EP2449647A1 - System and method for supplying electric power to an aircraft - Google Patents

System and method for supplying electric power to an aircraft

Info

Publication number
EP2449647A1
EP2449647A1 EP10745333A EP10745333A EP2449647A1 EP 2449647 A1 EP2449647 A1 EP 2449647A1 EP 10745333 A EP10745333 A EP 10745333A EP 10745333 A EP10745333 A EP 10745333A EP 2449647 A1 EP2449647 A1 EP 2449647A1
Authority
EP
European Patent Office
Prior art keywords
transformer
aircraft
neutral
homopolar
rectifier
Prior art date
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.)
Withdrawn
Application number
EP10745333A
Other languages
German (de)
French (fr)
Inventor
Lucien Prisse
Brice Aubert
Vincent Pauvert
Dominique Alejo
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
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 Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of EP2449647A1 publication Critical patent/EP2449647A1/en
Withdrawn legal-status Critical Current

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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
    • H02J3/00—Circuit arrangements for ac mains or ac distribution networks
    • H02J3/26—Arrangements for eliminating or reducing asymmetry in polyphase networks
    • 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
    • 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
    • H02J2310/00—The network for supplying or distributing electric power characterised by its spatial reach or by the load
    • H02J2310/40—The network being an on-board power network, i.e. within a vehicle
    • H02J2310/44—The network being an on-board power network, i.e. within a vehicle for aircrafts
    • 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
    • Y02E40/00—Technologies for an efficient electrical power generation, transmission or distribution
    • Y02E40/50—Arrangements for eliminating or reducing asymmetry in polyphase networks

