• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    To reduce the mass of a hybrid propulsion system (30) for a multirotor rotary wing aircraft, the system comprises at least one inverter (36) configured to supply in parallel a plurality of electric motors (46A, 46B) for respectively driving the engine. system propellers.
    公开号:FR3056555A1
    申请号:FR1659366
    申请日:2016-09-29
    公开日:2018-03-30
    发明作者:Thomas Klonowski；Ludovic Meziere；Bernard Plissonneau
    申请人:Safran Helicopter Engines SAS；
    IPC主号:
    专利说明:

    DESCRIPTION
    TECHNICAL AREA
    The present invention relates to a hybrid propulsion system intended for multirotor rotary wing aircraft, as well as to a method for manufacturing such a hybrid propulsion system.
    PRIOR STATE OF THE ART
    A hybrid propulsion system for a multirotor rotary wing aircraft is known from the state of the art, comprising:
    - an internal combustion engine, and an electric generator coupled to the internal combustion engine so that in operation, the internal combustion engine drives the electric generator,
    a rectifier connected to the electric generator for converting an alternating current delivered by the electric generator into a direct current, means for converting direct current into alternating current, and an electric network connecting the rectifier to the conversion means,
    - electric motors connected to the conversion means so that in operation, the conversion means supply the first electric motors with alternating current, and
    - propellers coupled to electric motors so that in operation, the electric motors drive the propellers.
    In particular, the conversion means comprise inverters respectively connected to the electric motors so as to supply the latter with alternating current.
    However, these propulsion systems have the disadvantage of being relatively heavy.
    STATEMENT OF THE INVENTION
    The object of the invention is in particular to provide a simple, economical and effective solution to this problem.
    To this end, it offers a hybrid propulsion system for rotary wing aircraft, comprising:
    - an internal combustion engine and an electric generator coupled to the internal combustion engine so that in operation, the internal combustion engine drives the electric generator,
    a rectifier connected to the electric generator for converting an alternating current delivered by the electric generator into a direct current, conversion means configured to convert the direct current into alternating current, and an electric network connecting the rectifier to the conversion means,
    at least a first group of at least two first electric motors connected to the conversion means so that in operation, the conversion means supply the first electric motors with alternating current, and
    - propellers coupled to the first electric motors so that in operation, the first electric motors drive the propellers.
    According to the invention, the conversion means comprise a first inverter configured to supply the first electric motors in parallel.
    The general principle of the invention thus consists in sharing the supply of several electric motors of a hybrid propulsion system of rotary wing aircraft by means of the same inverter.
    The invention thus allows a reduction in mass compared to hybrid propulsion systems of known type, on the one hand, by reducing the number of inverters, and also by reducing the number and mass of EMC filters.
    In addition, the supply of several electric motors by the same inverter makes it possible to optimize the synchronization of these electric motors. This improves the lift of the hybrid propulsion system.
    There are preferably two first electric motors powered by the first inverter.
    In certain embodiments of the invention, the propellers coupled to the first electric motors are two coaxial counter-rotating propellers.
    In a preferred embodiment of the invention, the hybrid propulsion system comprises at least one other group of at least two other electric motors, and other propellers coupled to these other electric motors, and the conversion means comprise, for the or each other group of other electric motors, another corresponding inverter configured to supply the other electric motors in parallel.
    In this case, the first electric motors and the other electric motors advantageously have an intrinsic characteristic whose variance, calculated for the motors of any one of the first group and of the other or of each other group, is less than the variance of said intrinsic characteristic calculated for all of the first electric motors and of the other electric motors.
    The intrinsic characteristic or characteristics considered are preferably electrical or electromagnetic characteristics such as stator resistances, synchronous inductances, and fluxes of rotor origin.
    Preferably, the hybrid propulsion system further comprises an energy storage unit connected to the electrical network in parallel with the electrical generator.
    The invention also relates to a multirotor rotary wing aircraft, comprising a hybrid propulsion system of the type described above.
    The invention also relates to a method for manufacturing a hybrid propulsion system of the type described above, comprising at least the steps consisting respectively in:
    - providing a plurality of electric motors, propellers, an internal combustion engine, an electric generator, a rectifier, an electric network, and a first inverter;
    - couple the electric generator to the internal combustion engine;
    - connect the rectifier to the electric generator;
    - connect the first inverter to the rectifier by means of the electrical network;
    - Select, from the plurality of electric motors, a first group of at least two first electric motors;
    - connect the first electric motors to the first inverter in parallel;
    - couple at least part of the propellers to the first electric motors.
    In the preferred embodiment of the invention, the method further comprises the steps consisting respectively in:
    - select, from the plurality of electric motors, at least one other group of at least two other electric motors;
    - make available, for the or each other group of other electric motors, another corresponding inverter;
    - connect the other electric motors of the or each other group in parallel to the other corresponding inverter.
