FR3125507A1 - Electric aircraft architecture with electric or hybrid propulsion - Google Patents
Electric aircraft architecture with electric or hybrid propulsion Download PDFInfo
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- FR3125507A1 FR3125507A1 FR2108100A FR2108100A FR3125507A1 FR 3125507 A1 FR3125507 A1 FR 3125507A1 FR 2108100 A FR2108100 A FR 2108100A FR 2108100 A FR2108100 A FR 2108100A FR 3125507 A1 FR3125507 A1 FR 3125507A1
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- 230000001141 propulsive effect Effects 0.000 claims abstract description 13
- 238000002955 isolation Methods 0.000 claims abstract description 5
- 230000002441 reversible effect Effects 0.000 claims abstract description 4
- 239000002184 metal Substances 0.000 claims description 3
- 230000007935 neutral effect Effects 0.000 claims description 3
- 230000000903 blocking effect Effects 0.000 claims description 2
- 239000003990 capacitor Substances 0.000 claims description 2
- 238000004804 winding Methods 0.000 claims description 2
- 239000011888 foil Substances 0.000 claims 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical group [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000002803 fossil fuel Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M3/00—Conversion of dc power input into dc power output
- H02M3/22—Conversion of dc power input into dc power output with intermediate conversion into ac
- H02M3/24—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters
- H02M3/28—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac
- H02M3/325—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal
- H02M3/335—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
- H02M3/33569—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only having several active switching elements
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
- H01F27/00—Details of transformers or inductances, in general
- H01F27/28—Coils; Windings; Conductive connections
- H01F27/288—Shielding
- H01F27/2885—Shielding with shields or electrodes
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M1/00—Details of apparatus for conversion
- H02M1/0095—Hybrid converter topologies, e.g. NPC mixed with flying capacitor, thyristor converter mixed with MMC or charge pump mixed with buck
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M1/00—Details of apparatus for conversion
- H02M1/32—Means for protecting converters other than automatic disconnection
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M3/00—Conversion of dc power input into dc power output
- H02M3/003—Constructional details, e.g. physical layout, assembly, wiring or busbar connections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M1/00—Details of apparatus for conversion
- H02M1/0064—Magnetic structures combining different functions, e.g. storage, filtering or transformation
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M3/00—Conversion of dc power input into dc power output
- H02M3/22—Conversion of dc power input into dc power output with intermediate conversion into ac
- H02M3/24—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters
- H02M3/28—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac
- H02M3/325—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal
- H02M3/335—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
- H02M3/33569—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only having several active switching elements
- H02M3/33573—Full-bridge at primary side of an isolation transformer
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M7/00—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output
- H02M7/42—Conversion of dc power input into ac power output without possibility of reversal
- H02M7/44—Conversion of dc power input into ac power output without possibility of reversal by static converters
- H02M7/48—Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode
- H02M7/483—Converters with outputs that each can have more than two voltages levels
- H02M7/4837—Flying capacitor converters
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M7/00—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output
- H02M7/42—Conversion of dc power input into ac power output without possibility of reversal
- H02M7/44—Conversion of dc power input into ac power output without possibility of reversal by static converters
- H02M7/48—Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode
- H02M7/483—Converters with outputs that each can have more than two voltages levels
- H02M7/487—Neutral point clamped inverters
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Rectifiers (AREA)
Abstract
Architecture électrique d’aéronef à propulsion électrique ou hybride Architecture électrique d’aéronef à propulsion électrique ou hybride comportant un réseau d’alimentation électrique haute tension propulsif (HVDC moteur) relié à un réseau électrique de bord haute tension non propulsif (HVDC avion) via un convertisseur de tension DC/DC, dans laquelle, pour permettre une isolation galvanique et un transfert de puissance réversible entre les deux réseaux électriques haute tension, le convertisseur de tension DC/DC comprend un convertisseur de tension DC/AC (10) relié d’une part au réseau d’alimentation électrique haute tension propulsif et d’autre part à un primaire (120) d’un transformateur électrique (12) ayant un secondaire à point milieu (122) et un écran (126) entre primaire et secondaire, et un convertisseur de tension AC/DC (14) relié d’une part au secondaire du transformateur électrique et d’autre part au réseau électrique de bord haute tension non propulsif, le point milieu (124) du secondaire et l’écran (126) étant reliés à un point froid de référence (128). Figure pour l’abrégé : Fig. 1.Electrical architecture of an electrically or hybrid-powered aircraft Electrical architecture of an electrically-powered or hybrid aircraft comprising a propulsion high voltage power supply network (engine HVDC) connected to a non-propulsion high voltage on-board electrical network (aircraft HVDC) via a DC/DC voltage converter, in which, to allow galvanic isolation and reversible power transfer between the two high voltage electrical networks, the DC/DC voltage converter comprises a DC/AC voltage converter (10) connected to on the one hand to the propulsive high voltage power supply network and on the other hand to a primary (120) of an electrical transformer (12) having a midpoint secondary (122) and a screen (126) between primary and secondary , and an AC/DC voltage converter (14) connected on the one hand to the secondary of the electrical transformer and on the other hand to the non-propulsive high voltage on-board electrical network, the midpoint (12 4) of the secondary and the screen (126) being connected to a reference cold point (128). Figure for abstract: Fig. 1.
