• 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 an electrohydraulic actuator for the landing gear of an aircraft, in particular an aircraft, with at least one consumer coupled to a landing gear landing gear leg, with or without at least one landing gear an electric motor pump (1), at least one accumulator (2), at least one hydraulic block (3) having at least one integrated valve, with or without an engine controller and with at least one filter (5).
    公开号:FR3066999A1
    申请号:FR1854899
    申请日:2018-06-06
    公开日:2018-12-07
    发明作者:Reinhold Kleinhans；Martin Brusecke
    申请人:Liebherr Aerospace Lindenberg GmbH；
    IPC主号:
    专利说明:

    The invention relates to an electrohydraulic actuator for the landing gear of an aircraft, in particular of an aircraft, with at least one consumer coupled to a landing gear leg of the landing gear, with or without at least one electric motor pump, at least one accumulator, at least one hydraulic unit having at least one integrated valve, with or without an engine controller and with at least one filter.
    Electrohydraulic actuators for aircraft landing gear are known from the prior art, which are supplied with energy by central hydraulic systems, the actuators or the corresponding landing gear consumers being slaved via valves and / or servo valves forming part of the landing gear system.
    In this, compact systems or power packs (“Power Pack”) with pumps with electric motor, accumulators, filters and / or hydraulic blocks with integrated valves can be mounted as modules assembled in the landing gear span.
    Such known devices of the state of the art are disadvantageous insofar as instructions or aspects of assembly and maintenance concerning the actuators are not or are not sufficiently well filled and where possibilities of relative savings the costs and the weight of the actuators are not exploited.
    Compared to this situation, the object of the invention is to provide an electrohydraulic actuator which is lighter, simpler to assemble and easier to maintain than is the case for actuators known to the state of the art.
    The object of the invention is achieved according to the invention by an electro-hydraulic actuator for the landing gear of an aircraft, in particular of an aircraft. The electrohydraulic actuator comprises at least one consumer coupled to a landing gear leg of the landing gear, none or at least one pump with an electric motor, at least one accumulator, at least one hydraulic block having at least one integrated valve , none or an engine controller and at least one filter.
    Regarding the consumer, it can be for example a hydraulic cylinder or a cylinder / piston device. The electric motor pump can be an integrated motor pump by which electrical energy can be transformed into hydraulic energy.
    The hydraulic unit can be constitutive here of any hydraulic device which is suitable for regulating / controlling the hydraulic flow between the pump with electric motor and the consumer.
    The electric motor pump can be a device in which an electric motor is combined with a hydraulic pump, in particular in a common casing.
    According to the invention, it is intended that, in addition to the consumer, at least one other of the components listed is coupled to the landing gear for common actuation. Landing gear actuation may include retracting and exiting and / or steering the landing gear or parts thereof. Said component or a plurality of components of the electrohydraulic actuator can be arranged in different zones or near different components or in the same zone or near the same component of the landing gear leg and can in particular be integrated in or with it.
    By this, it is possible to arrange the hydraulic supply or the electric motor pump and / or other components of the actuator as close as possible to the consumer, in order to make possible short hydraulic lines optimally. and thus the lightest possible. The term actuator is to be understood here as broadly as possible and may include the components provided according to the invention as well as other components.
    By the optimal arrangement made possible by the invention, components of the electrohydraulic actuator to the entire landing gear, the mounting or arrangement of the hydraulic lines can be simplified and made optimal as much as possible, thanks to what the integration of the hydraulic lines in the plane is simplified.
    Overall, said component or at least one component of the electrohydraulic actuator can be chosen, as regards its distribution, its arrangement and / or its location, so that good access for mounting and component maintenance is given.
    In order to make the shortest possible hydraulic lines and in order to make the problem of the paths of the lines as moderate as possible, it is here possible, according to the invention, on the one hand to have the decentralized hydraulic supply or the electric motor pump as close as possible to the consumer (s)) and on the other hand to make the complexity of the paths of the hydraulic lines, for example on the movement angle of about 100 ° during the retraction and the exit landing gear, as small as possible.
    At the same time, it is possible to improve or simplify the access necessary for the original installation of the device and also for the maintenance of already installed components of the device, by an appropriate distribution of the components of the electrohydraulic actuator. .
    According to a preferred embodiment, it is conceivable that all of the stated components are coupled to the landing gear, in particular to the landing gear leg of the landing gear, for common actuation, and / or that the electric motor pump includes a bidirectional hydraulic pump.
    The components can be arranged in a distributed manner over different zones, in particular on zones spaced apart from each other, of the landing gear or of the landing gear leg.
