• 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 of maneuvering an aircraft undercarriage (1) movable between a retracted position and an extended position, the method comprising: - the use of an actuating actuator (10) of electromechanical type rotary hitched a portion of the undercarriage (4a) for raising the extended position to the retracted position; - disengaging the operating actuator during a descent of the undercarriage from the retracted position to the deployed position and the use of a hydraulic linear damper (20) coupled to a portion of the undercarriage (4a) for regulating a descent speed and / or damping an arrival of the undercarriage in the deployed position; - the neutralization of the shock absorber during lifting.
    公开号:FR3073494A1
    申请号:FR1760763
    申请日:2017-11-15
    公开日:2019-05-17
    发明作者:Florent FORTIER；Sebastien Dubois
    申请人:Safran Landing Systems SAS；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION
    Aircraft undercarriages mounted on the aircraft are known between a deployed position. In general, associated with an actuator
    The undercarriage of one on the descent, the actuator in the retracted position and one each undercarriage is operated to move the other of the positions. When maneuvering is mainly used speed regulate the of for descent,
    1'atterrisseur descendant of himself towards the position deployed under The action of gravity and of the efforts aerodynamic. The position deployed East in general defined by 1'alignement a strut of
    The undercarriage of and it is important to slow down the course of
    The undercarriage when approaching the deployed position to avoid any
    1'atterrisseur.
    shock detrimental to the integrity of
    This deceleration is simple to organize with a linear hydraulic actuator, by providing in the actuator an end-of-travel retarder (dash-pot). Furthermore, the probability of blockage of such an actuator is so low that a declutching system is not required to meet the certification requirements.
    As part of aircraft electrification programs, the attention of aircraft manufacturers has been drawn to the use of electromechanical type actuators. It has for example been proposed in the document FR 2946319 to use a rotary electromechanical type actuator actuator coupled to one of the arms of the strut stabilization member in the aligned position to both ensure the maneuver of 1 ' undercarriage and unlocking of the stabilization member.
    It is difficult to regulate the speed of descent of the undercarriage with this type of actuator. In fact, if the regulation is ensured by the actuator motor, the latter then acts essentially as a brake and reinjects current into the network of the aircraft, which is generally not desired. It is then necessary to equip the electromechanical actuator with a speed regulation and end-of-travel damping member, for example a device or in the hydraulic device document FR2958981 adapted mechanical friction such as that illustrated to actuators
    However, these devices notably the electromechanical actuator.
    rotatable.
    complicate
    In addition, the reliability of this type of actuator is not to dispense with a declutching system deployment of the undercarriage in high enough allowing the possibility of a blockage of the actuator.
    damping must be the actuator is disengaged,
    The regulator capable of operating even when this adds to the complexity of such an actuator.
    OBJECT OF THE INVENTION
    The invention aims to propose a method for maneuvering an aircraft undercarriage making it possible to use a simple electromechanical actuator.
    PRESENTATION OF THE INVENTION
    With a view to achieving this goal, a method of maneuvering a mobile aircraft undercarriage between a retracted position and a deployed position is proposed, the method comprising:
    - the use of a rotary electromechanical actuator of maneuver coupled to a part of the undercarriage to ensure the lifting of the deployed position to the retracted position;
    - disengagement of the operating actuator during a descent of the undercarriage from the retracted position to the deployed position and the use of a linear hydraulic shock absorber coupled to a part of the undercarriage to regulate a descent speed and / or cushion an arrival of the undercarriage in the deployed position;
    - neutralization of the shock absorber during lifting.
    The method of the invention makes it possible to use a very simple electromechanical actuator provided with a simple declutching member.
    The regulation and damping are entrusted to a hydraulic shock absorber very simple to design.
    Speed regulation is very easily obtained by means of a simple calibrated orifice, and can even be varied throughout the race by using a suitable rolling needle.
    End-of-travel damping is very easily achieved by means of an end-of-travel retarder. Finally, neutralization of the shock absorber during lifting is easily obtained in a purely passive manner by means of a bypass valve. The hydraulic shock absorber is very simple to design, and performs its function even in the event of the electromechanical actuator blocking.
    The shock absorber is preferably an autonomous member, not connected to a hydraulic circuit of the aircraft. The method of the invention therefore allows the use of simple organs, and easy to install.
    PRESENTATION OF THE FIGURES
    The invention will be better understood in the light of the following description of a particular embodiment of the invention with reference to the figures of the accompanying drawings, among which
    - Figure 1 is a side view of a landing gear applying the provisions of the invention, illustrated here in the deployed position;
    - Figures 2 to 4 are skeletal side views of the undercarriage of Figure 1, showing it at various stages of a lift, namely the deployed position, an intermediate position, and the retracted position;
    - Figure 5 is a schematic sectional view of the hydraulic linear shock absorber fitted to the undercarriage of Figure 1.