Description
La présente invention se rapporte au domaine des architectures électriques d’aéronef à propulsion électrique ou hybride et elle concerne plus particulièrement l’isolation et le transfert de puissance électrique entre les deux réseaux d’alimentation électrique propulsif et non propulsif de l’aéronef.The present invention relates to the field of electrical architectures of electrically or hybrid-powered aircraft and it relates more particularly to the isolation and transfer of electrical power between the two propulsion and non-propulsion power supply networks of the aircraft.
Dans un réseau électrique conventionnel tel qu’il existe sur les aéronefs traditionnels utilisant des énergies fossiles, lorsqu’il y a plusieurs niveaux de tension embarqués sur un aéronef, la passerelle entre ces réseaux à niveaux de tension différents est réalisée par des convertisseurs de puissance passifs, à diodes essentiellement, ou actifs (DC/DC, AC/DC). La propagation de défauts pouvant se produire d’un réseau à un autre, les systèmes ainsi que les équipements sont conçus pour résister et être tolérants aux transitoires induits par ces défauts. Les points froids de référence électrique communs à ces réseaux sont souvent connectés à la structure métallique de l’aéronef ou à un réseau de neutre commun pour des aéronefs à structure carbone. Les convertisseurs eux-mêmes peuvent être non isolés pour réduire leurs masses.In a conventional electrical network such as exists on traditional aircraft using fossil fuels, when there are several voltage levels on board an aircraft, the gateway between these networks at different voltage levels is made by power converters passive, mainly with diodes, or active (DC/DC, AC/DC). Since the propagation of faults can occur from one network to another, systems and equipment are designed to withstand and be tolerant to transients induced by these faults. The electrical reference cold points common to these networks are often connected to the metal structure of the aircraft or to a common neutral network for carbon structure aircraft. The converters themselves can be non-isolated to reduce their masses.
Par contre, dans des aéronefs à propulsion tout électrique ou hybride-électrique, un réseau d’alimentation électrique est ajouté comme énergie de propulsion à ce réseau électrique conventionnel.On the other hand, in all-electric or hybrid-electric propulsion aircraft, an electrical power supply network is added as propulsion energy to this conventional electrical network.
Or, avec un réseau haute-tension supplémentaire (typiquement de 800 à 1500Vdc) dont la fonction principale est d’assurer la propulsion de l’aéronef, il est absolument nécessaire, pour des raisons de sécurité, de ne pas avoir de propagation de défauts quel qu’il soit venant du réseau de bord traditionnel (230Vac, 115Vac, 28Vdc) qui pourrait perturber les performances de vol. A l’inverse, la haute tension utilisée dans le réseau électrique de propulsion ne doit pas se propager sur le réseau de bord traditionnel de plus basse tension car les équipements ne sont pas conçus pour résister et être tolérants à ce niveau de tension aussi élevé. Parmi ces équipements, il y a en effet des équipements critiques, comme les calculateurs de commandes de vol, de radio et de navigation dont la perte peut être catastrophique.However, with an additional high-voltage network (typically from 800 to 1500 Vdc) whose main function is to ensure the propulsion of the aircraft, it is absolutely necessary, for safety reasons, not to have fault propagation whatever it is coming from the traditional on-board network (230Vac, 115Vac, 28Vdc) that could disrupt flight performance. Conversely, the high voltage used in the propulsion electrical network must not propagate on the traditional lower voltage on-board network because the equipment is not designed to withstand and be tolerant of such a high voltage level. Among this equipment, there is indeed critical equipment, such as flight control, radio and navigation computers, the loss of which could be catastrophic.
