.
- the programmable component 31 sends, to the card 5 of the central unit of the onboard computer, called the CPU card, a signal 34 of long cutout LPF (Long Power Failure, in English terms) to 0.
- This inactive state of the signal LPF means that the cut was short.
- This LPF signal (active or inactive) is obtained by resetting the computer, that is to say by releasing the reset key of the computer.
- the programmable component 31 sends a switching signal COM at 1.
- the switch 42 closes.
- the capacitor 41 is then recharged by the auxiliary source 44. As soon as the capacitor is recharged, the system is ready to measure the duration of the next break.
- the capacitor has a capacity of the order of 10 microfarads.
- the capacity of the capacitor is chosen according to the cut-off time to be measured. For example, for a duration of 5 seconds, a capacitor of 10 microfarads can be used.
- the LEVEL signal obtained at the output 433 of the comparator 433 is at 1.
- the programmable component 31 sends, to the CPU 5 board, a long LPF cut signal at 1.
- This signal LPF active means that the power cut was long.
- the COM signal of the programmable component 31 remains inactive.
- the capacitor 41 remains unloaded. If a new power failure occurs, as the capacitor is not recharged, the system will always indicate that it is a long break. In other words, the long cutoff information is saved by the measuring circuit 4 because it can not make a measurement after said long break has been taken into account.
- the long cutoff information When the long cutoff information has been taken into account by the CPU board, it sends a RLPF (Reload Long Power Failure) long signal to the programmable component 31.
- This signal RLPF means, for the programmable component 31, that the long cutoff information has been taken into account and that the self-tests have been performed.
- This RLPF signal therefore means that the backup of the long break information is complete and that said long break information can be cleared.
- the programmable component 31 On receipt of this signal RLPF, the programmable component 31 emits a signal COM at 1.
- the switch 42 closes, which allows the capacitor 41 to recharge from the auxiliary source 44. The system is then ready again to measure a next break.
- the capacitor is charged and then remains charged.
- the power supply of the capacitor stops and the capacitor is discharged.
- the discharge time of the capacitor provides information on the duration of the power failure.
- the capacitor is recharged almost immediately after the end of the break.
- the cut is long, the long cutoff information is saved by the measuring circuit itself. The capacitor is then recharged as soon as the central unit 5 signals that the self-tests have been carried out.
- the central unit 5 knows that the cut is long and that self-tests must be performed when restarting the computer. Indeed, receiving an active LPF signal means that the cut is long. The restart of the computer can therefore be performed with the necessary self-tests after a maintenance phase. Not receiving any LPF signal (ie an inactive LPF signal) means either that there is no power failure or that the power supply cutoff is short and that, therefore, the calculator must restart as soon as possible after resumption of the power supply. Throughout the duration of the long break, the measuring circuit is open and the capacitor discharged. There is no other measure of power failure possible during this time. After long shutdown, the measuring circuit is closed only after receiving the signal RLPF which allows to recharge the capacitor until the next power failure.
- FIG. 2 shows an example of a timing diagram showing different signals of the circuit of FIG. 1, during a long cut and during a short cut.
- Channel 1 of the timing diagram shows the grid voltage
- Channel 2 shows the supply voltage of the programmable component
- Channel 3 shows the reset pulse of the computer
- Channel 4 shows the signal RLPF of long cutoff acknowledgment
- channel 5 shows the output signal LEVEL of the comparator
- channel 6 shows the switching signal COM.
- Each of these 6 channels shows a signal after a short cut (between t0 and t3), during and after a long break (between t3 and t6) and after acknowledgment (from t6), that is to say after the CPU has returned an end of backup order of the long cut information.
- the mains voltage goes up to a 28 volt level (at t1).
- the programmable component (channel 2) recovers a supply voltage from the 28 Volts, just after the end of the power failure. It is then powered by the voltage of 28 volts.
- the computer is reset (channel 3), that is to say that the computer restarts.
- the RLPF signal is inactive, as is the LEVEL signal.
- the switching signal COM (channel 6) goes to the active state, t2, that is to say at the moment when the computer is reset.
- the network voltage decreases to 0.
