EP2548249A2 - Dispositif de régulation d'énergie destiné à réguler des sources d'énergie hybrides pour un aéronef - Google Patents

Dispositif de régulation d'énergie destiné à réguler des sources d'énergie hybrides pour un aéronef

Info

Publication number
EP2548249A2
EP2548249A2 EP11707638A EP11707638A EP2548249A2 EP 2548249 A2 EP2548249 A2 EP 2548249A2 EP 11707638 A EP11707638 A EP 11707638A EP 11707638 A EP11707638 A EP 11707638A EP 2548249 A2 EP2548249 A2 EP 2548249A2
Authority
EP
European Patent Office
Prior art keywords
consumer
energy
control device
resource
energy control
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Withdrawn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
EP11707638A
Other languages
German (de)
English (en)
Inventor
Andreas Westenberger
Lars Frahm
Till Marquardt
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 GmbH
Original Assignee
Airbus Operations GmbH
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 GmbH filed Critical Airbus Operations GmbH
Publication of EP2548249A2 publication Critical patent/EP2548249A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • B64D41/00—Power installations for auxiliary purposes
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M16/00—Structural combinations of different types of electrochemical generators
    • H01M16/003—Structural combinations of different types of electrochemical generators of fuel cells with other electrochemical devices, e.g. capacitors, electrolysers
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04007—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
    • H01M8/0432—Temperature; Ambient temperature
    • H01M8/04373—Temperature; Ambient temperature of auxiliary devices, e.g. reformers, compressors, burners
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
    • H01M8/0438—Pressure; Ambient pressure; Flow
    • H01M8/04402—Pressure; Ambient pressure; Flow of anode exhausts
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
    • H01M8/0438—Pressure; Ambient pressure; Flow
    • H01M8/0441—Pressure; Ambient pressure; Flow of cathode exhausts
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
    • H01M8/0438—Pressure; Ambient pressure; Flow
    • H01M8/04425—Pressure; Ambient pressure; Flow at auxiliary devices, e.g. reformers, compressors, burners
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
    • H01M8/04537—Electric variables
    • H01M8/04574—Current
    • H01M8/04589—Current of fuel cell stacks
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04313—Processes for controlling fuel cells or fuel cell systems characterised by the detection or assessment of variables; characterised by the detection or assessment of failure or abnormal function
    • H01M8/04537—Electric variables
    • H01M8/04604—Power, energy, capacity or load
    • H01M8/04626—Power, energy, capacity or load of auxiliary devices, e.g. batteries, capacitors
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04694—Processes for controlling fuel cells or fuel cell systems characterised by variables to be controlled
    • H01M8/04701—Temperature
    • H01M8/04738—Temperature of auxiliary devices, e.g. reformer, compressor, burner
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04694—Processes for controlling fuel cells or fuel cell systems characterised by variables to be controlled
    • H01M8/04746—Pressure; Flow
    • H01M8/04776—Pressure; Flow at auxiliary devices, e.g. reformer, compressor, burner
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04298—Processes for controlling fuel cells or fuel cell systems
    • H01M8/04694—Processes for controlling fuel cells or fuel cell systems characterised by variables to be controlled
    • H01M8/04858—Electric variables
    • H01M8/04925—Power, energy, capacity or load
    • H01M8/04947—Power, energy, capacity or load of auxiliary devices, e.g. batteries, capacitors
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/24—Grouping of fuel cells, e.g. stacking of fuel cells
    • H01M8/249—Grouping of fuel cells, e.g. stacking of fuel cells comprising two or more groupings of fuel cells, e.g. modular assemblies
    • 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
    • H02J1/00—Circuit arrangements for dc mains or dc distribution networks
    • H02J1/14—Balancing the load in a network
    • 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
    • H02J3/12—Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load
    • H02J3/14—Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load by switching loads on to, or off from, network, e.g. progressively balanced loading
    • 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
    • H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers
    • 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
    • H02J4/00—Circuit arrangements for mains or distribution networks not specified as ac or dc
    • 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
    • B64D41/00—Power installations for auxiliary purposes
    • B64D2041/005—Fuel cells
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2250/00—Fuel cells for particular applications; Specific features of fuel cell system
    • H01M2250/20—Fuel cells in motive systems, e.g. vehicle, ship, plane
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2250/00—Fuel cells for particular applications; Specific features of fuel cell system
    • H01M2250/40—Combination of fuel cells with other energy production systems
    • 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
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
    • H02J7/345—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering using capacitors as storage or buffering devices
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
    • H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
    • 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
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/30—Hydrogen technology
    • Y02E60/50—Fuel cells
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S903/00—Hybrid electric vehicles, HEVS
    • Y10S903/902—Prime movers comprising electrical and internal combustion motors
    • Y10S903/903—Prime movers comprising electrical and internal combustion motors having energy storing means, e.g. battery, capacitor

