• 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:
    The invention relates to a method for managing an electric motor (6) intended to drive in rotation an aircraft wheel (4) (1), the method comprising the step of short-circuiting the phases of the electric motor (6). ) when the aircraft (1) is in a period of deactivation of the engine (6) during which it is planned not to use the electric motor (6).
    公开号:FR3022887A1
    申请号:FR1455930
    申请日:2014-06-25
    公开日:2016-01-01
    发明作者:Sylvain Jaber；Raffi Cekic
    申请人:Messier Bugatti Dowty SA；
    IPC主号:
    专利说明:

    [0001] The invention relates to a method for managing an electric motor for rotating an aircraft wheel. This method protects the electric motor against the electromotive force occurring when the engine is off and the aircraft moves on the ground at high speed. BACKGROUND OF THE INVENTION In order to allow fuel savings and to reduce the noise and pollution generated by the operation of ground reactors, it has been proposed to ensure the movement of an aircraft over an airport area without the assistance of the engines, by motorizing certain wheels of the aircraft. The motorization of the wheels of the aircraft generally uses, for each motorized wheel of the aircraft, an electric motor for driving the wheel in rotation. When the electric motor is not used to drive the wheel of the aircraft and the aircraft moves on the ground, the rotor of the electric motor is rotated by the rotation of the wheel, which generates a certain electromotive force between the phases of the electric motor. When the ground speed of the aircraft is high, especially during the take-off and landing phases, this electromotive force increases significantly and may damage the electric motor. A disengaging device is thus used to mechanically disconnect the electric motor from the wheel during these phases. This type of device is generally relatively heavy and complex because of the high levels of torque to be transmitted and the required reliability. OBJECT OF THE INVENTION The object of the invention is to protect against the electromotive force mentioned earlier an electric motor intended to drive in rotation an aircraft wheel, while reducing the increase in the mass of the aircraft resulting from the implementation of this protection.
    [0002] SUMMARY OF THE INVENTION With a view to achieving this object, there is provided a method of managing an electric motor for rotating an aircraft wheel, the method comprising the step of short-circuiting the engine phases. electrical when the aircraft is in a period of deactivation of the engine during which it is planned not to use the electric motor. By short-circuiting the phases of the electric motor when the aircraft is in the deactivation period, it prevents the formation of an electromotive force which, when the ground speed of the aircraft is important, is likely to damage the aircraft. electric motor. The short-circuiting of the phases of the electric motor can be done by means of switches (electrical, electromechanical) whose use generates an increase in the mass of the aircraft significantly lower than that resulting from the use of traditional mechanical disengaging devices .
    [0003] BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood in the light of the description which follows with reference to the figures of the appended drawings, in which: FIG. 1 represents an aircraft as well as a detailed view of the aircraft showing a main undercarriage; carrying two wheels adapted to be rotated by electric motors on which the management method of the invention is implemented; FIG. 2 represents an electric motor such as the one mentioned earlier, an inverter supplying this motor, and a switching element designed to short-circuit the phases of the motor; - Figure 3 shows the electric motor, the inverter and the switching member while the motor phases are not short-circuited; - Figure 4 shows the electric motor, the inverter and the switching member while the motor phases are short-circuited; FIG. 5 is a graph illustrating a short-circuit current of the electric motor as a function of the speed of rotation of the wheel; FIG. 6 is a graph illustrating a parasitic torque of the electric motor as a function of the rotational speed of the wheel.
    [0004] DETAILED DESCRIPTION OF THE INVENTION Referring to Figure 1, the invention is here implemented on an aircraft 1 having an undercarriage 2 and two landing gear 3a, 3b. The invention is described with reference only to the main undercarriage 3a, the entire description being applicable to the other main undercarriage 3b. The main undercarriage 3a is provided with two wheels 4. Rotational drive means 5 of the wheels 4 are installed on the main landing gear 3a. These drive means 5, shown schematically in Figure 1, comprise for each wheel 4 a drive actuator comprising an electric motor 6 for driving the wheel 4 in rotation. Electric motors 6 are three-phase synchronous electric motors with permanent magnets. The electric motors 6 are driven by a control computer 7 associated with the two wheels 4 of the main undercarriage 3a. The control computer 7 35 contains in particular, for each electric motor 6, an inverter 8 connected to the electric motor 6. With reference to FIG. 2, each inverter 8 is intended to deliver to the associated electric motor 6 a supply voltage for the electric motor 6 rotates the wheel 4 at a controlled rotational speed and in a controlled direction of rotation. The inverter 8 conventionally comprises three switching cells 9, each connected to a phase Ph of the electric motor 6, and whose offset controls make it possible to form a three-phase system of currents and voltages. Each switching cell 9 comprises two electric switches 11 each consisting of a transistor 12 and a diode mounted parallel to the transistor and not visible in the figures.