    Preferably, the first electric motors and the other electric motors are chosen so as to have an intrinsic characteristic whose variance, calculated for the motors of any one of the first group and of the other or of each other group, is less to the variance of said intrinsic characteristic calculated for all of the first electric motors and of the other electric motors.
    BRIEF DESCRIPTION OF THE DRAWINGS
    The invention will be better understood, and other details, advantages and characteristics thereof will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which:
    - Figure 1 is a schematic top view of a multirotor rotary wing aircraft according to a preferred embodiment of the invention;
    - Figure 2 is a partial schematic view of a hybrid propulsion system fitted to the aircraft of Figure 1;
    - Figure 3 is a schematic view of part of the hybrid propulsion system of Figure 2, illustrating in particular an inverter and two electric motors belonging to this system.
    DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
    FIG. 1 illustrates a rotary wing aircraft 10, for example an octorotor aircraft, of the type comprising four pairs 12, 14, 16, 18 of counter-rotating propellers 12A, 12B, 14A, 14B, 16A, 16B, 18A, 18B.
    In general, these propellers are respectively coupled to electric motors (not visible in Figure 1) which thus ensure the rotational drive of the propellers. These electric motors are themselves supplied with electric energy by an electric generator 20 driven by an internal combustion engine 22 such as a turbomachine. The connection between the electric generator 20 and the electric motors is operated by direct current, at a relatively high voltage, in order to improve the stability of the network and the power management. For this purpose, a rectifier ensures the conversion of the alternating current delivered by the electric generator 20 into direct current, while conversion means ensure the conversion of this direct current into alternating current intended for the electric motors, as will appear more clearly in this following. The connection between the electric generator 20 and the electric DC motors is particularly advantageous because the electric generator 20 operates at a constant speed and therefore makes it possible to have a stable DC voltage after conversion.
    Preferably, an energy storage unit 26 is also provided for temporarily supplying the electric motors by supplementing or replacing the electric generator 20, in a manner known per se. The energy storage unit 26 is for example of the electrochemical type but may, as a variant, be of the electrostatic (capacitive) or mechanical type.
    The direct current connection mentioned above has in this case an additional advantage of the fact that such a connection makes it possible to connect in a simple manner the electric generator 20 and the energy storage unit 26, on the one hand, to the electric motors, on the other hand.
    As a variant, the energy storage unit 26 can be connected to the rest of the system by means of a chopper, also known as a continuous converter, making it possible in particular to ensure proper recharging of the energy storage unit 26 and also to ensure redundancy of the electric chain in the event that the energy storage unit 26 should fail.
    All of these elements form a hybrid propulsion system 30, which will now be described in more detail with reference to FIG. 2.
    The hybrid propulsion system 30 therefore comprises the internal combustion engine 22 and the electric generator 20. The latter typically comprises a rotor coupled to an output shaft 32, such as a shaft of a free or linked turbine, of the combustion engine internal 22.
    An electrical output of the electrical generator 20 is connected to an input of the rectifier 34 to convert the alternating current AC supplied by the electrical generator 20 into direct current DC.
    An output of rectifier 34 is connected in parallel, by means of an electrical network 44, to respective inputs of conversion means, namely a first inverter 36, a second inverter 38, a third inverter 40 and a fourth inverter 42, designed to convert DC direct current into AC alternating current for powering electric motors.
    More specifically, the first inverter 36 has an output connected in parallel to a first group 46 of two first electric motors 46A, 46B, which the first inverter 36 thus supplies AC alternating current.
    Similarly, the other inverters 38, 40, 42 have respective outputs which are respectively connected in parallel to other groups 48, 50, 52 each comprising two other corresponding electric motors 48A, 48B, 50A, 50B, 52A, 52B .
    The hybrid propulsion system 30 thus comprises several groups each comprising two electric motors, and is configured so that the motors of the same group are supplied with electric energy by the same corresponding inverter.
    The two electric motors 46A-52B of each group are respectively coupled to the two propellers of a corresponding pair 12-18 of counter-rotating propellers.
    Powering electric motors from the same inverter reduces the mass of the hybrid propulsion system.
    In addition, such a configuration allows good synchronization of these motors, and therefore of the propellers driven by the latter. This makes it possible to improve the lift of the hybrid propulsion system, particularly in the case of a system with counter-rotating propellers such as the system illustrated in the figures.
    Furthermore, the energy storage unit 26 is also connected in parallel to each of the inverters 36-42.
    The 46A-52B electric motors are all of the same type. However, to optimize the joint control and synchronization of the two motors of each group, the electric motors 46A-52B are distributed in the different groups 46-52 so as to have at least one intrinsic characteristic including the variance, calculated for the electric motors of any of groups 46-52, or less than the variance of said intrinsic characteristic calculated for all electric motors 46A-52B. In other words, the electric motors are grouped according to the value of the aforementioned intrinsic characteristic in order to minimize the difference in value of this characteristic within each group.