Definitions

  • Energy control device for controlling hybrid energy sources for an aircraft
  • the present invention relates to an energy control device for controlling hybrid energy sources for an aircraft, an energy system for an aircraft, a method for controlling hybrid energy sources for an aircraft, and a vehicle
  • Energy sources such as solar cells, fuel cells or batteries are used.
  • Energy control device for controlling multiple hybrid energy sources.
  • an energy control device for controlling hybrid energy sources for an aircraft an energy system for an aircraft, a method for controlling hybrid energy sources for an aircraft and by the use of an energy control device and an aircraft with an energy control device having the features according to the independent patent claims.
  • an energy control device for controlling hybrid energy sources for an aircraft is provided, wherein the energy control device is adapted to meet a need for a first
  • a hybrid energy source By means of a hybrid energy source, at least the first consumable and the second consumable can be generated simultaneously.
  • the energy control device controls the power source depending on the need for the first resource and a second resource, such that the demand for the first resource and the second resource is covered by the energy source. If there is no need for one of the first or second consumables, which can be provided by the energy source, and consumed, the excess consumable is applied to a third consumer.
  • the energy control device is preferably designed to determine the operating characteristic of the energy source for adapting the control. Thereby, a targeted control of the energy source for generating a sufficient amount of the required resources or
  • the term "consumables” means a means which is required for the operation of a consumer and can be manufactured or provided by a power source. Such a resource does not necessarily have to be of a material nature, but can also be realized in the form of electric power, heat or the like.
  • the need for a resource may be both an absolute value, i. Energy, volume, mass or the like, but also as a time derivative thereof, i. E. in the form of a performance, one
  • operating characteristic of an energy source designates the general characteristics of an energy source and could, for example, be a definition of an energy source
  • Ratio between educts and products or supplies An operating characteristic could be determined by the amount of incorporated reactants and by the amount of products delivered, such as electrical energy, thermal energy and other products. Furthermore, environmental conditions such as pressure, temperature or humidity may be affected by the operating characteristics. On the basis of the operating characteristics of the efficiency of a device or an energy source can also be determined. The best efficiency is achieved at a working or operating point at which from a certain amount of educts the largest amount of desired products, such as electrical energy is provided. For example, the operating characteristic may provide clues as to which operating parameters, such as educt feed, valve positions, or the like, of the energy source must be influenced in what manner to achieve a desired supply or production of the desired consumable.
  • the present invention provides an energy control device that is capable of increasing the efficiency of an aircraft such that multiple consumers that have different fuel efficiency
  • Require supplies can be operated by a common source of energy. Since, according to experience, the necessary energy for a first consumer or a second consumer does not exist over the entire mission or
  • the energy control device can act on a third consumer with an excess demand, so that the power source is able to perform a steady and uninterrupted operation.
  • the third consumer as a means of consumption for a Excess supplies ensure the regular operation of the energy source and therefore of the first and second consumers.
  • the interaction with regard to an electrical or thermodynamic efficiency or with regard to the additional products of energy sources can be improved by the energy control device according to the invention, which optimizes the overall energy balance of the aircraft.
  • the nature of the third consumer is not necessarily prescribed in this context. However, this third consumer could preferably be set up to accommodate a large number of different resources in order to ensure regular operation or at least to dispose of an excess of supplies. Some of several possible types of construction or nature of the third consumer will be discussed in more detail below.
  • first consumer and second consumer does not mean that the energy control device of the present invention is exclusively capable of controlling only a single first consumer and only a single second consumer.
  • the wording should be understood to mean that at least two different types of consumers in an aircraft can be supplied with energy by a source of energy, but this does not preclude any number of other consumers requiring different types of resources from also having to do so Plane could be arranged.
  • the first consumer and the second consumer may also be grouped into one system or subsystem that has multiple
  • the energy control device can always be a proper operation of the power source and thus all consumers done, the power of the power source could be coordinated to the effect that the relevant first or second consumer with the greatest need for supplies significantly determines the operation of the power source and all excess supplies, by-products and the like by said third
  • Consumers who may also be a plurality of different third consumers, consumed or dissipated.
  • the third consumer is adapted to be additionally charged with a third resource. This means for the energy control device that for the operation of the third
  • a third resource is directed to the third consumer and this may be more efficient than operating the power source and giving up the first and second
