• 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 aircraft undercarriage having a leg (2) pivotally mounted on a structure of the aircraft according to a pivot axis (X1) between an extended position and a retracted position, the undercarriage having a strut ( 3a, 3b) with two articulated elements, one of which is articulated on the leg, and the other is articulated on the structure of the aircraft, so that when the leg is in the deployed position, the two elements of the strut are locked in substantially aligned position, the undercarriage being further equipped with a rotary actuator (10) having an output shaft acting on one of the strut members to cause the pivoting of the leg between the two positions. The operating actuator is pivotally mounted on the aircraft structure about an axis of rotation (X3) of the output shaft, the actuating actuator having a housing (12) connected by a reaction rod ( 13) to the leg to take a torque developed by the actuator maneuver during a maneuver of the undercarriage.
    公开号:FR3053311A1
    申请号:FR1656315
    申请日:2016-07-01
    公开日:2018-01-05
    发明作者:Dominique Ducos；Philippe Henrion
    申请人:Safran Landing Systems SAS；
    IPC主号:
    专利说明:

    ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY © Publication number:
    (to be used only for reproduction orders)
    ©) National registration number
    053 311
    56315
    COURBEVOIE
    ©) Int Cl 8 : B 64 C 25/18 (2017.01)
    PATENT INVENTION APPLICATION
    A1
    ©) Date of filing: 01.07.16. © Applicant (s): SAFRAN LANDING SYSTEMS— FR. ©) Priority: ©) Inventor (s): DUCOS DOMINIQUE and HENRION PHILIPPE. (43) Date of public availability of the request: 05.01.18 Bulletin 18/01. ©) List of documents cited in the report preliminary research: Refer to end of present booklet (© References to other national documents ©) Holder (s): SAFRAN LANDING SYSTEMS. related: ©) Extension request (s): @) Agent (s): CABINET BOETTCHER.
    (04) AIRCRAFT LANDER WITH ROTARY MANEUVER ACTUATOR.
    FR 3 053 311 - A1 (b /) The invention relates to an aircraft undercarriage having a leg (2) pivotally mounted on a structure of the aircraft along a pivot axis (X1) between a deployed position and a retracted position, the undercarriage comprising a strut (3a, 3b) with two articulated elements, one of which is articulated on the leg, and the other is articulated on the structure of the aircraft, so that when the leg is in deployed position, the two elements of the strut are locked in a substantially aligned position, the undercarriage being further equipped with a rotary actuator (10) having an output shaft acting on one of the elements of the strut to cause the pivoting of the leg between the two positions. The operating actuator is pivotally mounted on the structure of the aircraft about an axis of rotation (Χ3) of the output shaft, the operating actuator having a casing (12) connected by a reaction rod ( 13) on the leg to take up a torque developed by the maneuvering actuator during a maneuver of the undercarriage.

    i
    The invention relates to an aircraft undercarriage with rotary actuator.
    TECHNOLOGICAL BACKGROUND OF THE INVENTION
    There are known aircraft undercarriages articulated on a structure of the aircraft between a deployed position and a retracted position. In the deployed position, the undercarriage is generally stabilized by a strut which is coupled to the undercarriage and to the structure of the aircraft, and which comprises two elements hinged together and kept in the aligned position. To allow the landing gear to be raised, the elements of the strut are misaligned in order to allow the landing gear to pivot to its retracted position under the action of a maneuvering actuator.
    There are known undercarriages in which the operating actuator is a rotary actuator acting on one of the elements of the strut. The maneuvering actuator is generally fixed to the structure of the aircraft and drives one of the elements of the strut, either directly or via a linkage. The structure of the aircraft must then be dimensioned to take up the forces and the torque developed by the maneuvering actuator during the maneuver of the undercarriage.
    OBJECT OF THE INVENTION
    The object of the invention is to propose an installation of the undercarriage relieving the structure of the aircraft during maneuvers of the undercarriage.