Definitions

  • the invention relates to a system and method for powering an aircraft, for example an aircraft.
  • the neutral system commonly used is the TN-C regime, which means:
  • each main generator G is connected to the fuselage 10 'of the aircraft, at the level of the engine mats (1 meter of cable) to ensure the return of the imbalance currents and defects.
  • all the masses of the equipment are connected to this fuselage.
  • the fuselage is therefore both the role of neutral conductor and earth.
  • FIG. 1 there is shown a three-phase generator G, whose neutral N is connected to the fuselage 10 ', connected to an electric core 11' by its phases ph1, ph2 and ph3, a phase-earth fault load 12 'of which the mass is connected to the fuselage 10 '.
  • a fault current id 13 ' relating to this load 12' in default, which transits to the fuselage 10 ', is also illustrated.
  • the main generators G fulfill the functions of direct, inverse and homopolar current component generators described for example in the document referenced [1] at the end of the description.
  • the neutral regime as defined above makes it possible to achieve a large mass gain by avoiding the addition of additional cables.
  • the neutral distribution of the main generators G is overweight for two reasons:
  • connection of the neutral of each generator G to the fuselage allows the circulation of the harmonic currents 3, that is to say the circulation of homopolar currents, which causes additional losses.
  • harmonic currents 3 that is to say the circulation of homopolar currents, which causes additional losses.
  • generators designed with a 2/3 pitch winding structure which implies a slight attenuation of the fundamental. As a result, the mass power of the generator decreases.
  • each generator G can not be connected to the engine mat. It is connected to the PVR (Point Voltage Reference) of the ESN ("Electrical Structural Network") 10, as shown in Figure 2. The neutral and the mass of charges are connected to the ESN.
  • PVR Point Voltage Reference
  • the object of the invention is to eliminate such neutral cables in order to reduce the volume and the mass of the power supply on board the aircraft, the main generators retaining the role of generators of the direct and inverse components but the function of homopolar generator being provided by a specific equipment.
  • the invention relates to an electrical power supply system for an aircraft comprising an electrical network comprising main generators supplying electric distribution channels, electric cores, and loads, characterized in that it comprises means for setting up a neutral artificial electric cores comprising a homopolar generator, which is an equipment of the electrical network.
  • Such a transformer-rectifier comprises:
  • a three-phase transformer with galvanic isolation comprising:
  • the invention also relates to a method for powering an aircraft comprising an electrical network comprising main generators supplying electrical distribution channels, electric cores, and loads, in which the direct and reverse current components are generated. using these generators, characterized by setting up an artificial neutral at the level of the electric cores and in that the homopolar component is generated by means of a specific equipment, which is an equipment of the electrical network.
  • This equipment of the electrical network can include a transformer. It can be a transformer-rectifier.
  • the invention thus makes it possible to eliminate the distribution of the neutral between the generators and the electric cores using cables, with the establishment of an artificial neutral in the electric cores, which allows for savings in mass of the aircraft and sizing of these generators.
  • the creation of an artificial neutral using a homopolar generator makes it possible, in fact, to convey the fault currents that are distributed over three phases in the form of three homopolar components and no longer only on the single short-circuit phase.
  • TRU transformer-rectifier as a homopolar generator makes it possible to pool the homopolar generator function on an existing equipment by connecting the neutral of the primary of the transformer to the PVR of the aircraft.
  • FIGS 1, 2 and 3 illustrate a power system of an aircraft according to the prior art.
  • FIG. 4 illustrates the integration of a homopolar generator in an electrical network according to the invention.
  • FIG. 5 illustrates the embodiment of the homopolar generator illustrated in FIG. 4 using a transformer whose primer is coupled in a star.
  • FIG. 6 illustrates an embodiment of the system of the invention in which a transformer-rectifier (TRU) is used as homopolar generator.
  • TRU transformer-rectifier
  • Figure 7 illustrates the current distribution in a transformer-rectifier as shown in Figure 6 in case of a fault.
  • the power supply system of the invention thus comprises an electrical network consisting of a main generator G, an electric core 11, a load 12 in default, and the ESN 10 of the aircraft. It further comprises a homopolar generator 30.
  • a homopolar generator makes it possible to create an impedant neutral on an electrical network that does not have one, and to ground this network through this impedance.
  • the impedance is calculated to limit the fault current to a specified value. The value of the fault current depends on the network to be protected.
  • Such a homopolar generator 30 is characterized by:
  • such a homopolar generator 30 makes it possible to create an artificial neutral which makes it possible to eliminate the neutral cables coming from the main generators.
  • the homopolar generator function can be performed with existing equipment in the aircraft electrical network which allows for mass savings.
  • This equipment may be, for example, a transformer 40.
  • the secondary of this transformer may or may not be connected to functional loads 41.
  • This transformer 40 must have the following characteristics:
  • the invention thus makes it possible to reduce the mass of the aircraft, mainly because of the removal of the neutral cable.
  • the invention also allows:
  • the winding structure 2/3 pitch which has the disadvantage of attenuating the fundamental currents, is no longer necessary for eliminating the harmonics 3. It is therefore possible to use another type of winding, for example a winding with a pitch of 5/6, which makes it possible to minimize the harmonics 5 and 7 while obtaining a fundamental value of 10% higher compared to a winding step 2/3.
  • the invention makes it possible to obtain a distribution of the three-phase fault currents in the form of three homopolar components, unlike the known-art system, in which all of the fault currents flow on the phase in short circuit.
  • the generator given fault current, the generator must only provide 2/3 of the fault current on the short-circuit phase instead of its entirety, before the protections are triggered.
  • the sizing of the generators therefore becomes less restrictive with respect to the short-circuit currents.
  • the rise of the fault and unbalance currents is ensured by an artificial neutral made with a transformer-rectifier TRU ("Transformer Rectifier Unit") functioning as homopolar generator.
  • TRU Transformer Rectifier Unit
  • Such a transformer-rectifier TRU 59 used to create a continuous network from a three-phase AC network, is composed of:
  • a three-phase transformer with galvanic isolation comprising:
  • N 'of the primary of the transformer 60 is connected by a link 50 to the ESN 10 of the aircraft, as shown in FIG. 6.
  • the rise of the homopolar currents in the primary does not disturb the DC network at the output of the TRU 59.
  • L galvanic isolation between the primary 60 and the two secondary 61 and 62 coupled in star and in triangle without distributed neutral does not allow the circulation of homopolar components.
  • Figure 7 illustrates the distribution of currents in the transformer 59 in the event of a fault.
  • the direct three-phase currents i pA , i pB , i pC carrying the power to the DC network and the zero-sequence currents i 0 coming from the imbalances on the electrical network are superimposed.
  • the direct three-phase currents i sa, i sb, i sc and ij, i sb ⁇ ij conveying power to the DC network are the only flow to the twelve-phase rectifier 64.

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Supply And Distribution Of Alternating Current (AREA)
  • Control Of Eletrric Generators (AREA)

Abstract

The invention relates to a system and a method for supplying electric power to an aircraft. This system comprises an electrical network comprising main generators (G) for supplying electrical distribution channels and a homopolar generator (30) for creating an artificial neutral.

