IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0176846
(2011-07-06)
|
등록번호 |
US-8757542
(2014-06-24)
|
우선권정보 |
FR-10 02867 (2010-07-08) |
발명자
/ 주소 |
- Hopdjanian, Marie-Laure
- Connaulte, Matthieu
- Gazzino, Marc
- Mercier, Christian
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
11 인용 특허 :
4 |
초록
▼
A hybrid power plant (5) for an aircraft (1) comprises at least: a hybrid drive system (37) having a main on-board electricity network (16) and an auxiliary electricity network (34); and a selective adaptation interface (38) arranged to enable electrical energy to be exchanged selectively between th
A hybrid power plant (5) for an aircraft (1) comprises at least: a hybrid drive system (37) having a main on-board electricity network (16) and an auxiliary electricity network (34); and a selective adaptation interface (38) arranged to enable electrical energy to be exchanged selectively between the main and auxiliary electricity networks (16; 34). At least one engine and a hybrid drive auxiliary electrical machine (7, 31) are mechanically connected to a transmission (8); said machine (7) being electrically connected to at least one auxiliary electrical bus (36) in parallel with at least one auxiliary device for delivering electric charge.
대표청구항
▼
1. A rotary wing aircraft comprising: a main on-board electricity network;a power plant having at least one rotor for being driven in rotation, and at least one transmission for driving said rotor in rotation;the power plant being a hybrid power plant associating at least one main combustion engine
1. A rotary wing aircraft comprising: a main on-board electricity network;a power plant having at least one rotor for being driven in rotation, and at least one transmission for driving said rotor in rotation;the power plant being a hybrid power plant associating at least one main combustion engine with at least one hybrid drive auxiliary electrical machine;the main engine and the auxiliary electrical machine being mechanically coupled to the transmission;said auxiliary electrical machine being placed within the hybrid power plant to constitute in turn a member for mechanically driving the transmission or a member for generating electricity under the effect of being driven mechanically by said transmission;the on-board electricity network possessing at least one main electrical bus at a main nominal voltage;the main electrical bus having connected thereto at least one main device for delivering electric charge with at least one main storage battery, and a main electrical machine acting as a starter that is reversibly operable as a generator, said main electrical machine forming a starter being mechanically connected to said engine, wherein the hybrid power plant includes at least one hybrid drive system with at least one auxiliary electricity network for providing hybrid drive purposes, the auxiliary electricity network possessing a dedicated auxiliary electrical bus at an auxiliary nominal voltage, the auxiliary electrical machine being connected to the auxiliary electrical bus at the auxiliary nominal voltage;the main electrical bus and the hybrid drive auxiliary electrical bus being connected together via a selective adaptation interface in such a manner that the main on-board electricity network and the auxiliary electricity network are electrically distinct from one another, the selective adaption interface being configured to enable electrical energy to be exchanged selectively between the main and auxiliary electricity networks. 2. An aircraft according to claim 1, wherein the machine forming a starter is electrically connected to the main network via disconnection means of a main device for delivering electric charge within the main network; whereas the auxiliary electrical bus has electrically connected thereto firstly a monitoring and control module or member together with said auxiliary machine, and secondly at least one selected adaptation interface arranged by selective connection to the main electricity network to enable electrical energy to be exchanged selectively between the main and auxiliary electricity networks. 3. An aircraft according to claim 1, wherein said auxiliary machine that is mechanically connected to said transmission is electrically connected to the auxiliary electrical bus in parallel with at least one auxiliary device for delivering electric charge and at least one secondary storage battery; the auxiliary charge-delivery device, the monitoring member, the auxiliary machine, the auxiliary network, and the selective adaptation interface forming parts of the hybrid drive system. 4. An aircraft according to claim 1, wherein the power plant includes a single main gearbox (MGB) mechanically connected to at least one lift rotor of the aircraft and to a single engine such as a turboshaft engine or a diesel engine; at least one auxiliary electrical machine being connected to said gearbox. 5. An aircraft according to claim 4, wherein the power plant includes a single main gearbox (MGB), and at least two auxiliary electrical machines connected to said gearbox. 6. An aircraft according to claim 1, wherein the power plant includes a single main gearbox (MGB) that is mechanically connected to at least one lift rotor of the aircraft and to a plurality of engines, such as two turboshaft engines or two diesel engines; at least one auxiliary electrical machine being connected to said gearbox. 