    DETAILED DESCRIPTION OF A PARTICULAR MODE OF IMPLEMENTING THE INVENTION
    Referring firstly to FIG. 1, the undercarriage comprises, in a manner known per se, a leg 1 articulated to the structure of the aircraft along an axis of articulation X (seen here at the end) to be movable between a position deployed illustrated here in which the undercarriage is brought before a landing, and a retracted position which is that of the undercarriage in flight.
    A breaking strut 2 is articulated on the one hand on the leg 1 and on the other hand on the structure of the aircraft.
    The breaker strut comprises two connecting rods 2a,
    2b, articulated together at a knee 3. The connecting rod 2a is also articulated on the aircraft, while the connecting rod 2b is articulated on the leg 1. The breaker strut is stabilized in a substantially aligned position by means of a stabilization member 4 comprising two links 4a,
    4b, also hinged together.
    The link
    4a is articulated on the leg 1, and the link
    4b is articulated on the strut 2. The rods
    4a,
    4b are held in a substantially aligned position by a locking member 5 comprising return springs 6 recalling the rods 4a, 4b towards the locking position defined by stops 7a, 7b. Thus stabilized, the breaking strut 2 opposes any rotation of the leg 1 around its axis of articulation X, so that the deployed position is a stable position. As is well known, the connecting rods 2a, 2b and the connecting rods 4a, 4b are designed so that to arrive at the locked position illustrated here, the articulation knee of the connecting rods and the articulation knee of the connecting rods pass slightly beyond the geometric alignment illustrated by the broken lines.
    According to the invention, a maneuver actuator 10 is arranged on the structure of the aircraft to be coupled to the link 4a of the stabilization member 4, that which is here articulated on the leg 1. Here, the actuator maneuver 10 is of the electromechanical rotary type and comprises an output shaft driving a crank 11 which is coupled to the rod 4a by means of a rod 8 coupled to a crank 11 integral with the output shaft of
    The operating actuator 10.
    The operating actuator 10 is provided with a disengaging member making it possible to disengage in rotation the crank 11 from its output shaft, and, consequently, to disengage the operating actuator 10 from
    1'atterrisseur.
    Always according to
    Invention, a linear hydraulic shock absorber
    20, separate from
    The operating actuator
    10, is coupled on the one hand the structure of
    The aircraft and on the other hand to a crank secured to the link 4a.
    The operation of the assembly is now explained with reference to FIGS. 2 to 4. When the undercarriage has to be raised in the retracted position, the operating actuator 10 is acted upon. It exerts a traction on the link 4a (see arrow), which has the effect of making it pivot around its axis of rotation on the leg, and thus breaking the alignment of the
    rods 4a, 4b against of 1'action of the springs reminder 6 of the locking member 5. As the link 4b is harnessed at the strut 2 1'alignement of the rods 2a, 2b East
    also broken. The undercarriage is thus unlocked and can be pivoted about its hinge axis under the action of the operating actuator 10, as illustrated in FIG. 3.
    While the actuator 10 continues to rotate the link 4a, the latter successively drives the other link 4b, the links 2a, 2b of the strut 2, and, finally, the leg 1 of the undercarriage. All these elements are linked together so that an angular position of the link 4a corresponds to one and only one position of each of these elements. The movement continues until the position illustrated in FIG. 4, in which the leg 1 has arrived in the retracted position.
    It is important to ensure that during the movement of the undercarriage from its deployed position to its retracted position, the link 4a moves in a continuous movement and without singularity, so that the movement of the leg can be ensured by means of 'A continuous action and always in the same direction of the operating actuator 10 on the link 4a. So,
    with one actuator, we ensure the misalignment of The organ of stabilization, this mistletoe provoke of the misalignment of the strut, and therefore the displacement of leg.
    The lander in position
    For the descent of deployed, we order
    1 clutch release member
    The operating actuator
    10, this mistletoe makes it possible to separate in rotation the shaft from
    The actuator and the crank 11 laguelle the rod
    The undercarriage can descend freely under the action of gravity and aerodynamic forces acting on
    1'atterrisseur.
    In addition, the presence of the declutching member makes it possible to guarantee the descent of
    The undercarriage even in the event of failure, and in particular of blockage, of
    The operating actuator 10.