Description

SYSTEME ET PROCEDE D'ALIMENTATION ELECTRIQUE D'UN  SYSTEM AND METHOD FOR ELECTRICALLY SUPPLYING A
AERONEF  AIRCRAFT
DESCRIPTION DESCRIPTION
DOMAINE TECHNIQUE TECHNICAL AREA
L' invention concerne un système et un procédé d'alimentation électrique d'un aéronef, par exemple d'un avion.  The invention relates to a system and method for powering an aircraft, for example an aircraft.
Dans la suite, pour des raisons de simplification, on considère, à titre d'exemple, un aéronef de type avion.  In the following, for reasons of simplification, it is considered, for example, an aircraft-type aircraft.
ÉTAT DE LA TECHNIQUE ANTÉRIEURE STATE OF THE PRIOR ART
En aéronautique, le régime de neutre couramment utilisé est le régime TN-C, ce qui veut dire :  In aeronautics, the neutral system commonly used is the TN-C regime, which means:
- T : neutre de l'installation reliées directement à la terre,  - T: neutral of the installation connected directly to the earth,
- N : masses de l'installation reliées au conducteur de neutre,  - N: masses of the installation connected to the neutral conductor,
- C : conducteur de protection des masses de l'installation et conducteur de neutre confondus.  - C: protective conductor of the installation masses and neutral conductor combined.
Dans un système d'alimentation électrique à bord d'un avion, le neutre de chaque générateur principal G est relié au fuselage 10' de l'avion, au niveau des mats moteurs (1 mètre de câble) afin d'assurer le retour des courants de déséquilibre et de défauts. De plus, toutes les masses des équipements sont connectées à ce fuselage. Le fuselage tient donc à la fois le rôle de conducteur de neutre et de terre. Ainsi sur la figure 1, sont représentés un générateur triphasé G, dont le neutre N est relié au fuselage 10', relié à un cœur électrique 11' par ses phases phi, ph2 et ph3, une charge en défaut phase-terre 12' dont la masse est reliée au fuselage 10' . Un courant id de défaut 13' relatif à cette charge 12' en défaut, qui transite vers le fuselage 10', est également illustré. In an electrical power system on board an aircraft, the neutral of each main generator G is connected to the fuselage 10 'of the aircraft, at the level of the engine mats (1 meter of cable) to ensure the return of the imbalance currents and defects. In addition, all the masses of the equipment are connected to this fuselage. The fuselage is therefore both the role of neutral conductor and earth. Thus, in FIG. 1, there is shown a three-phase generator G, whose neutral N is connected to the fuselage 10 ', connected to an electric core 11' by its phases ph1, ph2 and ph3, a phase-earth fault load 12 'of which the mass is connected to the fuselage 10 '. A fault current id 13 'relating to this load 12' in default, which transits to the fuselage 10 ', is also illustrated.
Dans une telle configuration, les générateurs principaux G remplissent les fonctions de générateurs de composantes de courant directes, inverses et homopolaires décrites par exemple dans le document référencé [1] en fin de description.  In such a configuration, the main generators G fulfill the functions of direct, inverse and homopolar current component generators described for example in the document referenced [1] at the end of the description.
Le régime de neutre tel que défini ci-dessus permet de réaliser un gain massique important en évitant le rajout de câbles supplémentaires. Cependant, la distribution du neutre des générateurs principaux G entraîne un surpoids pour deux raisons :  The neutral regime as defined above makes it possible to achieve a large mass gain by avoiding the addition of additional cables. However, the neutral distribution of the main generators G is overweight for two reasons:
Le raccordement du neutre de chaque générateur G au fuselage autorise la circulation des courants d'harmonique 3, c'est-à-dire la circulation de courants homopolaires, qui occasionne des pertes supplémentaires. Pour réduire fortement la valeur de ces courants d'harmonique 3, on peut utiliser des générateurs conçus avec une structure de bobinages à pas 2/3, qui implique une légère atténuation du fondamental. Par conséquent, la puissance massique du générateur diminue.  The connection of the neutral of each generator G to the fuselage allows the circulation of the harmonic currents 3, that is to say the circulation of homopolar currents, which causes additional losses. To greatly reduce the value of these harmonic currents 3, it is possible to use generators designed with a 2/3 pitch winding structure, which implies a slight attenuation of the fundamental. As a result, the mass power of the generator decreases.