7. An aircraft according to claim 1, wherein the power plant includes at least one auxiliary gearbox (AGB) mechanically connected to at least one auxiliary rotor such as one or more tail rotors and/or one or more propulsion rotors of at least one lateral arrangement of propellers for a long-range high-speed rotary wing aircraft; at least one auxiliary electrical machine being connected to said gearbox. 8. An aircraft according to claim 1, wherein at least one switch is arranged in the hybrid drive system between two main and/or auxiliary buses. 9. An aircraft according to claim 1, wherein the on-board electricity network is at a main nominal voltage and/or uses a main phase type that is/are distinct respectively from an auxiliary nominal voltage and/or an auxiliary nominal phase type for the auxiliary electricity network; in which case the interface includes at least one phase converter. 10. An aircraft according to claim 9, wherein the nominal voltage and/or phase type are distinct between the main and auxiliary electricity networks, at least one phase converter of the selective exchange adaptation interface is reversible between an energy exchange direction in which electricity is delivered to the main network and an energy exchange direction in which electricity is delivered to the auxiliary electricity network. 11. An aircraft according to claim 1, wherein at least one main and/or auxiliary device for delivering electric charge is of the electrochemical and/or capacitive and/or kinetic energy type. 12. An aircraft according to claim 1, wherein the hybrid drive system is a multichannel system that includes at least two hybrid drive electrical machines, each having in common at least one auxiliary device for delivering electric charge and/or a monitoring module or member, and/or a selective adaptation interface. 13. An aircraft according to claim 1, wherein the hybrid drive system is a multichannel system and includes at least two auxiliary electrical machines, each channel having at least one auxiliary device for delivering electric charge and/or a monitoring module and/or a selective adaptation interface specific thereto. 14. An aircraft according to claim 1, wherein the hybrid power plant includes at least one main engine in the form of a turboshaft engine coupled to a machine forming a starter that can be operated reversibly as a generator and that is mechanically engaged with the turboshaft engine and placed on a main electricity network at low voltage; a hybrid drive system including at least one auxiliary electrical machine in the form of a high voltage electric motor/generator, said auxiliary electric motor being mechanically engaged with the transmission and being placed on the high voltage auxiliary electricity network of said hybrid drive system. 15. An aircraft according to claim 1, wherein the hybrid power plant includes electronic means for controlling operation of the main engine(s) and/or of the auxiliary electric motors, said means being in communication with at least one manual control desk and/or a flight controller of the hybrid power plant and connected to and powered by the main electricity network. 16. An aircraft according to claim 1, wherein the hybrid power plant includes electronic means for monitoring the state and the operation of the main engine(s) and/or of the auxiliary electrical machine(s), said monitoring means being connected to and powered by the main electricity network. 17. An aircraft according to claim 16, wherein the monitoring means are in communication with means providing information about the state and the operation of the main engine(s) and/or of the auxiliary electrical machine(s), said monitoring electrical machines being connected to and powered by the main electricity network. 18. An aircraft according to claim 1, wherein the aircraft includes an auxiliary power unit with an auxiliary generator; said auxiliary power unit is mechanically connected to said transmission of the hybrid power plant in such a manner as to be connected to and deliver electricity to the on-board electricity network and/or to the auxiliary electricity network in certain stages of flight. 19. An aircraft according to claim 16, wherein the electronic monitoring means are associated with measurement, analysis, and storage means that include at least one of the following components: a voltage sensor for sensing the voltage of at least one of the main electricity network and/or the auxiliary electricity network, said voltage sensor being associated with comparator means for comparing the sensed voltage(s) with at least one setpoint voltage;a current sensor for sensing the current in at least one of the main electricity network and/or the auxiliary electricity network, said current sensor being associated with comparator means for comparing the sensed current(s) and at least one setpoint current;a temperature sensor for sensing the temperature of at least one of the main electricity network and/or the auxiliary electricity network, the temperature sensor being associated with comparator means for comparing the sensed temperature(s) and at least one setpoint temperature;analyzer means for analyzing the level of charge in at least one charge-delivery device of the main and/or auxiliary on-board electricity network;a speed sensor for sensing the speed of rotation of at least one of the engine(s) and/or the electrical machine(s), and/or the transmission; anda counter for counting the number of recharging and discharging cycles of at least one charge-delivery device of the main and/or auxiliary on-board electricity network, said cycle counter being associated with analyzer means for analyzing the lifetime of the charge-delivery device(s). 