    PRESENTATION OF THE INVENTION
    In order to achieve this goal, an aircraft undercarriage is provided having a leg pivotally mounted on a structure of the aircraft along a pivot axis between a deployed position and a retracted position, the undercarriage comprising a double strut articulated elements, one of which is articulated on the leg, and the other is articulated on the structure of the aircraft, so that when the leg is in the deployed position, the two elements of the strut are locked in a substantially aligned position, The undercarriage is furthermore equipped with a rotary actuator having an output shaft acting on one of the elements of the strut to cause the leg to pivot between the two positions. According to the invention, the operating actuator is pivotally mounted on the structure of the aircraft about an axis of rotation of the output shaft, the lifting actuator having a casing connected by a reaction rod to the leg to take up a torque developed by the maneuvering actuator during a maneuver of the undercarriage.
    Thanks to the arrangement of the invention, the torque developed by the maneuvering actuator is not transmitted to the structure of the aircraft, but is taken up by the undercarriage itself.
    According to a particular embodiment of the invention, when the undercarriage is in the deployed position, the reaction rod is aligned with the pivot axis of the leg. Thus, in the event of movement or deformation of the undercarriage, for example on landing, the connecting rod cannot exert on the casing of the maneuvering actuator for a moment which would result in unlocking of the strut.
    According to another particular embodiment of the invention, the output shaft of the operating actuator acts on the element of the strut by means of a toggle lock locking the elements of the strut in an aligned position. when the undercarriage is in the deployed position.
    PRESENTATION OF THE FIGURES
    The invention will be better understood in the light of the description which follows of the particular embodiments of the invention, with reference to the figures of the appended drawings among which:
    - Figure 1 is a perspective view of an undercarriage according to a first particular mode of
    realisation of The invention, represented in position deployed; - The figure 2 is a side view partial of The lander the figure 1, shown in position deployed; - The figure 3 is a side view partial of 1 undercarriage the figure 1 shown in position retracted; - The figure 4 is a perspective view of a
    undercarriage according to a second particular embodiment of the invention, shown in the deployed position;
    - Figure 5 is a side view of the undercarriage of Figure 4, shown in the deployed position;
    - Figure 6 is a side view of the undercarriage of Figure 4 shown in the retracted position;
    - Figure 7 is a partial perspective view of the lock fitted to the strut of the undercarriage of Figure 4;
    - Figure 8 is another perspective view
    partial of lock fitted the strut of The lander in Figure 4. DETAILED DESCRIPTION OF MODES OF REALIZATION PARTICULARS OF THE INVENTION With reference to Figures 1 at 3, and in accordance at a first particular fashion of production of
    the invention, the undercarriage 1 comprises a leg 2 mounted articulated on the structure of an aircraft (not visible here) by means of a pivot 201 along a pivot axis XI, here substantially horizontal, to be movable between a deployed position illustrated in FIGS. 1 and 2 and a retracted position illustrated in FIG. 3. In the following, all the articulations mentioned have a pivot axis perpendicular to the plane of the figure, so that the pivot axes are all parallel between them.
    The undercarriage 1 comprises a strut 3, comprising two bracing elements 3a and 3b hinged together to a knee with a pivot axis X2. The first bracing element 3a is articulated on the structure of the aircraft by means of a pivot 202 along a pivot axis X3 while the second bracing element 3b is articulated on the leg 2 along a pivot axis X4 . In the deployed position, the two bracing elements 3a, 3b, and therefore the pivot axes X2, X3, X4 are substantially aligned. This position is defined by respective stops 4a, 4b of the bracing elements 3a, 3b, and is confirmed by means of a confirmation spring 5 coupled to the two bracing elements 3a, 3b to confirm the contact between the stops 4a, 4b .
    A rotary actuator 10 is disposed at the level of the pivot axis X3 so that its output shaft is rotatable along the pivot axis X3. The output shaft (not visible here) is directly connected to the first bracing element 3a. The actuator 10 comprises a casing 12 which is mounted for free rotation along the axis X3. A reaction rod 13 is articulated along two pivot axes X5, X6 between on the one hand the leg 2 and on the other hand a crank pin 14 secured to the casing 12.