Dans le cas d'un avion dont le fuselage est en carbone, le neutre de chaque générateur G ne peut être relié au mat moteur. Il est relié au PVR (« Point Voltage Référence » ou point de référence des tensions) de l'ESN (« Electrical Structural Network » ou réseau structurel électrique) 10, comme illustré sur la figure 2. Le neutre et la masse des charges sont reliés à l'ESN. In the case of an aircraft whose fuselage is carbon, the neutral of each generator G can not be connected to the engine mat. It is connected to the PVR (Point Voltage Reference) of the ESN ("Electrical Structural Network") 10, as shown in Figure 2. The neutral and the mass of charges are connected to the ESN.
- La localisation des générateurs principaux G dans les ailes d'un avion 20 à proximité de chaque moteur 21 et celle des cœurs électriques 22 à l'avant de l'avion impose une longueur de câble de neutre 23 non négligeable, comme illustré sur la figure 3, un tel « cœur électrique » étant un noeud d' interconnexion sources - charges incluant des organes de protection et de contact, dont la tension est stabilisée par un élément extérieur. Il en résulte un coût massique important surtout dans le cas où l'avion 20 dispose de quatre canaux d'alimentation électrique, et donc de quatre câbles de neutre.  The location of the main generators G in the wings of an aircraft 20 near each engine 21 and that of the electric cores 22 at the front of the aircraft imposes a length of neutral cable 23 not insignificant, as shown in FIG. FIG. 3, such an "electrical core" being a source-charge interconnection node including protection and contact elements, the voltage of which is stabilized by an external element. This results in a significant mass cost especially in the case where the aircraft 20 has four power supply channels, and therefore four neutral cables.
L'invention a pour objet de supprimer de tels cables de neutre afin de diminuer le volume et la masse de l'alimentation électrique à bord de l'avion, les générateurs principaux conservant le rôle de générateurs des composantes directes et inverses mais la fonction de générateur homopolaire étant assurée par un équipement spécifique.  The object of the invention is to eliminate such neutral cables in order to reduce the volume and the mass of the power supply on board the aircraft, the main generators retaining the role of generators of the direct and inverse components but the function of homopolar generator being provided by a specific equipment.
EXPOSÉ DE L'INVENTION STATEMENT OF THE INVENTION
L' invention concerne un système d'alimentation électrique d'un aéronef comportant un réseau électrique comprenant des générateurs principaux alimentant des canaux de distribution électrique, des cœurs électriques, et des charges, caractérisé en ce qu'il comprend des moyens de mise en place d'un neutre artificiel au niveau des cœurs électriques comportant un générateur homopolaire, qui est un équipement du réseau électrique. The invention relates to an electrical power supply system for an aircraft comprising an electrical network comprising main generators supplying electric distribution channels, electric cores, and loads, characterized in that it comprises means for setting up a neutral artificial electric cores comprising a homopolar generator, which is an equipment of the electrical network.
Il peut comprendre un transformateur. Ce peut être un transformateur-redresseur. Un tel transformateur-redresseur comporte :  It can include a transformer. It can be a transformer-rectifier. Such a transformer-rectifier comprises:
un transformateur triphasé à isolement galvanique comprenant :  a three-phase transformer with galvanic isolation comprising:
• un primaire en étoile, dont le neutre est connecté à la terre,  • a star primer, whose neutral is connected to the ground,
• un secondaire en triangle,  • a secondary in a triangle,
• un secondaire en étoile,  • a star secondary,
• une structure magnétique à trois colonnes.  • a magnetic structure with three columns.
un étage redresseur dodécaphasé pour créer le réseau continu.  a 12-phase rectifier stage to create the continuous network.
L' invention concerne également un procédé d'alimentation électrique d'un aéronef comportant un réseau électrique comprenant des générateurs principaux alimentant des canaux de distribution électrique, des cœurs électriques, et des charges, dans lequel on génère les composantes directes et inverses de courant à l'aide de ces générateurs, caractérisé en ce qu'on met en place un neutre artificiel au niveau des cœurs électriques et en ce que l'on génère la composante homopolaire à l'aide d'un équipement spécifique, qui est un équipement du réseau électrique. Cet équipement du réseau électrique, peut comprendre un transformateur. Ce peut être un transformateur- redresseur .  The invention also relates to a method for powering an aircraft comprising an electrical network comprising main generators supplying electrical distribution channels, electric cores, and loads, in which the direct and reverse current components are generated. using these generators, characterized by setting up an artificial neutral at the level of the electric cores and in that the homopolar component is generated by means of a specific equipment, which is an equipment of the electrical network. This equipment of the electrical network, can include a transformer. It can be a transformer-rectifier.