    [0005] The method for managing an electric motor of the invention aims at protecting the electric motor 6 during periods of deactivation of the electric motor 6 during which the electric motor 6 is not to be used. These deactivation periods correspond here to the Flight Phases including take-off and landing. The information relating to the flight phase in which the aircraft 1 is transmitted is transmitted at all times to the control computer 7. During these periods of deactivation, for example during takeoff where the speed of the aircraft is approximately 10 times higher than the speed during taxing, the ground speed of the aircraft 1 is important, and therefore the electromotive force generated by the rotor of the electric motor 6 driven by the rotation of the wheel 4 is potentially very high. The protection of the electric motor 6 consists of short-circuiting the phases Ph of the electric motor 6 during these periods of deactivation of the motor, so as to cancel this electromotive force.
    [0006] Two external switching members 14 are connected for this purpose between the control computer 7 and the electric motors 6 of the drive means 5 of the wheels 4 of the main gear 3a. Each switching member 14 is connected at its input to the output of one of the inverters 8, and at its output to the three phases Ph of the electric motor 6 powered by this inverter 8. Each switching member 14 comprises three electromechanical switches 16 connected to the associated inverter 8 and the three phases Ph of the electric motor 6, as illustrated in FIGS. 3 and 4. Each electromechanical switch 16 comprises an electromagnet and a contact. The electromagnets of the electromechanical switches 16 are controlled by the control computer 7 to selectively and simultaneously actuate the contacts by bringing them into a first state in which each contact connects a switching cell 9 of the inverter 8 to a phase Ph of the motor 6, or in a second state in which the three phases Ph of the electric motor 6 are short-circuited. FIGS. 3 and 4 respectively show the state of the electromechanical switches 16 when the aircraft 1 is in an activation period during which the electric motor 6 is expected to be used, and in a deactivation period during which is not to use the electric motor 6. During the activation period, the electromechanical switches 16 are controlled by the control computer 7 so as to connect the switching cells 9 of the inverter 8 to the three phases Ph of the electric motor 6, which can be controlled normally. During the deactivation period, the three phases Ph of the electric motor 6 are short-circuited and no electromotive force is generated within the electric motor 6 by the effect of the rotation of the wheel 4. FIG. 5 shows that the short-circuit current Icc appearing in a motor such as the electric motor 6 is almost constant from a small value of rotation speed Vo of the wheel 4. The value of this current of Short circuit Icc is therefore relatively easy to predict, which makes it possible to effectively anticipate the thermal impact of this current-circuit current Icc on the electric motor 6 and the possible thermal protections to be implemented during the design of the Electric motor 6. It is also noted, with reference to FIG. 6, that the parasitic torque Cp associated with the short-circuit current Ic is maximum at low speed and decreases very rapidly. During take-off, this spurious torque Cp adds a low rolling resistance of the aircraft 1 at low speed which decreases very rapidly and does not disturb the take-off. On landing, the speed of rotation of the wheel 4 is very high when it touches the ground, the parasitic torque is very low, and the rolling resistance does not disturb the landing. The invention is not limited to the particular embodiment that has just been described, but, on the contrary, covers any variant within the scope of the invention as defined by the claims. Although a particular and simplified architecture of the wheel rotation drive system has been used here to describe the invention, the method of the invention is of course applicable to any aircraft with at least one braked wheel associated with it. an electric motor driving in rotation of the wheel. It is also possible, in order to short-circuit the phases, to use instead of the electromechanical switches one or more electrical switches of the inverter 7 supplying the phases of the electric motor 6 The suppression of the electromechanical contactors 14 allows a gain of mass and increased reliability of the system. Although it has been indicated here that the electric motor is a three-phase motor, the invention applies to motors with a different number of phases. The invention applies in particular to a single-phase motor, the "short-circuiting phases" in a single-phase motor of connecting together the two ends of the motor winding. Although it has been indicated that the periods of deactivation of the engine are periods including take-off and landing, these periods of deactivation can of course be defined differently. A deactivation period may thus include a period during which a speed of the aircraft is greater than a predetermined speed threshold. It is then expected to transmit to the control computer measures or estimates of the speed of the aircraft, rather than the information relating to the flight phase in which the aircraft is located. Note that in case of unavailability of the taxing function, resulting for example from a failure of an aircraft system or a loss of power, such as the rest position of the engine management method electric corresponds to a short-circuited state, the impact on the behavior of the aircraft is negligible.