    According to another preferred embodiment, it is conceivable that said at least one consumer is, each, at least one control actuator, a retraction actuator, an emergency actuator, a door actuator, a train lock retracted, a train lock out and / or a locking actuator.
    The retraction actuator can be adapted to retract the landing gear in the span of the landing gear. The emergency actuator may be an actuator which is designed to bring out the landing gear or the landing gear leg, in particular in free fall, in an emergency.
    The door actuator can be designed to open and / or close the door of the landing gear bay.
    According to another preferred embodiment, it is conceivable that the hydraulic actuator comprises exactly two hydraulic lines arranged along the landing gear leg. These exactly two hydraulic lines can connect, for example, a consumer located at the bottom or at the bottom of the landing gear leg to a hydraulic supply arranged above. The lower zone of the landing gear leg corresponds in this case to the zone in which at least one wheel of the landing gear is arranged.
    According to another preferred embodiment, it is conceivable that the accumulator and / or the hydraulic block and the filter with or without motor controller and / or the pump with electric motor are integrated inside a landing gear shock absorber of the landing gear.
    According to another preferred embodiment, it is conceivable that the accumulator and / or the hydraulic block and / or the filter and / or the motor controller and / or the electric motor pump are integrated in the area of the landing gear bolt axis.
    According to another preferred embodiment, it can be provided that the components set out are arranged inside or outside of a V-shaped area of a landing gear housing of the landing gear. . The components can also be arranged inside or outside the area of the steering actuator.
    It is also also conceivable to have the components listed inside or outside the area of at least one consumer different from the control actuator. The various possibilities stated for the integration or arrangement of the components makes it possible to place them with the least possible space and in a protected manner, inside or on the structure of the landing gear.
    It can in particular be provided that different components are provided in different areas of the landing gear and that in this way, the advantages supposed to be obtained according to the invention can be obtained.
    The invention further relates to a landing gear for an aircraft, in particular for an aircraft, the landing gear comprising at least one electrohydraulic actuator that is to say according to the invention and / or the one of its embodiments set out above.
    Other details and advantages of the invention appear from the embodiments shown by way of examples in the figures and explained. In these figures, Figures 1a, 1b show a first embodiment of an electrohydraulic actuator according to the invention with a circuit diagram, Figures 2a, 2b show a second embodiment of an electrohydraulic actuator according to the invention with a circuit diagram.
    It is known that components of the electrohydraulic actuator which can be reached without auxiliary means by an operator or by a maintenance person, are easier to install and / or maintain. More particularly, components which are arranged in the area of the landing gear leg are easier to assemble and / or maintain.
    In the case of an electrohydraulic actuator designed according to the invention, the different components or at least one of these components can be provided in different zones, for example in a lower zone of the landing gear leg and can thus be more easily accessible for operating personnel or for maintenance personnel.
    The electrohydraulic actuator according to the invention makes it possible to supply decentralized direct hydraulic power to a consumer of the landing gear. Thanks to this, short hydraulic lines can be used in the area of the landing gear and its actuators or consumers. The short hydraulic lines make possible better laying of the lines whereby savings in weight and manufacturing costs are possible. By easier access to components, installation and maintenance options and maintenance costs can be minimized.
    It is known from the state of the art that individual components are combined in one unit. This includes for example a filter 5 which can be plugged, if necessary, and which, in this case, must be cleaned or replaced. A suitable power pack further includes a tank or accumulator 2 which must also be maintained. The power pack may further include a prestressed pressure tank which must also be accessible for maintenance. As regards the accumulator 2 according to the invention, it is a hydraulic accumulator filled, for example, with nitrogen.
    The power pack may further include a valve which must also be accessible for maintenance work. The valve may in particular be a safety valve 10 for securing the pump.
    According to the invention, it can be avoided, advantageously, to integrate into the plane or in the area of the landing gear, with a lot of effort, long or heavy hydraulic lines. In addition, the device according to the invention makes possible a good and simple characteristic of installation and maintenance of the actuator or of its components. The availability of the actuator can be increased by providing redundant components such as a tank or the accumulator 2, for example the hydraulic block 3 or individual valve units, the filter unit or the filter 5, the motor controller 4 and / or the pump set or the electric motor pump 1.
    According to the invention, it is also possible to reduce the amount of oil that the system needs and the accumulator 2 or the accumulators 2 can be designed in a smaller and lighter manner.