Il existe donc aujourd’hui un besoin pour les aéronefs électriques ou hybrides d’une architecture électrique permettant d’exploiter ces deux modes d’alimentation électrique avec en outre des transferts de puissance réversibles entre les deux réseaux.There is therefore today a need for electric or hybrid aircraft for an electrical architecture making it possible to exploit these two modes of electrical power supply with, in addition, reversible power transfers between the two networks.
La présente invention a donc pour but principal de répondre à ce besoin en proposant une architecture électrique d’aéronef à propulsion électrique ou hybride comportant un réseau d’alimentation électrique supplémentaire de forte puissance associé à un réseau de bord traditionnel dont le point de référence électrique permet une isolation galvanique et un transfert de puissance entre les deux réseaux.The main purpose of the present invention is therefore to meet this need by proposing an electrical architecture for an aircraft with electric or hybrid propulsion comprising an additional high-power electrical supply network associated with a traditional on-board network whose electrical reference point allows galvanic isolation and power transfer between the two networks.
Ce but est atteint par une architecture électrique d’aéronef à propulsion électrique ou hybride comportant un réseau d’alimentation électrique haute tension propulsif (HVDC moteur) relié à un réseau électrique de bord haute tension non propulsif (HVDC aéronef) via un convertisseur de tension DC/DC, caractérisé en ce que pour permettre une isolation galvanique et un transfert de puissance réversible entre les deux réseaux électriques haute tension, le convertisseur de tension DC/DC comprend un convertisseur de tension DC/AC relié d’une part au réseau d’alimentation électrique haute tension propulsif et d’autre part à un primaire d’un transformateur électrique ayant un secondaire à point milieu et un écran entre primaire et secondaire, et un convertisseur de tension AC/DC relié d’une part au secondaire du transformateur électrique et d’autre part au réseau électrique de bord haute tension non propulsif, le point milieu du secondaire et l’écran étant reliés à un point froid de référence.This object is achieved by an electric or hybrid propulsion aircraft electrical architecture comprising a propulsion high voltage power supply network (engine HVDC) connected to a non-propulsion high voltage on-board electrical network (aircraft HVDC) via a voltage converter DC/DC, characterized in that to allow galvanic isolation and reversible power transfer between the two high voltage electrical networks, the DC/DC voltage converter comprises a DC/AC voltage converter connected on the one hand to the power supply network propulsive high voltage power supply and on the other hand to a primary of an electric transformer having a midpoint secondary and a screen between primary and secondary, and an AC/DC voltage converter connected on the one hand to the secondary of the transformer electricity and on the other hand to the non-propulsive high voltage on-board electrical network, the middle point of the secondary and the screen being connected to a reference cold point.
Par sa liaison à la masse électrique, l’écran empêche la propagation de défauts et d’interférences au travers du transformateur électrique dont le primaire est flottant et le point milieu du secondaire relié à la même masse électrique. Il permet une parfaite séparation des deux réseaux électriques propulsif et non-propulsif ainsi créés.Through its connection to the electrical ground, the screen prevents the propagation of faults and interference through the electrical transformer, the primary of which is floating and the middle point of the secondary connected to the same electrical ground. It allows perfect separation of the two propulsion and non-propulsion electrical networks thus created.
Avantageusement, l’écran est disposé entre des enroulements primaire et secondaires du transformateur et est réalisé par un feuillard conducteur métallique.Advantageously, the screen is arranged between the primary and secondary windings of the transformer and is produced by a metallic conductive strip.
De préférence, le convertisseur de tension DC/AC est onduleur multiniveaux à capacités flottantes et le convertisseur de tension AC/DC est un redresseur multiniveaux à diodes de blocage.Preferably, the DC/AC voltage converter is a multilevel inverter with floating capacitors and the AC/DC voltage converter is a multilevel rectifier with blocking diodes.
Avantageusement, le point froid de référence est une partie structurelle métallique de l’aéronef ou un neutre commun d’un aéronef à structure carbone.Advantageously, the reference cold point is a metal structural part of the aircraft or a common neutral of a carbon structure aircraft.