    权利要求:
    Claims (5)
    [0001]
    REVENDICATIONS1. A method of managing an electric motor (6) for rotating an aircraft wheel (4) (1), the method comprising the step of shorting phases (Ph) of the electric motor (6) when the aircraft (1) is in a period of deactivation of the engine (6) during which the electric motor (6) is not to be used.
    [0002]
    2. A method of managing an electric motor according to claim 1, wherein the short-circuiting of the phases (Ph) of the electric motor (6) is achieved by at least one electrical switch of an inverter (8) delivering a voltage. power supply to the electric motor (6).
    [0003]
    3. A method of managing an electric motor according to claim 1, wherein the short-circuiting of the phases (Ph) of the electric motor (6) is achieved by at least one electromechanical switch (16) connected to the phases of the electric motor.
    [0004]
    4. Management method according to one of the preceding claims, wherein the deactivation period comprises a period during which a speed of the aircraft (1) is greater than a predetermined speed threshold.
    [0005]
    5. Management method according to one of the preceding claims, wherein the deactivation period comprises a takeoff phase and / or a landing phase of the aircraft (1).
    类似技术:
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    同族专利:
    公开号 | 公开日
    EP2960153A1|2015-12-30|
    US9630707B2|2017-04-25|
    CN105270609A|2016-01-27|
    US20150375855A1|2015-12-31|
    CN105270609B|2018-11-13|
    FR3022887B1|2016-10-21|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1911146A1|2005-07-27|2008-04-16|Oerlikon Textile GmbH & Co. KG|Electric motor|
    EP2733843A1|2011-07-12|2014-05-21|Toyota Jidosha Kabushiki Kaisha|Vehicle and vehicle control method|
    US20140156130A1|2011-10-26|2014-06-05|Mitsubishi Electric Corporation|Control apparatus of electrically-driven vehicle|
    US3769710A|1969-04-01|1973-11-06|R Reister|Electronic celestial navigation means|
    IL199009A|2009-05-27|2013-11-28|Israel Aerospace Ind Ltd|Air vehicle|
    FR2954235B1|2009-12-17|2012-03-16|Michelin Soc Tech|ELECTRIC MOTORIZATION SYSTEM OF A WHEEL|
    IL204509A|2010-03-15|2015-01-29|Israel Aerospace Ind Ltd|System for landing a vtol aircraft|CN103516281B|2013-10-25|2015-02-11|南车株洲电力机车研究所有限公司|Method, device and system for controlling PMSMto put into operation again at belt speed|
    GB2538081B|2015-05-06|2017-08-16|Rolls Royce Plc|Apparatus and methods for controlling velocity of aircraft during landing roll-out and/or taxiing|
    FR3057849A1|2016-10-24|2018-04-27|Safran Landing Systems|METHOD FOR MAINTAINING AN IMMOBILE AIRCRAFT DURING GROUND DISPLACEMENT PHASES|
    FR3058821B1|2016-11-14|2019-01-25|Safran Landing Systems|METHOD FOR CONTROLLING AN ELECTRIC TAXIAGE SYSTEM|
    CN106452200B|2016-11-22|2019-02-19|广东美的暖通设备有限公司|Typhoon power protecting circuit, outdoor unit and the air conditioner of outdoor fan in air conditioner|
    法律状态:
    2015-06-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-01| PLSC| Search report ready|Effective date: 20160101 |
    2016-06-27| PLFP| Fee payment|Year of fee payment: 3 |
    2017-06-21| PLFP| Fee payment|Year of fee payment: 4 |
    2017-06-23| CD| Change of name or company name|Owner name: MESSIER-BUGATTI-DOWTY, FR Effective date: 20170518 |
    2018-06-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1455930A|FR3022887B1|2014-06-25|2014-06-25|METHOD FOR MANAGING AN ELECTRIC MOTOR|FR1455930A| FR3022887B1|2014-06-25|2014-06-25|METHOD FOR MANAGING AN ELECTRIC MOTOR|
    EP15173389.6A| EP2960153A1|2014-06-25|2015-06-23|Method for managing an electric motor|
    US14/746,953| US9630707B2|2014-06-25|2015-06-23|Method for managing an electric motor|
    CN201510358700.2A| CN105270609B|2014-06-25|2015-06-25|Method for managing electric notor|
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