• 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 aim of the invention is to propose a simple device for locking and unlocking the locking member of a striker strut lug comprising an unlocking device comprising: a rotary actuator with an axis parallel to an axis of articulation of the links the stabilizing member, • a crank connected to the actuator shaft, • a pawl articulated at the end of the crank and comprising a redan, • an integral and protruding olive of one of the rods of the stabilizing member, • the pawl return means bearing towards the olive, the actuator being operable between a first angular position for which the olive is in contact with the pawle opposite the redan while the rods are substantially aligned and a second angular position for which the pawl has pushed the olive, causing misalignment of the links of the stabilizing member.
    公开号:FR3022886A1
    申请号:FR1455929
    申请日:2014-06-25
    公开日:2016-01-01
    发明作者:Du Marc Quenerch；Gerard Balducci
    申请人:Messier Bugatti Dowty SA；
    IPC主号:
    专利说明:

    [0001] The invention relates to a device for unlocking a landing gear strut breaker. BACKGROUND OF THE INVENTION As illustrated in FIGS. 1 and 2, which are diagrammatic views of a straightener strut machine equipped with a crank locking device, and as otherwise described in the document FR2960215, an undercarriage is known. aircraft which has a leg 7 articulated on the aircraft along a lifting axis 5 perpendicular to the plane of the figure. It also comprises a bracing member comprising a strut 2 itself consisting of two connecting rods 2a and 2b, articulated together in one knee 4 and hitched respectively to the leg 7 and to the aircraft. The rods 2a and 2b of the strut 2 are held in position substantially aligned by a stabilizing member 3 comprising two links 3a and 3b hinged together, one link 3a is articulated on the strut 2 and another 3b is articulated on the leg , said rods 3a and 3b being maintained in substantially aligned position and locked by at least one locking member comprising a locking spring 10 which recalls the links to a substantially aligned position defined by a stop 12. The unlocking spring 10 allows avoid an accidental rupture of the alignment of the stabilization member but imposes a major effort to break this alignment voluntarily during a lift of the undercarriage. The substantially aligned position of the rods 3a and 3b of the stabilizing member 3 is provided by a stop 12 comprising two half-stops 12a and 12b respectively mounted on the rods 3a and 3b and cooperating to block the movement of the stabilizing member 3 As more particularly visible in FIG. 2, the undercarriage is equipped with an unlocking device 6 which here comprises: a support 61 that can be attached to the aircraft or to the leg 7, a rotary actuator 62, fixed a support 61, and axis parallel to the axis of the rods 3a and 3b of the stabilizing member, ^ a crank 63 connected by one of its ends to the rotary shaft of the actuator 62, ^ a ratchet 64 articulated at the end of the crank 63 and having a body in which is formed a redan 65 and a rod 68 extending the body beyond the redan, ^ An olive 31 integral and protruding from the stabilizing member 3 and placed on one of the links 3b, ^ Exhaust roller 32 placed on the same link 3b as the olive 31, ^ And a spring 67 for returning the pawl 64 to the olive 31. Figure 3 also illustrates the stop 12 in a position for which the half stops 12a and 12b are in contact and ensure the alignment of the rods 3a and 3b. In this position, the redan 65 is formed in the pawl 64 so that it is not in contact with the olive 31. The crank 63 is operable between a first angular position for which the olive 31 is in contact with the pawl 64 opposite the redan 65 while the rods are substantially aligned, and a second angular position that the crank 63 reaches while the redan 65 of the pawl 64 has pushed the olive 31, causing the misalignment of the rods 3a, 3b of the Thus, the unlocking device makes it possible to release the stabilization member by means of a simple actuator, all without a permanent link between the rods of the stabilization member and the actuator. so that if the actuator locks, the undercarriage can still be maneuvered. However, it could occur failure cases in which the unlocking device could be faulty, preventing the retraction of the undercarriage or immobilizing the undercarriage when it is not yet locked. Although this case of failure is not critical from the point of view of the safety of the aircraft, it nevertheless forces the pilot to turn back to return for repair, which significantly disrupts the operation of the aircraft . OBJECT OF THE INVENTION The object of the invention is to propose a simple solution making it possible to ensure retraction and extension of the undercarriage even with a breakdown of the unlocking device while the undercarriage is in the deployed position. PRESENTATION OF THE INVENTION In view of the embodiment, there is provided an aircraft landing gear comprising a leg articulated on the aircraft along a lifting axis, the leg being stabilized in the extended position by a strut with two connecting rods articulated with each other, the strut being maintained in aligned position by a stabilizing member comprising