    The role of the hydraulic linear damper is now explained. As can be seen in FIG. 5, the linear hydraulic damper 20 comprises a body 22 in leguel a rod 23 terminated by a piston 24 slides with sealing, defining two chambers 25 and 26 filled with hydraulic fluid. A calibrated orifice 27 extending through the piston 24 allows the fluid to pass from one chamber to the other during an extension of the damper 20 by exerting a resistance to the passage of the fluid proportional to the square of the speed d 'elongation. A by-pass valve 28 carried by the piston 24 allows the fluid to pass from one chamber to the other without resistance during a shortening of the damper 20. Finally, the piston 24 has at its base a bulge 30 which penetrates adjustable in a cylindrical cavity 31 at the bottom of the body 22, trapping fluid which can only come out through a channel with calibrated diameter 32 which returns the fluid to one of the chambers of the shock absorber (device known as the dashpot ). An accumulation device, not shown, absorbs or supplies the differences in volume of fluid between the two chambers during maneuvers of the undercarriage.
    Thus, during the raising of the undercarriage illustrated in FIGS. 2 to 4, the hydraulic linear damper 20 shortens but exerts no resistance, the bypass 28 allowing the free passage of one chamber to the other of the hydraulic fluid and thus completely passive neutralization of the hydraulic linear shock absorber during lifting.
    On the contrary, during the descent of the undercarriage under the sole effect of gravity and aerodynamic forces, the hydraulic linear shock absorber lengthens and the internal fluid is forced to pass from one chamber to the other through 1 calibrated orifice
    27, inducing a rolling of the proportional resistor of elongation of the shock absorber, of descent before the force position at the defined locking of the undercarriage.
    fluid and therefore a the links 4a,
    square speed this who regulates speed In end racing, just 4b born reach the ; speak s stops 7a, 7b, the
    31, in the bulge cavity 30 penetrates with adjustment forcing the fluid thus trapped to exit through the calibrated orifice
    32, which greatly slows
    The undercarriage thus avoiding any brutal shock during
    The arrival of
    The undercarriage in the deployed position.
    The hydraulic linear damper 20 operates during any descent of the undercarriage, whether this is voluntarily controlled by the pilot prior to a landing, or following a blocking of the maneuvering actuator 10 during a lifting operation bringing the pilot to command an emergency exit from the undercarriage during which the maneuvering actuator 10 is detached from the undercarriage by command of its declutching member.
    The invention is not limited to what has just been described, but on the contrary covers any variant coming within the scope defined by the claims.
    In particular, although in the example illustrated, the maneuvering actuator 10 is coupled to one of the links of the stabilization member, which allows it to be unlocked at the same time as the landing gear is raised, otherwise arrange the operating actuator, for example directly on the pivot of the rod 4A, or alternatively by coupling it to the leg of the undercarriage or to one of the rods of the strut.
    It will then be necessary to provide an unlocking actuator for misaligning the links of the stabilization member during the raising of the undercarriage.
    Preferably, the hydraulic linear damper is arranged to act on one of the connecting rods
    The locking member to cushion
    The arrival in the locked position of the rods, and therefore the arrival in the aligned position of the strut. However, it may be arranged otherwise, for example by being coupled between the strut and the stabilization member, or by being coupled between the structure of the aircraft and the landing gear leg. In addition, it may be arranged so as to shorten when descending the undercarriage and lengthen when lifting the undercarriage. Finally, if necessary, a variation of the resisting force with the stroke of the damper can be organized, for example by means of a rolling needle.
    Finally, the provisions of the invention apply particularly to a landing gear comprising at least one breaker strut and to alignment member 10 with alignment. However, they can be applied to other types of undercarriages, in particular undercarriages with an internally locked strut, or undercarriages with telescopic strut.
    权利要求:
    Claims (5)
    [1" id="c-fr-0001]
    1. Method for maneuvering an aircraft undercarriage (1) movable between a retracted position and a deployed position, the method comprising:
    - the use of a maneuver actuator (10) of the rotary electromechanical type coupled to a part of the undercarriage (4a) to ensure the lifting of the deployed position to the retracted position;
    - disengaging of the maneuvering actuator during a descent of the undercarriage from the retracted position to the deployed position and the use of a linear hydraulic shock absorber (20) coupled to a part of the undercarriage (4a) to regulate a descent speed and / or dampen an arrival of the undercarriage in the deployed position;
    neutralization of the shock absorber during lifting.
    [2" id="c-fr-0002]
    2. Method according to claim 1, applied to a undercarriage comprising at least one breaker strut with two connecting rods (2a, 2b), stabilized in the aligned position by a stabilization member with two connecting rods (4a, 4b) recalled in the aligned position. by a spring member (6) of a locking member (5), in which the lifting actuator (10) is coupled to one of the rods of the locking member (4a).
    [3" id="c-fr-0003]
    3. Method according to claim 2, wherein the hydraulic linear damper (20) is also coupled to one of the rods of the stabilization member (4a).
    [4" id="c-fr-0004]
    4. Method according to claim 1, in which the disengagement of the operating actuator is carried out by means of a disengaging member equipping the operating actuator and making it possible to separate an output shaft of the operating actuator from an element (11) driven by the output shaft to maneuver
    1'atterrisseur.