L'invention permet ainsi la suppression de la distribution du neutre entre les générateurs principaux et les cœurs électriques à l'aide de cables, avec la mise en place d'un neutre artificiel au niveau des cœurs électriques, ce qui permet de réaliser des économies de masse de l'aéronef et de dimensionnement de ces générateurs. La création d'un neutre artificiel en utilisant un générateur homopolaire permet, en effet, de véhiculer les courants de défaut se répartissant sur trois phases sous la forme de trois composantes homopolaires et non plus seulement sur la seule phase en court-circuit. The invention thus makes it possible to eliminate the distribution of the neutral between the generators and the electric cores using cables, with the establishment of an artificial neutral in the electric cores, which allows for savings in mass of the aircraft and sizing of these generators. The creation of an artificial neutral using a homopolar generator makes it possible, in fact, to convey the fault currents that are distributed over three phases in the form of three homopolar components and no longer only on the single short-circuit phase.
L'utilisation d'un équipement déjà existant dans le réseau électrique comme générateur homopolaire permet de réaliser des économies de masse en évitant de rajouter un équipement supplémentaire.  The use of equipment already existing in the electricity network as a homopolar generator makes it possible to save mass by avoiding adding additional equipment.
L'utilisation d'un transformateur- redresseur TRU comme générateur homopolaire permet de mutualiser la fonction de générateur homopolaire sur un équipement existant en connectant le neutre du primaire du transformateur au PVR de l'avion.  The use of a TRU transformer-rectifier as a homopolar generator makes it possible to pool the homopolar generator function on an existing equipment by connecting the neutral of the primary of the transformer to the PVR of the aircraft.
BRÈVE DESCRIPTION DES DESSINS BRIEF DESCRIPTION OF THE DRAWINGS
Les figures 1, 2 et 3 illustrent un système d'alimentation électrique d'un avion selon l'art connu.  Figures 1, 2 and 3 illustrate a power system of an aircraft according to the prior art.
La figure 4 illustre l'intégration d'un générateur homopolaire dans un réseau électrique selon 1' invention .  FIG. 4 illustrates the integration of a homopolar generator in an electrical network according to the invention.
La figure 5 illustre la réalisation du générateur homopolaire illustré sur la figure 4 en utilisant un transformateur dont le primaire est couplé en étoile. La figure 6 illustre un mode de réalisation du système de l'invention dans lequel un transformateur-redresseur (TRU) est utilisé comme générateur homopolaire. FIG. 5 illustrates the embodiment of the homopolar generator illustrated in FIG. 4 using a transformer whose primer is coupled in a star. FIG. 6 illustrates an embodiment of the system of the invention in which a transformer-rectifier (TRU) is used as homopolar generator.
La figure 7 illustre la répartition des courants dans un transformateur-redresseur tel qu'illustré sur la figure 6 en cas de défaut.  Figure 7 illustrates the current distribution in a transformer-rectifier as shown in Figure 6 in case of a fault.
EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERS Dans la suite de la description, les références utilisées pour les éléments illustrés sur la figure 2 sont conservées pour illustrer des éléments analogues sur les figures 4, 5 et 6. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS In the remainder of the description, the references used for the elements illustrated in FIG. 2 are preserved to illustrate similar elements in FIGS. 4, 5 and 6.
Le système d'alimentation électrique de l'invention, comme illustré sur la figure 4, comprend ainsi un réseau électrique constitué d'un générateur principal G, d'un cœur électrique 11, d'une charge 12 en défaut, et le l'ESN 10 de l'avion. Il comprend, de plus, un générateur homopolaire 30.  The power supply system of the invention, as illustrated in FIG. 4, thus comprises an electrical network consisting of a main generator G, an electric core 11, a load 12 in default, and the ESN 10 of the aircraft. It further comprises a homopolar generator 30.
Comme cela est bien connu d'un homme du métier, un générateur homopolaire permet de créer un neutre impédant sur un réseau électrique n'en comportant pas, et de mettre ce réseau à la terre à travers cette impédance. L'impédance est calculée de façon à limiter le courant de défaut à une valeur déterminée. La valeur du courant de défaut dépend du réseau que l'on veut protéger.  As is well known to a person skilled in the art, a homopolar generator makes it possible to create an impedant neutral on an electrical network that does not have one, and to ground this network through this impedance. The impedance is calculated to limit the fault current to a specified value. The value of the fault current depends on the network to be protected.