  • the operation of the third consumer could be more efficient, with a different and more tailored to the third consumer needs.
  • the energy control device is a consumable from the group consisting of electrical energy and Additional products selected, wherein the additional product is selected from the group consisting of water, thermal energy and low-oxygen exhaust air.
  • the additional product is selected from the group consisting of water, thermal energy and low-oxygen exhaust air.
  • This combination of different resources can supply a wide variety of consumers, so that, for example, a main consumer requires electrical energy, while other consumers need more water, thermal energy or low-oxygen exhaust air.
  • the low-oxygen exhaust air could be used to inertise rooms, the thermal energy for defrosting the flow-exposed surfaces of the aircraft and water could be used for example for the supply of sanitary facilities.
  • the energy control device is set up such that, depending on a flight phase, the need for the first resource and the need for the second resource can be determined.
  • the energy control device is set up such that the need for a third requirement means of another
  • the energy control device is set up in such a way that a priority can be assigned to each of the first consumer and the second consumer, wherein the energy regulation device is set up such that depending on the priority the relevant consumable can be supplied to the first consumer and the second consumer. For example, if a second consumer is only directed to making a little-used convenience feature, low priority could be given. For example, if the operation of the first consumer over a longer period is not planned and the second consumer only a resource available when the first consumer requests this first resource, it might be advantageous from an energy point of view, the second consumer over a longer period not operate or only with reduced power. The second consumer in such a case would receive a lower priority than the first consumer.
  • the energy control device could be set up in such a way that the priority can be allocated taking account of flight safety factors. In a reverse case, as already mentioned above, this could lead to safety-critical functions being given such high priority that they can be maintained over the entire mission or mission period.
  • a first or second consumer could be an inerting device for a tank or extinguishing device, which is designed to operate by means of oxygen-poor air
  • An inventive energy system for an aircraft could be a
  • Energy control device at least a first consumer and at least a second consumer, and having a power source, wherein the
  • the power controller controls the power source depending on the need for the first resource and a second resource and, if there is no need for one of the first or second resources to be provided by the energy source and excess, applies a third consumer to the excess resource.
  • the first consumer and / or the second consumer is adapted to receive both a first and a second resource for providing a function.
  • the energy system according to the invention is capable of supplying, for example, an excess supply already to one of the first or second consumers.
  • hybrid consumers Such consumers may be referred to as hybrid consumers.
  • hybrid consumers In general, it would be beneficial to design several consumers so that they tolerate a hybrid power supply. These consumers should be so neutral in the case of electrical supply within certain operating limits that they do not adversely affect other consumers on board the aircraft.
  • electrical energy for the local generation of heat such consumers could also absorb waste heat from an energy source which is forwarded to a specific location.
  • the energy control device is accordingly preferably configured to have at least one hybrid
  • third consumers could be provided that consume the excess supplies substantially without effect, for example by being supplied to the environment of the aircraft.
  • An aircraft according to the invention with an energy control device such as
  • an excess of electrical power could be used as thermal power in a water tank or a kerosene tank up to a certain safe limit be filed.
  • Other consumers could for example be realized with batteries or pressure or vacuum tanks that can be charged by means of an excess electrical power. At the same time could
  • Fig. 1 shows a first embodiment of the control device according to the invention.
  • Fig. 2 shows a second embodiment of the invention
  • Fig. 3 shows a third embodiment of the invention
  • 4a and 4b show a schematic block-based representation of a
  • FIG. 5 shows an aircraft with at least one inventive
  • the energy control device 2 is set up to drive, by way of example, two energy sources El and E2.
  • the energy control device 2 is adapted to detect an operating characteristic of the power sources E1 and E2.
  • the energy control device 2 is further configured to detect a need for a first resource of at least one first consumer VI and a need for a second resource of at least one second consumer V2.
  • the energy source El and / or E2 is capable of producing at least the first resource and the second resource simultaneously. In this case, the energy control device 2 controls the
  • the energy control device 2 via sensors, data transmission means or other means the necessary
  • Deicing systems and water consuming systems (e.g.
  • the consumables of these consumers could therefore be an electrical power in the form of direct current or alternating current, a mass flow of oxygen
  • Demand agent streams can be detected by a corresponding sensor. while at the same time a consumer VI or V2 could communicate to the energy control device 2 a momentary shortage of a demand flow via a corresponding signal by means of a signal line or the like.
  • the energy source El is considered to be one
  • Fuel cell running the supplied via educts electric power