- the supply voltage of the programmable component decreases to 0. All other channels in the timing diagram are also 0.
- the long break ends.
- the network voltage goes back to 28 volts.
- the supply voltage of the programmable component returns to its active level.
- the computer is reset (channel 3).
- the LEVEL signal goes to the active state.
- the COM signal is at O.
- an RLPF signal is sent.
- the LEVEL signal then goes back to O and the COM signal goes to 1.
- the programmable component is preferably selected so as to ensure that its outputs are low or high during the power-up phase, thereby ensuring that the rise of power supply does not control the switch through the switching signal.
- the network voltage is at 28 Volts constant.
- the supply voltage of the programmable component is also high.
- the reset reset signal of the computer is at 1, which means that the computer is powered and working properly.
- the RLPF signal returns to O, as does the LEVEL signal.
- the switching signal COM remains at 1.
- the programmable component of the system of the invention can be a simple component without a meter. It can be a modern component, for example, a power sequencer, relatively inexpensive and reliable compared to the low-power components of the prior art.
- the power supply card on which is mounted the electronic circuit of Figure 1 is relatively small and light.
- This power supply card requires a supply current, and in particular a starting current, low compared to the prior art due to a reserve of energy of reduced capacity.
- the system of the invention requires no non-volatile memory or management of a low power mode, which simplifies its architecture.
- the long duration information is not stored on a memory but is intrinsically saved by the capacitor in the discharge phase.
Landscapes
- Engineering & Computer Science (AREA)
- Theoretical Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Power Sources (AREA)
- Stand-By Power Supply Arrangements (AREA)
- Emergency Protection Circuit Devices (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BRPI0812759A BRPI0812759A2 (pt) | 2007-06-29 | 2008-06-24 | método e sistema de gestão de cortes de alimentação elétrico à bordo de uma aeronave |
EP08806072A EP2165246A2 (fr) | 2007-06-29 | 2008-06-24 | Procede et systeme de gestion de coupures d'alimentation electrique a bord d'un aeronef |
US12/666,917 US8417995B2 (en) | 2007-06-29 | 2008-06-24 | Method and system for managing electrical power supply outages on board an aircraft |
JP2010514059A JP5345143B2 (ja) | 2007-06-29 | 2008-06-24 | 航空機の機中の停電管理方法及びシステム |
CN2008801050941A CN101796469B (zh) | 2007-06-29 | 2008-06-24 | 飞行器上的管理供电中断的方法和*** |
CA2692300A CA2692300C (fr) | 2007-06-29 | 2008-06-24 | Procede et systeme de gestion de coupures d'alimentation electrique a bord d'un aeronef |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0756176A FR2918188B1 (fr) | 2007-06-29 | 2007-06-29 | Procede et systeme de gestion de coupures d'alimentation electrique a bord d'un aeronef |
FR0756176 | 2007-06-29 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2009007591A2 true WO2009007591A2 (fr) | 2009-01-15 |
WO2009007591A3 WO2009007591A3 (fr) | 2009-03-19 |
Family
ID=39048904
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2008/051140 WO2009007591A2 (fr) | 2007-06-29 | 2008-06-24 | Procede et systeme de gestion de coupures d'alimentation electrique a bord d'un aeronef |
Country Status (9)
Country | Link |
---|---|
US (1) | US8417995B2 (fr) |
EP (1) | EP2165246A2 (fr) |
JP (1) | JP5345143B2 (fr) |
CN (1) | CN101796469B (fr) |
BR (1) | BRPI0812759A2 (fr) |
CA (1) | CA2692300C (fr) |
FR (1) | FR2918188B1 (fr) |
RU (1) | RU2010102947A (fr) |
WO (1) | WO2009007591A2 (fr) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4837152B1 (ja) * | 2011-02-14 | 2011-12-14 | 三菱電機株式会社 | プログラマブルコントローラ |