two links articulated together, one link is articulated on the strut and another articulated on the leg or on the aircraft, said links being held in substantially aligned and locked position, wherein the undercarriage comprises an unlocking device comprising: a rotary actuator with an axis parallel to an axis of articulation of the rods of the stabilization member; a crank connected to an actuator shaft; a ratchet articulated at the end of the crank and comprising a redan, - an integral and protruding olive of one of the rods of the stabilizing member, the return means of the pawl bearing towards the olive, the crank being operable between a first angular position for which the olive is in contact with the pawl opposite the redan while the rods are substantially aligned, and a second angular position that the crank reaches while the redan of the pawl pushed back the olive, causing misalignment of the rods of the stabilizing member. From this position, the main actuating actuator manages complete retraction and full extension of the undercarriage, the unlocking device no longer being activated. The reset of the unlocking actuator is triggered only when the undercarriage is in the deployed, locked position. According to the invention, the rotary actuator of the unlocking device comprises two actuating elements connected in parallel to actuate the crank, the two actuating members being controlled and fed by two distinct paths independent of one another each of the actuating members being able to actuate the crank alone. Thus, the failure of one of the actuating members does not cause the locking of the undercarriage. The undercarriage can be returned to, retracted position using the second actuator. After detection of the non-return of the locking device 30 in its initial position the faulty actuating member can be the subject of a maintenance action on arrival of the aircraft at its destination. Preferably, the unlocking device comprises a spare control to separate the pawl of the olive in case of failure of the actuator during the descent of the undercarriage. BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood in the light of the figures of the accompanying drawings among which, in addition to Figures 1 and 2 already mentioned: - Figures 3a to 3d are views of the same unlocking device of the undercarriage already illustrated, illustrating the latter at different stages of lifting the undercarriage - Figure 4 is a detailed view of the actuator of the unlocking device according to one embodiment of the invention.
    [0002] DETAILED DESCRIPTION OF THE INVENTION Referring to the references of the figures already illustrated, FIGS. 3a to 3d illustrate in detail the operation of the unlocking device 6 when the undercarriage passes from the deployed position to the retracted position. FIG. 3a illustrates the actuator 62 in a first angular position D corresponding to the undercarriage deployed, for which the olive 31 is in contact with the pawl 64 opposite the redan 65. The substantially aligned position of the rods 3a and 3b of the stabilizing member 3 is provided by half-stops 12a and 12b respectively mounted on the rods 3a and 3b and which form a stop 12. As illustrated in Figure 3b, the actuator is then actuated in the direction indicated by the arrow, causing a pawl push (arrow P) on the rod 3b via the redan 65 and the olive 31, and therefore the rupture of the alignment of the rods 3a and 3b of the stabilizing member 3 The actuator 2 continues its movement until the pawl 64 comes into contact with the exhaust roller 32. The latter pushes the pawl 64_ and breaks the support between the olive 31 and the pawl 64 as illustrated in FIG. Figure 3c. The actuator 62 is represented here in a second angular position R in which it therefore no longer exerts thrust on the rod 3b of the stabilizing member 3. The lifting cylinder 8 then takes over to cause the recovery of the lander. During this ascent, the olive 31 separates more and more from the pawl 64, the exhaust roller 32 sliding on the body of the pawl 64. Figure 3d illustrates the unlocking device 6 when the undercarriage is in the retracted position . According to the invention, and with reference to FIG. 4, the rotary actuator 62 comprises two actuating members 100 and 101 mounted in parallel to rotate both the crank 63. Each actuating member comprises a motor 100A, 101A associated with a reducer 100B, 101B whose output shaft drives the crank 63. Each reducer is arranged so that the driving of the crank 63 by one of the actuating members can not be prevented or disturbed by the other actuator. Thus, the failure of one of the actuating members does not cause irreversible locking of the undercarriage in the deployed position, since the other actuator can take the relay and operate the pawl 64 to unlock the strut 2. Each engine 100A, 101A is powered and controlled by two separate channels 100C, 101C, independent of each other. In normal mode, the two actuators 100, 101 may work together or alternatively to allow their regular operation test. Of course, each actuator is capable by itself of operating the crank 63. The invention is not limited to what has just been described, but on the contrary encompasses any variant within the scope defined by the claims.