  • the energy control device 2 is able to determine the operating characteristics of the power source El. This makes it possible to determine how an activation of the supply of educts could cause the fuel cell to vary, ie to increase or decrease, the products supplied, in order to meet different supply flows.
  • the energy source E2 could be implemented as a conventional engine generator, whose efficiency as well as electrical maximum power is known. The maximum deliverable electrical power of the engine generator could continue by determining the speed of the engine and its
  • Engine generator have deliverable shaft power.
  • the energy control device 2 is capable of informing the consumers VI, V2 and V3 of the operating characteristics by knowing the operating characteristics of the power sources El and E2 and the required resource flows
  • Energy control device 2 is therefore arranged to supply the consumer with the highest priority with a maximum share of the required demand flow through a priority distribution among consumers VI, V2 and V3, while the other consumers VI, V2 or V3 with a lower priority a smaller proportion of the relevant Received demand flow.
  • the energy control device 2 is further configured to control the energy source El and / or E2 such that excess resources can be consumed or discarded by the third consumer V3. This means that, for example, by means of a consumer VI or V2 with a high priority, the energy source E1 and / or E2 is controlled in such a way that the consumable necessary for the consumer VI or V2 is produced, as shown in FIG.
  • Constellation with the production of additional or main products For example, consumers VI and V2 could request a heat flow or a mass flow of oxygen depleted air, which, however, can be provided in fuel cell E1 only once electrical power is removed. If the entire electrical power can not be consumed, this can be supplied by the energy control device 2 to the switchable third consumer V3, in which it can then be consumed or discarded. For this reason, the third consumer V3 can be referred to as a blind consumer, which consumes the excess consumable in an effect-neutral manner in the sense of a lack of influence on the function and safety of the aircraft.
  • thermoelectric elements Conversion into a heat flow by means of thermoelectric elements or the like. Due to the "artificial" need for electric power, the production of by-products in the fuel cell El is maintained.
  • the third consumer V3 could be an electrothermal element that delivers its produced heat directly to the outside air of the aircraft.
  • the third consumer V3 could heat directly or indirectly via a buffer in the form of a water tank or a fuel tank with these options, the respective permissible operating limits must be adhered to.
  • the third consumer V3 itself could be realized as a memory temporarily storing, for example, oxygen depleted air, water or electrical energy.
  • FIG. 2 a different embodiment is shown in which consumers VI, V2 and V3 are provided, the hybrid loading with
  • Allow supplies This means that the consumers VI, V2 and V3 can each be operated with different supply streams or with a mixture of at least two different supply streams.
  • Energy control device 2 is in this case preferably able, by knowing the operating characteristics of the energy sources El and E2, to carry out a distribution of consumables VI, V2 and V3 that is as optimal as possible, so that the smallest possible amount of excess consumables arises, which must be discarded.
  • Such a hybrid consumer VI, V2 or V3 could, for example, be realized in the form of one or more de-icing devices at wing leading edges which can be acted upon both by electric current for generating heat and by a heat transfer medium flowing through or by another means for actively transferring a heat flow, to heat to the
  • another type of hybrid consumer VI, V2, or V3 could be implemented such that heat is generated or supplied in various ways in a galley or other consumer.
  • a different concept is pursued.
  • excess resources in the form of electrical energy, water, air or the like could be stored in memories 4 to be retrieved at another time or with a time lag.
  • Electrical storage could take the form of accumulators,
  • Supercapacitors or similar means can be realized. Material products such as water or air could be stored in storage tanks, such as pneumatic or hydraulic accumulators etc.
  • Fig. 4a a method according to the invention in a schematic
  • the method could exemplarily include the determination 100 of operating characteristics.
  • the need for a first resource, a second resource, possibly a third resource, etc. is determined 102, 104, 106, etc.
  • To control the energy sources it is necessary to know the deviation of the first, second, third, etc., currently provided.
  • the individual consumer's priority is also checked 120, so that if there is a need for 100, the resources available are distributed on a per-priority basis to the individual consumers VI, V2, V3, etc. 122.
  • FIG. 5 shows an aircraft 6 which is equipped with energy sources in the form of engines designated as E2 and additionally has an energy source E1 designed as a fuel cell.
  • An energy control device 2 according to the invention distributes consumables to consumers VI, V2, V31 and V32, whereby the consumers V31 and V32 are to be regarded as "third consumers” within the meaning of the invention.
  • the consumer V31 could have a heater in one
  • the consumer V32 could be designed in the form of heaters at wing leading edges of the aircraft 6 to prevent the accumulation of ice or to dissipate accumulated ice there. Also there, the heat can be carried out by means of a transfer of heat flow from the fuel cell El, as well as by applying an electric heater by electric current. Should there be any other need for heat in the aircraft 6 that should be provided by the fuel cell El, the consumer V32 could be powered by electrical energy.
  • “having” does not exclude other elements or steps, and "a” or “an” does not exclude a multitude, and it should be noted that features that are described with reference to any of the above