    The intrinsic characteristic or characteristics considered are preferably electrical or electromagnetic characteristics such as stator resistances, synchronous inductances, and fluxes of rotor origin.
    In the preferred embodiment of the invention, the electric motors 46A-52B are polyphase asynchronous motors. These motors can be of different types such as induction motors or variable reluctance motors.
    Preferably, the two electric motors of each group are of the multirotor mono-stator type, which makes it possible to reduce the mass and the volume of the electric motors while helping to minimize the variance of the stator resistances of the electric motors within each group. . This allows in particular to favor the equality of the respective electric currents within the two electric motors of the same group.
    FIG. 3 illustrates an example of configuration of the first inverter 36 as well as the first two electric motors 46A, 46B. The other 38-42 inverters have a similar configuration.
    As shown in FIG. 3, the first inverter 36 is a bridge inverter comprising three inverter arms 60, 62, 64 respectively delivering the three phases 66, 68, 70 of alternating current to each of the first two electric motors 46A, 46B . The first inverter 36 includes an emergency inverter arm 72 which is initially inoperative and which is intended to replace one of the three arms 60, 62, 64 in the event of its failure. The first inverter 36 further comprises conventionally a module 74 for controlling the inverter arms 60, 62, 64 and a module 76 for EMC filtering.
    The hybrid propulsion system 30 can be manufactured using a method comprising the steps of:
    - provide the electric motors 46A-52B, the propellers 12A-18B, the internal combustion engine 22, the electric generator 20, the rectifier 34, the electrical network 44, and the conversion means consisting of the first inverter 36, the second inverter 38, third inverter 40 and fourth inverter 42;
    - coupling the electric generator 20 to the internal combustion engine 22;
    - connect the rectifier 34 to the electric generator 20;
    - connect each of the inverters 36-42 to the rectifier 34 by means of the electrical network 44;
    - divide the electric motors 46A-52B into groups of two motors, so that the variance of at least one intrinsic characteristic of the electric motors calculated for the motors of any one of groups 46-52, is less than the variance of said intrinsic characteristic calculated for all 46A52B electric motors;
    - connect the electric motors of each group in parallel to a corresponding 36-42 inverter;
    - couple the propellers respectively to the electric motors 46A-52B.
    As explained above, the general principle of the invention consists in pooling the power supply of electric motors of a hybrid propulsion system of multirotor rotary wing aircraft by means of inverters.
    This general principle can be applied to various configurations of hybrid propulsion systems, without departing from the scope of the present invention.
    Thus, the number of propellers can be greater than or less than 8. It can for example be equal to four in the case of an aircraft of the quadrotor type, sometimes called quadricopter. In addition, propellers driven by electric motors of the same group may not adopt a configuration of coaxial counter-rotating propellers.
    The number of inverters can also vary, as can the type of these inverters.
    In addition, the number of electric motors powered by the same inverter can be more than two. It is however desirable that this number remains relatively low to maintain sufficient redundancy of the propulsive members, such redundancy being desirable to guarantee the safety of the aircraft.
    In its most general aspect, the hybrid propulsion system according to the invention therefore comprises at least one inverter and at least two electric motors powered by this inverter.
    ίο
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Hybrid propulsion system (30) for a multirotor rotary wing aircraft (10), comprising:
    - an internal combustion engine (22) and an electric generator (20) coupled to the internal combustion engine so that in operation, the internal combustion engine drives the electric generator,
    - a rectifier (34) connected to the electric generator for converting an alternating current delivered by the electric generator into a direct current, conversion means configured to convert the direct current into alternating current, and an electric network (44) connecting the rectifier to means of conversion,
    - at least a first group (46) of at least two first electric motors (46A, 46B) connected to the conversion means so that in operation, the conversion means supply the first electric motors with alternating current,
    - propellers (12A, 12B) coupled to the first electric motors so that in operation, the first electric motors drive the propellers, characterized in that the conversion means comprise a first inverter (36) configured to supply the first in parallel electric motors.
    [2" id="c-fr-0002]
    2. A hybrid propulsion system according to claim 1, in which the first two electric motors (46A, 46B) supplied by the first inverter (36) are two.
    [3" id="c-fr-0003]
    3. Hybrid propulsion system according to claim 2, in which the propellers (12A, 12B) coupled to the first electric motors (46A, 46B) are two counter-rotating coaxial propellers.
    [4" id="c-fr-0004]
    4. Hybrid propulsion system according to any one of claims 1 to 3, comprising at least one other group (48, 50, 52) of at least two other electric motors (48A, 48B, 50A, 50B, 52A, 52B) , and other propellers (14A, 14B,
    16A, 16B, 18A, 18B) coupled to these other electric motors, and in which the conversion means comprise, for the or each other group of other electric motors, another corresponding inverter (38, 40, 42) configured to supply other electric motors in parallel.