    权利要求:
    Claims (4)
    [0001]
    REVENDICATIONS1. An aircraft landing gear comprising a leg (7) articulated on the aircraft along a lifting axis (5), the leg being stabilized in the deployed position by a strut (2) with two connecting rods (2a, 2b) hinged together, the strut being held in aligned position by a stabilizing member (3) having two links (3a, 3b) hinged together, one link (3a) is articulated on the strut and another hinged (3b) on the leg or on the aircraft, said rods (3a, 3b) being maintained in substantially aligned and locked position, the undercarriage comprises an unlocking device (6) comprising: - a rotary actuator (62) having an axis parallel to an axis of articulation of the rods (3a, 3b) of the stabilizing member, - a crank (63) connected to a shaft of the actuator (62), 20 - a pawl (64) articulated to the end of the crank and comprising a redan (65), - an olive (31) integral and projecting a rods (3b) of the stabilizing member (3), 25 - pawl return means (64) bearing towards the olive (31), the crank (63) being operable between a first angular position for which the olive (31) is in contact with the pawl (64) facing the redan (65) while the rods are substantially aligned, and a second angular position that the crank (63) reaches while the redan (65) ratchet (64) pushed back the olive (31), causing misalignment of the rods (3a, 3b) of the stabilizing member (3); Characterized in that the rotary actuator (62) of the unlocking device comprises two actuators (100, 101) connected in parallel to actuate the crank, the two actuating members being controlled and fed by two separate channels (100C, 101C ) independent of each other, each of the actuators can alone operate the crank.
    [0002]
    2. Landing gear according to claim 1 wherein the rod (3b) which carries the olive (31) comprises an exhaust roller (32) cooperating with the pawl (64) to separate the ratchet (64) of the olive (31) when the actuator (62) moves from the first angular position to the second angular position.
    [0003]
    3. Landing gear according to claim 1 wherein the unlocking device 6 comprises a spare control to separate the pawl (64) of the olive (31) in case of failure of the actuator (32) during the descent of the lander.
    [0004]
    A landing gear according to claim 1 wherein the links (3a, 3b) are held in substantially aligned position by the engagement of the olive (31) with the step (65) when the actuator is in the first angular position.
    类似技术:
    公开号 | 公开日 | 专利标题
    CA2799688C|2015-06-30|Device for unlocking a landing gear in a deployed position and a landing gear comprising one such device
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    同族专利:
    公开号 | 公开日
    FR3022886B1|2016-10-21|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1749741A1|2005-07-26|2007-02-07|Airbus UK Limited|Landing gear|
    FR2960215A1|2010-05-18|2011-11-25|Messier Dowty Sa|DEVICE FOR UNLOCKING A LICENSOR IN A DEPLOYED POSITION AND LIGHTER EQUIPPED WITH SUCH A DEVICE|EP3263450A1|2016-07-01|2018-01-03|Safran Landing Systems|Aircraft undercarriage with a rotary drive actuator|
    CN108725762A|2017-04-14|2018-11-02|哈工大机器人集团有限公司|Novel unmanned plane undercarriage and unmanned plane|
    EP3539867A1|2018-03-16|2019-09-18|Safran Landing Systems|Maneuvering method for a landing gear between a deployed and a retracted position|
    FR3078943A1|2018-03-16|2019-09-20|Safran Landing Systems|METHOD FOR MANEUVERING AN AIRCRAFT ENGINEER BETWEEN A DEPLOYED POSITION AND A RETRACTED POSITION|
    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
    FR1455929A|FR3022886B1|2014-06-25|2014-06-25|DEVICE FOR UNLOCKING A LICENSOR IN A DEPLOYED POSITION AND LIGHTER EQUIPPED WITH SUCH A DEVICE|FR1455929A| FR3022886B1|2014-06-25|2014-06-25|DEVICE FOR UNLOCKING A LICENSOR IN A DEPLOYED POSITION AND LIGHTER EQUIPPED WITH SUCH A DEVICE|
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