    Figures 1a and 1b show an embodiment according to which the electric motor can drive the hydraulic pump which is in particular a bidirectional pump, the electric motor and the pump can form the electric motor pump group. The engine controller 4 which controls the electric motor can be placed not on the landing gear but at a distance from it. The different functions such as steering the aircraft via the steering actuator (SA), retraction and exit of the landing gear via a retraction actuator (RA) and / or actuation of the locking / unlocking actuator (uplock actuator UA) can be controlled by valves. In an emergency, the landing gear is extended (free fall) via an alternative EHA actuator or a replacement electrohydraulic actuator.
    In this embodiment, individual components such as the motor pump or electric motor pump 1, the tank, the valve block or the hydraulic block 3 are arranged on the landing gear leg, in close proximity to consumers, the steering cylinder can be arranged in the immediate vicinity of the components.
    Thus, one obtains in a non-complicated manner a fitting of pipes according to which only two hydraulic lines are placed on the leg of the rotary landing gear (angle of rotation about 100 °).
    Figures 2a and 2b show an embodiment where the electric motor can drive the hydraulic pump which is in particular a bidirectional pump, the electric motor and the pump can form the electric pump group. The engine controller 4 which controls the electric motor can be placed not on the landing gear but at a distance from it. The different functions such as steering the aircraft via the steering actuator (SA), retracting and exiting the landing gear via a retracting actuator (RA), actuating the locking actuator / unlocking (UA), actuating a door via a door actuator (door actuator DA), actuating a retracted train lock and / or a pump lock with an electric motor accumulator hydraulic unit filter or filter power pack hydraulic pump (approx. 14,000 rpm) compensator (approx. 10 bar) switching valve pump pressure limiting valve selector valve free fall deactivation valve control (rack + pinion) retraction actuator unlocking actuator selector valve door - landing gear locking actuator door closed door actuator - self-locking in retracted position "press to unlock the tra in landing, to retract "replacement electrohydraulic actuator" pull to retract the landing gear "" push to unlock the landing gear, retracted "" push to unlock the door "" pull to open the door "" pull to unlock the landing gear, to retract »door actuator door lock closed door closed can be controlled by valves. In an emergency, the landing gear is extended (free made) via an alternative function of the retracted train lock.
    In this embodiment, individual components such as the motor pump or electric motor pump 1, the tank, the valve block or the hydraulic block 3 are arranged on the landing gear leg, in the immediate vicinity of consumers, the steering cylinder can be arranged in the immediate vicinity of the components.
    List of reference numbers:
    100
    101
    102
    103
    104
    105
    106
    107
    108
    109
    110
    111
    112
    AT
    WASH
    B
    VS
    D
    E
    F
    DA
    D-uplock
    G-uplock 8landing gear lock retracted RA retraction actuator HER steering actuator UA locking / unlocking actuator
    权利要求:
    Claims (6)
    [1" id="c-fr-0001]
    1. Electrohydraulic actuator for the landing gear of an aircraft, in particular of an airplane, with at least one consumer coupled to a landing gear leg of the landing gear, with or without at least one motor pump electric (1), at least one
    5 accumulator (2), at least one hydraulic block (3) having at least one integrated valve, with or without an engine controller and with at least one filter (5), characterized in that, in addition to the consumer, at least one another of the components listed is coupled to the landing gear for joint actuation.
    [2" id="c-fr-0002]
    2. Electrohydraulic actuator according to claim 1, characterized in that all of the stated components are coupled to the landing gear, in particular to the landing gear leg of the landing gear, for joint actuation, and / or by that the electric motor pump (1) comprises a bidirectional hydraulic pump.
    [3" id="c-fr-0003]
    3. Electrohydraulic actuator according to claim 1 or 2, characterized in that said at least one consumer is, each, at least one control actuator, one
    15 retraction actuator, an emergency actuator, a door actuator DA), a retracted train lock, an extended train lock and / or a locking actuator (UA).
    [4" id="c-fr-0004]
    4. Electrohydraulic actuator according to one of the preceding claims, characterized in that it comprises exactly two hydraulic lines arranged along the landing gear leg.
    5. Electrohydraulic actuator according to one of the preceding claims, characterized in that the accumulator (2) and / or the hydraulic block (3) and the filter (5) with or without motor controller and / or the pump electric motor (1) are integrated inside a landing gear shock absorber of the landing gear.
    6. Electrohydraulic actuator according to one of the preceding claims, characterized in that the accumulator (2) and / or the hydraulic block (3) and / or the filter (5) and / or the engine controller and / or the electric motor pump (1) are integrated in the area of the landing gear bolt axis.
    7. Electrohydraulic actuator according to one of the preceding claims, characterized in that the accumulator (2) and / or the hydraulic block (3) and / or the filter (5) and / or the controller
    30 motor and / or the electric motor pump (1) are integrated inside or outside of a V-shaped area of a landing gear housing of the landing gear.