Un tel générateur homopolaire 30 est caractérisé par :  Such a homopolar generator 30 is characterized by:
- une faible impédance homopolaire pour faciliter la circulation des composantes homopolaires, - une forte impédance directe pour que le dispositif ne se comporte pas comme une charge. a low homopolar impedance to facilitate the circulation of homopolar components, - a strong direct impedance so that the device does not behave like a load.
Dans l'invention, un tel générateur homopolaire 30 permet de créer un neutre artificiel qui permet de supprimer les câbles de neutre provenant des générateurs principaux.  In the invention, such a homopolar generator 30 makes it possible to create an artificial neutral which makes it possible to eliminate the neutral cables coming from the main generators.
Ainsi, comme le montre la figure 4, dans le cas d'une charge 12 en défaut phase-terre, le courant de défaut id est véhiculé vers le réseau triphasé par l'intermédiaire du générateur homopolaire 30 sous forme de trois composantes homopolaires i0 =— , qui se répartissent sur les trois phases. Thus, as shown in FIG. 4, in the case of a load 12 in phase-to-earth fault, the fault current i d is conveyed to the three-phase network via the homopolar generator 30 in the form of three homopolar components i 0 = -, which are distributed over the three phases.
Dans un mode de réalisation avantageux de l'invention, illustré sur la figure 5, la fonction générateur homopolaire peut être réalisée avec un équipement existant dans le réseau électrique de l'avion ce qui permet de réaliser des économies de masse. Cependant, il est possible d'ajouter un équipement supplémentaire qui permet de créer un neutre artificiel et d'assurer ainsi la fonction de générateur homopolaire. Cet équipement peut être, par exemple, un transformateur 40. Le secondaire de ce transformateur peut être ou non relié à des charges fonctionnelles 41. Ce transformateur 40 doit posséder les caractéristiques suivantes :  In an advantageous embodiment of the invention, illustrated in Figure 5, the homopolar generator function can be performed with existing equipment in the aircraft electrical network which allows for mass savings. However, it is possible to add additional equipment that allows to create an artificial neutral and thus ensure the homopolar generator function. This equipment may be, for example, a transformer 40. The secondary of this transformer may or may not be connected to functional loads 41. This transformer 40 must have the following characteristics:
- une isolation galvanique entre primaire et secondaire, condition nécessaire pour que les charges électriques 41 reliées au secondaire du transformateur 40 ne soient pas perturbées par la remontée des courants de défaut, - un primaire couplé soit en étoile, soit en zigzag, a galvanic isolation between primary and secondary, a necessary condition so that the electric charges 41 connected to the secondary of the transformer 40 are not disturbed by the rise of the fault currents, a primary coupled in either star or zigzag,
- le neutre du primaire mis à la terre,  - the neutral of the primary grounded,
- une structure magnétique à trois colonnes afin de minimiser l'impédance homopolaire.  a magnetic structure with three columns in order to minimize the homopolar impedance.
L' invention permet ainsi de réduire la masse de l'avion, du fait principalement de la suppression du câble de neutre.  The invention thus makes it possible to reduce the mass of the aircraft, mainly because of the removal of the neutral cable.
L' invention permet également :  The invention also allows:
- d'augmenter la puissance massique des générateurs grâce à l'augmentation de la valeur du fondamental,  to increase the mass power of the generators by increasing the value of the fundamental,
- d'améliorer la qualité du réseau électrique en atténuant un peu plus les harmoniques 5 et 7.  - to improve the quality of the electricity network by slightly attenuating the harmonics 5 and 7.
En effet, le fait de ne plus raccorder le neutre des générateurs empêche la circulation des harmoniques 3. La structure de bobinages à pas 2/3, qui présente l'inconvénient d'atténuer le fondamental des courants, n'est donc plus nécessaire pour éliminer les harmoniques 3. On peut donc utiliser un autre type de bobinage, par exemple un bobinage à pas 5/6, qui permet de minimiser les harmoniques 5 et 7 tout en obtenant une valeur de fondamental de 10 % supérieure par rapport à un bobinage de pas 2/3.  Indeed, the fact of not connecting the neutral of the generators prevents the flow of harmonics 3. The winding structure 2/3 pitch, which has the disadvantage of attenuating the fundamental currents, is no longer necessary for eliminating the harmonics 3. It is therefore possible to use another type of winding, for example a winding with a pitch of 5/6, which makes it possible to minimize the harmonics 5 and 7 while obtaining a fundamental value of 10% higher compared to a winding step 2/3.