    [5" id="c-fr-0005]
    5. Method according to claim 1, in which the neutralization of the hydraulic linear damper (20) is obtained passively by a bypass (28) installed between two chambers (25,26) of the damper.
    类似技术:
    公开号 | 公开日 | 专利标题
    CA3024232C|2020-12-22|Manoeuver process for aircraft landing gear between a retracted position and a deployed position
    CA2764219C|2014-09-23|Method for operating a landing gear assembly with a breaker strut
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    CA2760646C|2015-03-03|Electromecanical telescopic actuator
    FR2689087A1|1993-10-01|Lifting landing gear for aerodynes, especially for helicopters.
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    FR2687123A1|1993-08-13|Retractable landing gear of an aircraft, especially for a helicopter
    EP3826918A1|2021-06-02|Device for opening an aircraft door in emergencies, said device having a lever-type retention member
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    FR3056552A1|2018-03-30|EXTERNAL ANCHORING HARPOON FOR AIRCRAFT
    FR3007483A1|2014-12-26|TRANSMISSION DEVICE AND AIRCRAFT ENGINE NACELLE COMPRISING AN ACTUATOR INCORPORATING SUCH A TRANSMISSION DEVICE
    BE430072A|
    同族专利:
    公开号 | 公开日
    US20190144104A1|2019-05-16|
    CA3024232A1|2019-05-15|
    EP3486166A1|2019-05-22|
    CA3024232C|2020-12-22|
    EP3486166B1|2021-03-17|
    ES2876201T3|2021-11-12|
    CN109774923A|2019-05-21|
    US11161600B2|2021-11-02|
    FR3073494B1|2019-12-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2437135A|1943-11-05|1948-03-02|Boeing Co|Airplane landing gear and emergency release mechanism therefor|
    EP0557181A1|1992-02-21|1993-08-25|Messier Bugatti|Aircraft landing-gear extension damper|
    FR2946319A1|2009-06-05|2010-12-10|Messier Dowty Sa|METHOD FOR MANEUVERING A BREAKER COUNTERFRAME|
    FR2958981A1|2010-04-15|2011-10-21|Messier Dowty Sa|ELECTROMECHANICAL ACTUATOR WITH HYDRAULIC REGULATION, AND LIGHTER EQUIPPED WITH SUCH ACTUATOR FOR ITS MANEUVER|
    DE102014003157A1|2014-03-03|2015-09-03|Liebherr-Aerospace Lindenberg Gmbh|Electromechanical rotary actuator with unlocking|
    JP6093612B2|2013-03-21|2017-03-08|Ｋｙｂ株式会社|Magnetorheological fluid shock absorber|
    US9412507B2|2014-04-01|2016-08-09|The Boeing Company|Positioning system for an electromechanical actuator|
    EP3135581B1|2015-08-25|2018-03-21|Safran Landing Systems UK Limited|Aircraft landing gear assembly|US11155345B2|2019-11-11|2021-10-26|Goodrich Corporation|Side folding and reforming linkage for landing gear|
    US20210323657A1|2020-04-17|2021-10-21|Goodrich Corporation|Tripod landing gear assembly|
    US20210362841A1|2020-05-21|2021-11-25|The Boeing Company|Nose landing gear assembly for use with an aircraft|
    法律状态:
    2018-11-23| PLFP| Fee payment|Year of fee payment: 2 |
    2019-05-17| PLSC| Publication of the preliminary search report|Effective date: 20190517 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 3 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 4 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1760763A|FR3073494B1|2017-11-15|2017-11-15|METHOD FOR MANEUVERING AN AIRCRAFT LANDER BETWEEN A RETRACTED POSITION AND A DEPLOYED POSITION|
    FR1760763|2017-11-15|FR1760763A| FR3073494B1|2017-11-15|2017-11-15|METHOD FOR MANEUVERING AN AIRCRAFT LANDER BETWEEN A RETRACTED POSITION AND A DEPLOYED POSITION|
    EP18205509.5A| EP3486166B1|2017-11-15|2018-11-09|Method of operating an aircraft landing gear between a retracted position and an extended position|
    ES18205509T| ES2876201T3|2017-11-15|2018-11-09|Procedure for maneuvering an aircraft lander between a retracted position and a deployed position|
    CA3024232A| CA3024232C|2017-11-15|2018-11-09|Manoeuver process for aircraft landing gear between a retracted position and a deployed position|
    US16/191,313| US11161600B2|2017-11-15|2018-11-14|Methods of moving an aircraft undercarriage between a retracted position and a deployed position|
    CN201811352810.8A| CN109774923A|2017-11-15|2018-11-14|A method of moving aircraft landing gear between retracted position and expanded position|
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