De préférence, le réseau d’alimentation électrique haute tension propulsif est un réseau continu de tension comprise entre -400Vdc +400Vdc et -750Vdc +750Vdc et le réseau électrique de bord haute tension non propulsif est un réseau continu de tension -270Vdc +270Vdc.Preferably, the propulsion high voltage power supply network is a direct voltage network between -400Vdc +400Vdc and -750Vdc +750Vdc and the non-propulsion high voltage on-board electrical network is a direct voltage network -270Vdc +270Vdc.
L’invention concerne également tout aéronef à propulsion électrique ou hybride muni d’une telle architecture électrique.The invention also relates to any electrically or hybrid-powered aircraft equipped with such an electrical architecture.
D’autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif et sur les lesquels :Other characteristics and advantages of the present invention will emerge from the description given below, with reference to the appended drawings which illustrate an example of embodiment devoid of any limiting character and on which:
Claims (9)
- un convertisseur de tension DC/AC (10) relié d’une part au réseau d’alimentation électrique haute tension propulsif et d’autre part à un primaire (120) d’un transformateur électrique (12) ayant un secondaire à point milieu (122) et un écran (126) entre primaire et secondaire, et
- un convertisseur de tension AC/DC (14) relié d’une part au secondaire du transformateur électrique et d’autre part au réseau électrique de bord haute tension non propulsif, le point milieu (124) du secondaire et l’écran (126) étant reliés à un point froid de référence (128).Electric or hybrid propulsion aircraft electrical architecture comprising a propulsion high voltage power supply network (engine HVDC) connected to a non-propulsion high voltage on-board electrical network (aircraft HVDC) via a DC/DC voltage converter, characterized in that to allow galvanic isolation and reversible power transfer between the two high voltage electrical networks, the DC/DC voltage converter comprises:
- a DC/AC voltage converter (10) connected on the one hand to the propulsive high voltage power supply network and on the other hand to a primary (120) of an electric transformer (12) having a midpoint secondary (122) and a screen (126) between primary and secondary, and
- an AC/DC voltage converter (14) connected on the one hand to the secondary of the electrical transformer and on the other hand to the non-propulsive high voltage on-board electrical network, the midpoint (124) of the secondary and the screen (126 ) being connected to a reference cold point (128).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR2108100A FR3125507A1 (en) | 2021-07-26 | 2021-07-26 | Electric aircraft architecture with electric or hybrid propulsion |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR2108100 | 2021-07-26 | ||
| FR2108100A FR3125507A1 (en) | 2021-07-26 | 2021-07-26 | Electric aircraft architecture with electric or hybrid propulsion |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| FR3125507A1 true FR3125507A1 (en) | 2023-01-27 |
Family
ID=77411957
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR2108100A Pending FR3125507A1 (en) | 2021-07-26 | 2021-07-26 | Electric aircraft architecture with electric or hybrid propulsion |
Country Status (1)
| Country | Link |
|---|---|
| FR (1) | FR3125507A1 (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20200191852A1 (en) * | 2018-12-17 | 2020-06-18 | Ge Aviation Systems Limited | Method and circuit for detecting an arc fault |
| US20210172382A1 (en) * | 2019-12-06 | 2021-06-10 | Rolls-Royce Plc | Electrical systems |
-
2021
- 2021-07-26 FR FR2108100A patent/FR3125507A1/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20200191852A1 (en) * | 2018-12-17 | 2020-06-18 | Ge Aviation Systems Limited | Method and circuit for detecting an arc fault |
| US20210172382A1 (en) * | 2019-12-06 | 2021-06-10 | Rolls-Royce Plc | Electrical systems |
Non-Patent Citations (2)
| Title |
|---|
| BUTICCHI GIAMPAOLO ET AL: "On-Board Microgrids for the More Electric Aircraft-Technology Review", IEEE TRANSACTIONS ON INDUSTRIAL ELECTRONICS, IEEE SERVICE CENTER, PISCATAWAY, NJ, USA, vol. 66, no. 7, July 2019 (2019-07-01), pages 5588 - 5599, XP011712607, ISSN: 0278-0046, [retrieved on 20190301], DOI: 10.1109/TIE.2018.2881951 * |
| KESHMIRI NILOUFAR ET AL: "Comparison of Isolated Bidirectional DC/DC Converters Using WBG Devices for More Electric Aircraft", IEEE OPEN JOURNAL OF THE INDUSTRIAL ELECTRONICS SOCIETY, IEEE, vol. 2, 9 February 2021 (2021-02-09), pages 184 - 198, XP011841497, DOI: 10.1109/OJIES.2021.3058196 * |
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