RU2492119C2 (ru) * | 2011-09-21 | 2013-09-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Московский государственный технический университет имени Н.Э. Баумана" (МГТУ им. Н.Э. Баумана) | Беспилотный летательный аппарат |
US20170307672A9 (en) * | 2013-01-29 | 2017-10-26 | Smart Drilling And Completion, Inc. | Stable grounding system to avoid catastrophic electrical failures in fiber-reinforced composite aircraft |
US9389665B1 (en) * | 2015-06-19 | 2016-07-12 | Rockwell Collins, Inc. | Power warning monitor system and method |
CN105826981B (zh) * | 2016-05-11 | 2019-01-29 | Tcl移动通信科技(宁波)有限公司 | 一种基于移动终端的充电设备重连配置方法及*** |
CN110160216B (zh) * | 2019-05-07 | 2021-12-21 | 重庆海尔空调器有限公司 | 一种用电设备的控制方法、控制装置及用电设备 |
CN112436503B (zh) * | 2020-12-01 | 2022-12-13 | 陕西航空电气有限责任公司 | 一种飞机高压直流供电***中的高压直流汇流条功率控制方法 |
US11682535B2 (en) | 2021-03-12 | 2023-06-20 | Essex Industries, Inc. | Rocker switch |
EP4309200A1 (fr) | 2021-03-15 | 2024-01-24 | Essex Industries, Inc. | Commutateur à cinq positions |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH08313564A (ja) * | 1995-05-19 | 1996-11-29 | Diamond Electric Mfg Co Ltd | 停電時間検出回路 |
DE29705503U1 (de) * | 1996-03-29 | 1997-06-05 | Siemens AG, 80333 München | Mikrocontroller mit verminderter Betriebsspannung |
EP1160650A2 (fr) * | 2000-06-02 | 2001-12-05 | Robert Bosch Gmbh | Dispositif et méthode d'identification de redémarrage à chaud d'un Calculateur |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IT1241288B (it) * | 1990-11-20 | 1993-12-29 | Sgs Thomson Microelectronics | Dispositivo di reset per microprocessore, in particolare in applicazioni automobilistiche |
US5929604A (en) * | 1997-06-18 | 1999-07-27 | Ericsson, Inc. | Battery-discharge-protection system for electronic accessories used in vehicles containing a battery |
US7308614B2 (en) * | 2002-04-30 | 2007-12-11 | Honeywell International Inc. | Control sequencing and prognostics health monitoring for digital power conversion and load management |
RU51250U1 (ru) | 2005-09-19 | 2006-01-27 | Общество с ограниченной ответственностью "Авионика-Вист" | Бортовой вычислитель |
-
2007
- 2007-06-29 FR FR0756176A patent/FR2918188B1/fr active Active
-
2008
- 2008-06-24 WO PCT/FR2008/051140 patent/WO2009007591A2/fr active Application Filing
- 2008-06-24 RU RU2010102947/08A patent/RU2010102947A/ru not_active Application Discontinuation
- 2008-06-24 JP JP2010514059A patent/JP5345143B2/ja active Active
- 2008-06-24 CA CA2692300A patent/CA2692300C/fr not_active Expired - Fee Related
- 2008-06-24 US US12/666,917 patent/US8417995B2/en active Active
- 2008-06-24 CN CN2008801050941A patent/CN101796469B/zh active Active
- 2008-06-24 EP EP08806072A patent/EP2165246A2/fr not_active Withdrawn
- 2008-06-24 BR BRPI0812759A patent/BRPI0812759A2/pt not_active IP Right Cessation
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH08313564A (ja) * | 1995-05-19 | 1996-11-29 | Diamond Electric Mfg Co Ltd | 停電時間検出回路 |
DE29705503U1 (de) * | 1996-03-29 | 1997-06-05 | Siemens AG, 80333 München | Mikrocontroller mit verminderter Betriebsspannung |
EP1160650A2 (fr) * | 2000-06-02 | 2001-12-05 | Robert Bosch Gmbh | Dispositif et méthode d'identification de redémarrage à chaud d'un Calculateur |
Also Published As
Publication number | Publication date |
---|---|
US20110047399A1 (en) | 2011-02-24 |
RU2010102947A (ru) | 2011-08-10 |
US8417995B2 (en) | 2013-04-09 |
EP2165246A2 (fr) | 2010-03-24 |
CA2692300A1 (fr) | 2009-01-15 |
JP2010531774A (ja) | 2010-09-30 |
CN101796469A (zh) | 2010-08-04 |
FR2918188B1 (fr) | 2009-12-04 |
CA2692300C (fr) | 2015-04-21 |
WO2009007591A3 (fr) | 2009-03-19 |
FR2918188A1 (fr) | 2009-01-02 |
JP5345143B2 (ja) | 2013-11-20 |
BRPI0812759A2 (pt) | 2019-09-24 |