20. An aircraft according to claim 1, wherein the hybrid drive system includes at least one kinetic energy recovery system (KERS) that is mechanically or electrically connected to at least one auxiliary electrical machine for recovering a fraction of the kinetic energy generated when it decelerates, and electrically connected to the auxiliary electricity network so as to be capable of powering said auxiliary electrical machine in return, when necessary. 21. An aircraft according to claim 19, wherein in the event of a power plant being provided with a kinetic energy recovery system, a speed sensor is coupled to said system so as to determine its instantaneous speed of rotation, the speed sensor being incorporated in the measurement, analysis, and storage means. 22. A method of operating a rotary wing aircraft, the aircraft having: a main on-board electricity network;a power plant having at least one rotor for being driven in rotation, and at least one transmission for driving said rotor in rotation;the power plant being a hybrid power plant associating at least one main combustion engine with at least one hybrid drive auxiliary electrical machine;the main engine and the auxiliary electrical machine being mechanically coupled to the transmission;the auxiliary electrical machine being placed within the hybrid power plant to constitute in turn a member for mechanically driving the transmission or a member for generating electricity under the effect of being driven mechanically by said transmission;the on-board electricity network possessing at least one main electrical bus at a main nominal voltage;the main electrical bus having connected thereto at least one main device for delivering electric charge with at least one main storage battery, and a main electrical machine acting as a starter that is reversibly operable as a generator, said main electrical machine forming a starter being mechanically connected to said engine, the hybrid power plant including at least one hybrid drive system with at least one auxiliary electricity network for providing hybrid drive purposes, the auxiliary electricity network possessing a dedicated auxiliary electrical bus at an auxiliary nominal voltage, the auxiliary electrical machine being connected to the auxiliary electrical bus at the auxiliary nominal voltage;the main electrical bus and the hybrid drive auxiliary electrical bus being connected together via a selective adaptation interface in such a manner that the main on-board electricity network and the auxiliary electricity network are electrically distinct from one another, the selective adaption interface being configured to enable electrical energy to be exchanged selectively between the main and auxiliary electricity networks,the method comprising:in a stage of starting the engine, initiating said starting from the starter powered via the auxiliary electricity network, with this applying with an engine;in a flight stage, driving the transmission via said engine in a mode of self-sustained operation; andin a flight stage and in order to deliver extra mechanical energy occasionally to the transmission, driving the transmission from the auxiliary electrical machine operating as a motor and powered by at least one device for delivering electric charge of the main electricity network, in addition to the drive delivered to the transmission by the engine, for the purpose of performing specific flight controls and/or of taking the place of the drive delivered to the transmission by said engine in the event of the engine failing. 23. A method according to claim 22, wherein the method provides for powering the on-board electricity network from the auxiliary electricity network via the selective adaptation interface, where appropriate, in order to: stand in for a possible failure of at least one of the device for delivering charge of the main electricity network and/or a reversible electrical machine; and/orrelieve the engine from driving the reversible electrical machine. 24. A method according to claim 22, wherein the method provides: in a stage of starting the engine, driving the transmission by an auxiliary electrical machine at a speed setting that is faster than that used when driving the engine by the electrical machine forming a reversible starter in order to decouple the engine from said transmission;allowing the engine to idle while the engine is in a mode of self-sustained operation; andcoupling the engine with the transmission by docking by progressively accelerating the engine up to a speed corresponding to the speed at which the transmission is driven by said auxiliary electrical machine, via a freewheel or analogous means; said freewheel between the engine and the transmission enabling them to be decoupled. 25. A method according to claim 22, wherein the method provides that in a flight stage and on the ground mechanical energy is taken from the transmission by the auxiliary electric motor in order to brake said rotor that is connected to said transmission. 26. A method according to claim 22, wherein display means respond to the data delivered by the measurement, analysis, and storage means to produce information representative of a length of time remaining during which the hybrid drive electrical machine can be used at maximum power, said remaining length of time being taken into account on the basis of a state of instantaneous load on said electrical machine and of the first power that the machine is capable of delivering at the given instant.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.