L'invention permet, enfin, d'obtenir une répartition des courants de défaut sur trois phases sous la forme de trois composantes homopolaires, contrairement au système de l'art connu, dans lequel l'intégralité des courant de défauts circulent sur la phase en court-circuit. Ainsi, dans l'invention, à courant de défaut donné, le générateur doit uniquement fournir 2/3 du courant de défaut sur la phase en court- circuit au lieu de son intégralité, avant les protections se déclenchent. Le dimensionnement des générateurs devient donc moins contraignant vis-à-vis des courants de court-circuit. Finally, the invention makes it possible to obtain a distribution of the three-phase fault currents in the form of three homopolar components, unlike the known-art system, in which all of the fault currents flow on the phase in short circuit. Thus, in the invention, given fault current, the generator must only provide 2/3 of the fault current on the short-circuit phase instead of its entirety, before the protections are triggered. The sizing of the generators therefore becomes less restrictive with respect to the short-circuit currents.
Exemple d' application Application example
Dans un exemple d'application, la remontée des courants de défaut et de déséquilibre est assurée par un neutre artificiel réalisé avec un transformateur-redresseur TRU (« Transformer Rectifier Unit ») fonctionnant en tant que générateur homopolaire .  In an application example, the rise of the fault and unbalance currents is ensured by an artificial neutral made with a transformer-rectifier TRU ("Transformer Rectifier Unit") functioning as homopolar generator.
Un tel transformateur-redresseur TRU 59, utilisé pour créer un réseau continu à partir d'un réseau triphasé alternatif, est composé de :  Such a transformer-rectifier TRU 59, used to create a continuous network from a three-phase AC network, is composed of:
un transformateur triphasé à isolement galvanique comprenant :  a three-phase transformer with galvanic isolation comprising:
• un primaire en étoile 60,  A star primer 60,
• un secondaire en triangle 62,  • a secondary triangle 62,
• un secondaire en étoile 61,  • a star secondary 61,
• une structure magnétique 63 à trois colonnes.  A magnetic structure 63 with three columns.
- un étage redresseur dodécaphasé 64 pour créer le réseau continu  a twelve-phase rectifier stage 64 to create the continuous network
Dans cet exemple de réalisation, le neutre In this embodiment, the neutral
N' du primaire du transformateur 60 est raccordé par une liaison 50 à l'ESN 10 de l'avion, comme illustré sur la figure 6. La remontée des courants homopolaires au primaire ne perturbe pas le réseau DC en sortie du TRU 59. L'isolation galvanique entre le primaire 60 et les deux secondaires 61 et 62 couplés en étoile et en triangle sans neutre distribué ne permettent pas la circulation de composantes homopolaires . N 'of the primary of the transformer 60 is connected by a link 50 to the ESN 10 of the aircraft, as shown in FIG. 6. The rise of the homopolar currents in the primary does not disturb the DC network at the output of the TRU 59. L galvanic isolation between the primary 60 and the two secondary 61 and 62 coupled in star and in triangle without distributed neutral does not allow the circulation of homopolar components.
La figure 7 illustre la répartition des courants dans le transformateur 59 en cas de défaut. On a ainsi :  Figure 7 illustrates the distribution of currents in the transformer 59 in the event of a fault. We thus have:
- Au primaire 60 du transformateur 59, les courants triphasés directs ipA, ipB , ipC véhiculant la puissance vers le réseau DC et les courants homopolaires i0 provenant des déséquilibres sur le réseau électrique se superposent. At the primary 60 of the transformer 59, the direct three-phase currents i pA , i pB , i pC carrying the power to the DC network and the zero-sequence currents i 0 coming from the imbalances on the electrical network are superimposed.
Aux secondaires 61 et 62 du transformateur 59, les courants triphasés directs isa , isb, isc et ij , isb\ ij véhiculant la puissance vers le réseau DC sont les seuls à circuler vers le redresseur dodécaphasé 64. 61 and 62 to the secondary of the transformer 59, the direct three-phase currents i sa, i sb, i sc and ij, i sb \ ij conveying power to the DC network are the only flow to the twelve-phase rectifier 64.
REFERENCES REFERENCES
[1] « Protection des réseaux-généralités » par Claude Corroyer (Techniques de l'ingénieur D4800, pp 1-16, 1991) . [1] "Protection of networks-general" by Claude Corroyer (Engineering Techniques D4800, pp 1-16, 1991).