CN101796469B (zh) | 2013-08-07 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CA2692300C (fr) | Procede et systeme de gestion de coupures d'alimentation electrique a bord d'un aeronef | |
CA2594826C (fr) | Procede de chargement equilibre d'une batterie lithium-ion ou lithium polymere | |
EP1079525B1 (fr) | Système de commande d'un interrupteur bidirectionnel à deux transistors | |
EP2363940B1 (fr) | Système et procédé d'alimentation en courant continu d'un système électrique | |
EP2924837B1 (fr) | Dispositif de gestion des causes de déclenchement dans un déclencheur électronique | |
FR2631168A1 (fr) | Dispositif pour charger des accumulateurs | |
FR2873209A1 (fr) | Procede et dispositif pour la determination de parametres de fonctionnement d'une batterie | |
EP2187227B1 (fr) | Système à sécurité intrinsèque et module de test, notamment pour une utilisation dans un système de signalisation ferroviaire | |
EP2363939B1 (fr) | Ensemble électrique et procédé d'alimentation sans interruption en courant alternatif d'une installation | |
EP3358307B1 (fr) | Procédé de gestion d'une alimentation auxiliaire d'un compteur et compteur, programme et moyen de stockage correspondants | |
EP2395594B1 (fr) | Dispositif et procédé d'alimentation pour système de communication sans fil et ensemble capteur comportant un tel dispositif | |
EP3220471B1 (fr) | Procédé de charge d'une batterie d'accumulateurs électrochimiques et dispositif de pilotage de la charge | |
EP0009606B1 (fr) | Dispositif de commande de charge d'une batterie d'accumulateurs | |
EP3258569B1 (fr) | Système d'alimentation comprenant une unité de gestion principale et une unité de gestion de réserve | |
FR2965626A1 (fr) | Systeme de gestion d'un dispositif photovoltaique | |
EP1102158B1 (fr) | Dispositif et procédé de contrôle de l'état de fonctionnement d'un système électronique en "zone grise" | |
FR3058271A1 (fr) | Procede et systeme de controle de charge d'une batterie d'un equipement electrique | |
EP3185389B1 (fr) | Dispositif et appareil électrique de génération d'une tension électrique à destination d'une unité de traitement d'informations, système électronique de traitement d'informations associé | |
EP3979282A1 (fr) | Dispositif de communication pour un appareil de commutation électrique | |
FR3117274A1 (fr) | Procédé d’équilibrage | |
FR3112868A1 (fr) | Ensemble comportant un automate programmable, une alimentation externe et une source d’alimentation principale | |
FR2965423A1 (fr) | Dispositif d'optimisation de la gestion d'energie pour reseau de bord de vehicule comprenant un ou une pluralite de dispositifs de maintien de tension | |
WO2002001696A1 (fr) | Dispositif d'alimentation d'un appareil electronique | |
FR2777396A1 (fr) | Dispositif et procede d'alimentation electrique securisee pour systeme de reproduction audiovisuelle | |
FR2795251A1 (fr) | Dispositif d'alimentation de microprocesseur de vehicule automobile a resistance accrue aux chutes d'alimentation |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WWE | Wipo information: entry into national phase |
Ref document number: 200880105094.1 Country of ref document: CN |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 08806072 Country of ref document: EP Kind code of ref document: A2 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2008806072 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2692300 Country of ref document: CA |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2010514059 Country of ref document: JP |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2010102947 Country of ref document: RU |
|
WWE | Wipo information: entry into national phase |
Ref document number: 12666917 Country of ref document: US |
|
ENP | Entry into the national phase |
Ref document number: PI0812759 Country of ref document: BR Kind code of ref document: A2 Effective date: 20091229 |