    8. Electrohydraulic actuator according to claim 3, characterized in that the accumulator (2) and / or the hydraulic block (3) and / or the filter (5) and / or a motor controller and / or the motor pump electric (1) are integrated inside or outside the area of the steering actuator.
    [5" id="c-fr-0005]
    5 9. Electrohydraulic actuator according to claim 3, characterized in that the accumulator (2) and / or the hydraulic block (3) and / or the filter (5) and / or a motor controller and / or the pump electric motor (1) are integrated inside or outside the area of at least one consumer different from the control actuator.
    [6" id="c-fr-0006]
    10. Landing gear for an aircraft, in particular for an airplane, with at least one electro-hydraulic actuator according to one of claims 1 to 9.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3066999A1|2018-12-07|ELECTRO-HYDRAULIC ACTUATOR FOR A PIVOTING LANDING GEAR OF AN AIRCRAFT
    CA2382809C|2008-08-12|Hydraulic actuating system with electric control
    US6227485B1|2001-05-08|Opening device common to two adjacent aircraft engine nacelle covers
    US6023134A|2000-02-08|Power conversion system for bi-directional conversion between hydraulic power and electrical power
    JP5574375B2|2014-08-20|Energy regeneration control circuit and work machine
    JP4380643B2|2009-12-09|Hydraulic control device for work machine
    JP2009133479A|2009-06-18|Hydraulic drive system
    EP0838396A1|1998-04-29|Power converting system for bidirectional conversion between hydraulic and electrical energy
    FR2760047A1|1998-08-28|TURBOJET DRIVE INVERTER WITH DOORS ASSOCIATED WITH A CONTROL SYNCHRONIZATION DEVICE
    EP1342645A1|2003-09-10|Hydraulic steering system
    FR2488943A1|1982-02-26|INTEGRATED HYDRAULIC CONTROL CIRCUIT
    JP2004245023A|2004-09-02|Hydraulic system for heavily equipped optional device
    CA2086482A1|1993-07-08|Schock absorber for aircraft landing gear
    FR2985499A1|2013-07-12|ELECTRIC CURRENT HAVING A FREE GAME MECHANISM FOR REMOVING ANTAGONIST FORCES
    FR2951330A1|2011-04-15|STEERING NETWORK FOR SINGLE OR MULTIMETER ACTUATORS, ESPECIALLY ADAPTED TO AERONAUTICAL APPLICATIONS SUCH AS THE POWER SUPPLY OF HOUSING HOUSING MOTORS
    EP2561209A1|2013-02-27|Hydraulic control system for a thrust reversal device
    EP1805423A1|2007-07-11|A non-symmetrical seal plate and valve housing
    US7810755B2|2010-10-12|Hydraulic distributor for airplane landing gear
    CN104696181A|2015-06-10|Pump for closed-circuit configuration
    EP0665381B1|1998-09-02|System for operating hydraulically actuated valves
    AU721674B2|2000-07-13|Mini-excavator with improved valve arrangement
    FR2940787A1|2010-07-09|MORE ELECTRIC FLIGHT CONTROL SYSTEM ABOVE AN AIRCRAFT
    US20010015127A1|2001-08-23|Arrangement for hydraulic actuation of a movable component on vehicles
    FR3061133A1|2018-06-29|ACTUATOR IN AN AIRCRAFT LANDING GEAR SYSTEM
    FR2634806A1|1990-02-02|
    同族专利:
    公开号 | 公开日
    DE102017112451A1|2018-12-06|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP3795468A1|2019-09-20|2021-03-24|Goodrich Corporation|Electric nose landing gear architecture|JP6283195B2|2012-12-04|2018-02-21|住友精密工業株式会社|Electric hydraulic actuator system for lifting and lowering legs|
    JP6170755B2|2013-06-18|2017-07-26|住友精密工業株式会社|Electric hydraulic actuator|DE102018127830A1|2018-11-07|2020-05-07|Liebherr-Aerospace Lindenberg Gmbh|Electro-hydrostatic actuation system|
    GB2586639A|2019-08-30|2021-03-03|Airbus Operations Ltd|Hydraulic actuation system for an aircraft|
    法律状态:
    2020-06-20| PLFP| Fee payment|Year of fee payment: 3 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017112451.9A|DE102017112451A1|2017-06-06|2017-06-06|Electrohydraulic actuator for a swiveling chassis of an aircraft|
    DE102017112451.9|2017-06-06|
    [返回顶部]