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  • Life Sciences & Earth Sciences (AREA)
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Abstract

L'invention concerne un dispositif de régulation d'énergie (2) destiné à réguler des sources d'énergie hybrides (E1, E2) pour un aéronef, ledit dispositif étant conçu pour déterminer une caractéristique de fonctionnement d'une source d'énergie (E1, E2), un besoin en une première ressource nécessaire d'au moins un premier consommateur (V1) et un besoin en une seconde ressource nécessaire d'un deuxième consommateur (V2). Le dispositif de régulation d'énergie (2) commande la source d'énergie (E1, E2) en fonction du besoin en la première ressource nécessaire et en la seconde ressource nécessaire et, en cas d'absence de besoin en une des première ou seconde ressources nécessaires pouvant être fournies par la source d'énergie et excédentaires, alimente un troisième consommateur (V3) à l'aide de la ressource nécessaire excédentaire. Ainsi, un système d'énergie peut faire fonctionner différents consommateurs indépendamment du type de ressource nécessaire généré et des dépendances existantes lors de leur génération.
EP11707638A 2010-03-15 2011-03-02 Dispositif de régulation d'énergie destiné à réguler des sources d'énergie hybrides pour un aéronef Withdrawn EP2548249A2 (fr)

Applications Claiming Priority (3)

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US31389710P 2010-03-15 2010-03-15
DE102010011416A DE102010011416A1 (de) 2010-03-15 2010-03-15 Energieregelvorrichtung zum Regeln hybrider Energiequellen für ein Flugzeug
PCT/EP2011/053097 WO2011113696A2 (fr) 2010-03-15 2011-03-02 Dispositif de régulation d'énergie destiné à réguler des sources d'énergie hybrides pour un aéronef

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EP (1) EP2548249A2 (fr)
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DE102011120322B4 (de) 2011-12-06 2018-01-04 Airbus Operations Gmbh Verwendung eines Verfahrens und/oder Systems zur Steuerung eines Hilfstriebwerks
DE102012002132A1 (de) * 2012-02-03 2013-08-08 Airbus Operations Gmbh Vereisungsschutzsystem für ein Flugzeug und Verfahren zum Betreiben eines Vereisungsschutzsystems
WO2013140306A1 (fr) * 2012-03-19 2013-09-26 Intertechnique Système de protection contre le givrage de voilure basé sur un système de pile à combustible
US20180319288A1 (en) * 2017-05-08 2018-11-08 Bell Helicopter Textron Inc. Ethanol-Fueled Fuel Cell Powered Aircraft
EP3823070A1 (fr) * 2019-11-12 2021-05-19 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Système de stockage d'énergie hybride

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WO2008113850A2 (fr) * 2007-03-20 2008-09-25 Airbus Operations Gmbh Dispositif régulateur de puissance pour aéronef

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US6568633B2 (en) * 2000-08-24 2003-05-27 James P. Dunn Fuel cell powered electric aircraft
DE102004044646B4 (de) * 2004-09-15 2009-08-27 Airbus Deutschland Gmbh Brennstoffzellen-System als primäre elektrische Energieversorgung für Luftfahrzeuge
DE102004058430B4 (de) * 2004-12-03 2010-07-29 Airbus Deutschland Gmbh Versorgungssystem zur Energieversorgung in einem Luftfahrzeug, Luftfahrzeug und Verfahren zum Versorgen eines Luftfahrzeugs mit Energie
WO2006077970A1 (fr) * 2005-01-24 2006-07-27 Yamaha Hatsudoki Kabushiki Kaisha Systeme de pile a combustible et son procede de demarrage
DE102008024826A1 (de) * 2008-05-23 2009-11-26 Enerday Gmbh Zusatzaggregat mit Entsalzungsvorrichtung

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WO2008113850A2 (fr) * 2007-03-20 2008-09-25 Airbus Operations Gmbh Dispositif régulateur de puissance pour aéronef

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DE102010011416A1 (de) 2011-09-15
WO2011113696A3 (fr) 2011-12-01
WO2011113696A2 (fr) 2011-09-22

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