    [5" id="c-fr-0005]
    5. Hybrid propulsion system according to claim 4, in which the first electric motors (46A, 46B) and the other electric motors (48A, 48B, 50A, 50B, 52A, 52B) have an intrinsic characteristic whose variance, calculated for the motors of any one of the first group (46) and of the other or each other group (48, 50, 52), is less than the variance of said intrinsic characteristic calculated for the set of first electric motors and other electric motors.
    [6" id="c-fr-0006]
    6. Hybrid propulsion system according to any one of claims 1 to 5, further comprising an energy storage unit (26) connected to the electric network (44) in parallel with the electric generator (20).
    [7" id="c-fr-0007]
    7. Multi-rotor rotary wing aircraft (10), comprising a hybrid propulsion system (30) according to any one of claims 1 to 6.
    [8" id="c-fr-0008]
    8. A method of manufacturing a hybrid propulsion system (30) according to any one of claims 1 to 6, comprising at least the steps consisting respectively in:
    - providing a plurality of electric motors, propellers, an internal combustion engine (22), an electric generator (20), a rectifier (34), an electrical network (44), and a first inverter (36);
    - couple the electric generator (20) to the internal combustion engine (22);
    - connect the rectifier (34) to the electric generator (20);
    - connecting the first inverter (36) to the rectifier (34) by means of the electrical network (44);
    - selecting, from the plurality of electric motors, a first group (46) of at least two first electric motors (46A, 46B);
    - connecting in parallel the first electric motors (46A, 46B) to the first inverter (36);
    - couple at least part of the propellers (12A, 12B) to the first electric motors (46A, 46B).
    [9" id="c-fr-0009]
    9. Method according to claim 8 for manufacturing a hybrid propulsion system (30) according to claim 5, further comprising the steps consisting respectively in:
    - selecting, from the plurality of electric motors, at least one other group (48, 50, 52) of at least two other electric motors (48A, 48B, 50A, 50B, 52A, 52B);
    - make available, for the or each other group of other electric motors, another corresponding inverter (38, 40, 42);
    - connect the other electric motors of the or each other group in parallel to the other corresponding inverter.
    [10" id="c-fr-0010]
    10. The method as claimed in claim 9, in which the first electric motors (46A, 46B) and the other electric motors (48A, 48B, 50A, 50B, 52A, 52B) are chosen so as to have an intrinsic characteristic including the variance, calculated for the motors of any one of the first group (46) and of the other or of each other group (48, 50, 52), is less than the variance of said intrinsic characteristic calculated for all of the first motors electric and other electric motors.
    1/3
    S.60959
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    法律状态:
    2017-05-04| PLFP| Fee payment|Year of fee payment: 2 |
    2018-03-30| PLSC| Search report ready|Effective date: 20180330 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 3 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1659366|2016-09-29|
    FR1659366A|FR3056555B1|2016-09-29|2016-09-29|HYBRID PROPULSIVE SYSTEM FOR MULTIROTOR ROTARY FLYWELL AIRCRAFT COMPRISING IMPROVED DC / AC CONVERSION MEANS|FR1659366A| FR3056555B1|2016-09-29|2016-09-29|HYBRID PROPULSIVE SYSTEM FOR MULTIROTOR ROTARY FLYWELL AIRCRAFT COMPRISING IMPROVED DC / AC CONVERSION MEANS|
    EP17783943.8A| EP3519294B1|2016-09-29|2017-09-27|Hybrid propulsion system for multi-rotor rotary-wing aircraft, comprising improved dc/ac conversion means|
    PCT/FR2017/052595| WO2018060591A1|2016-09-29|2017-09-27|Hybrid propulsion system for multi-rotor rotary-wing aircraft, comprising improved dc/ac conversion means|
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    JP2019517071A| JP2019534821A|2016-09-29|2017-09-27|Hybrid propulsion system for a multi-rotor rotorcraft with improved DC / AC conversion means|
    RU2019112618A| RU2745465C2|2016-09-29|2017-09-27|Hybrid power plant for multipropeller rotary-wing aircraft containing improved dc/ac converter|
    CN201780059691.4A| CN109789923A|2016-09-29|2017-09-27|The hybrid propulsion system including improved DC/AC conversion equipment for more rotor rotary-wing aircrafts|
    US16/336,537| US20200115062A1|2016-09-29|2017-09-27|Hybrid propulsion system for multi-rotor rotary wing aircraft, comprising improved dc/ac conversion means|
    KR1020197011625A| KR20190055189A|2016-09-29|2017-09-27|A hybrid propulsion system for multi-rotor rotary wing aircraft including improved DC / AC conversion means|
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