Claims

REVENDICATIONS
1. Système d'alimentation électrique d'un aéronef comportant un réseau électrique comprenant des générateurs principaux (G) alimentant des canaux de distribution électrique, des cœurs électriques (11), et des charges (12), caractérisé en ce qu'il comprend des moyens de mise en place d'un neutre artificiel au niveau des cœurs électriques comportant un générateur homopolaire (30), qui est un équipement du réseau électrique . A power supply system for an aircraft comprising an electrical network comprising main generators (G) supplying electrical distribution channels, electric cores (11), and loads (12), characterized in that it comprises means for setting up an artificial neutral at the level of the electric cores comprising a homopolar generator (30), which is an equipment of the electrical network.
2. Système selon la revendication 1, dans lequel le générateur homopolaire comprend un transformateur. 2. System according to claim 1, wherein the homopolar generator comprises a transformer.
3. Système selon la revendication 2, dans lequel le générateur homopolaire est un transformateur- redresseur (59) . 3. System according to claim 2, wherein the homopolar generator is a transformer-rectifier (59).
4. Système selon la revendication 3, dans lequel le transformateur-redresseur (59) comporte : 4. System according to claim 3, wherein the transformer-rectifier (59) comprises:
un transformateur triphasé à isolement galvanique comprenant :  a three-phase transformer with galvanic isolation comprising:
• un primaire en étoile (60), dont le neutre est connecté à la terre,  A star primer (60), the neutral of which is connected to the earth,
• un secondaire en triangle (62),  A triangle secondary (62),
• un secondaire en étoile (61),  • a star secondary (61),
• une structure magnétique (63) à trois colonnes.  A magnetic structure (63) with three columns.
- un étage redresseur dodécaphasé (64) pour créer le réseau continu. - A twelve-phase rectifier stage (64) to create the continuous network.
5. Procédé d'alimentation électrique d'un aéronef comportant un réseau électrique comprenant des générateurs principaux (G) alimentant des canaux de distribution électrique, des cœurs électriques (11), et des charges (12), dans lequel on génère les composantes directes et inverses de courant à l'aide de ces générateurs, caractérisé en ce qu'on met en place un neutre artificiel au niveau des cœurs électriques et en ce que l'on génère la composante homopolaire à l'aide d'un équipement spécifique, qui est un équipement du réseau électrique. 5. A method of powering an aircraft comprising an electrical network comprising main generators (G) supplying electrical distribution channels, electric cores (11), and loads (12), in which the direct components are generated. and inverse of current using these generators, characterized in that an artificial neutral is set up at the level of the electric cores and in that the homopolar component is generated using a specific equipment, which is an equipment of the electrical network.
6. Procédé selon la revendication 5, dans lequel l'équipement spécifique comprend un transformateur . 6. The method of claim 5, wherein the specific equipment comprises a transformer.
7. Procédé selon la revendication 5, dans lequel cet équipement spécifique est un transformateur- redresseur. 7. The method of claim 5, wherein said specific equipment is a transformer-rectifier.
8. Aéronef comportant un système selon l'une quelconque des revendications 1 à 4. Aircraft comprising a system according to any one of claims 1 to 4.
EP10745333A 2009-06-29 2010-06-25 System and method for supplying electric power to an aircraft Withdrawn EP2449647A1 (en)

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FR0954425A FR2947245B1 (en) 2009-06-29 2009-06-29 SYSTEM AND METHOD FOR ELECTRICALLY POWERING AN AIRCRAFT
PCT/FR2010/051313 WO2011001079A1 (en) 2009-06-29 2010-06-25 System and method for supplying electric power to an aircraft

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CN102804539A (en) 2012-11-28
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US9006923B2 (en) 2015-04-14
CN102804539B (en) 2015-04-08
CA2766488A1 (en) 2011-01-06
CA2766488C (en) 2016-09-13
WO2011001079A1 (en) 2011-01-06
FR2947245A1 (en) 2010-12-31

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