    Thus, during the supply of the rotary actuator 10, its output shaft causes the rotation of the second bracing element 3b around the axis X3. The reaction torque is taken up by the reaction rod 13, but without any torque being transmitted to the structure of the aircraft.
    It will be noted that in the deployed position illustrated in FIGS. 1 and 2, the reaction rod 13 is in line with the pivot axis XI of articulation of the leg 2, that is to say the pivot axes X1, X5, X6 are aligned. This arrangement prevents, in the event of deformation or parasitic movement of the leg 2, for example during the impact on landing, that the reaction rod 13 could cause a rotation of the casing 12 so as to inadvertently unlock the strut.
    To cause the retraction of the leg, it suffices to rotate the actuator output shaft in the direction tending to move the stops 4a, 4b apart from each other, against the spring 5, breaking thus the alignment of the strut 3 and authorizing the pivoting of the leg under the traction exerted by the first strut element 3a, itself driven in rotation by the output shaft of the rotary actuator 10. The movement continues until the position illustrated in figure 3. On this figure, we see that the reaction rod 13 is in line with the pivot axis X3, that is to say that the pivot axes X3, X5, X6 are connected, thus ensuring stabilization of the leg 2 in the retracted position. In this position, the crank pin 14 and the reaction rod 13 are aliqnes. The feed position is preferably defined by stops secured respectively to the reaction rod 13 and the crank pin 14 which come into contact with one another in the feed position. This position is confirmed by a confirmation spring 15 coupled between the reaction rod 13 and the crank pin 14.
    In the movement from the deployed position to the retracted position, only the pivot axes XI and X3 (which correspond to pivots 201,202 on the structure of the aircraft) remain fixed. All the other axes are closing, parallel to themselves. The casing 12 of the actuator 10 and the leg 2 have rotated about a quarter of a turn.
    According to a second embodiment illustrated in Figures 4 to 8, in which the elements common with the previous embodiment bear references increased by a hundred, the output shaft of the actuator 110 is no longer directly connected to the first bracing element 103a but to a toggle lock 120 ensuring locking of the strut 103 in the aligned position.
    The toggle bolt 120 comprises a first locking element 120a which is articulated on the first bracing element 103a along a pivot axis X7, and which is articulated on a second locking element 120b along a pivot axis X8, itself articulated on a crank pin 121 of the second bracing element 103b along a pivot axis X9. In the locked position, which corresponds to the deployed position of the undercarriage, the pivot axes X7, X8, X9 are substantially aligned. This position is defined by internal stops not shown here, but which play the same role as the stops 4a, 4b. Maintaining the locking elements 120a, 120b in an aligned position causes the bracing elements 103a, 103b to be kept in an aligned position.
    As before, the casing 112 of the rotary actuator 110 comprises a crank pin 114 connected to the leg 102 by a reaction rod 113.
    The output shaft comprises a control pin 122 which is coupled to the first locking element 120a by a rod 123. Starting from the deployed position illustrated in FIG. 4, the supply of the rotary actuator 110 brings the output shaft to be pulled on the rod 123 via the crank pin 122. This traction causes the locking elements 120a, 120b to be misaligned, which causes the bracing elements to be misaligned
    103a, 103b. The rest retracted is then ίο from the movement to the position identical to that of the previous embodiment, except that the output shaft of the lift actuator 110 is not directly linked to one of the elements bracing, but is linked to them via the locking elements 120a, 120b the rotary actuator 110 therefore ensures both the unlocking and the misalignment of the strut, and the lifting of the leg.
    In the same way as before, the lifting torque developed by the maneuvering actuator 110 is transmitted by the reaction rod 113 to the leg 102, which relieves the structure of the aircraft.
    权利要求:
    Claims (4)
    [1" id="c-fr-0001]
    1. aircraft undercarriage having a leg (2; 102) pivotally mounted on an aircraft structure along a pivot axis (XI) between a deployed position and a retracted position, the undercarriage comprising a strut (3a, 3b ; 103a, 103b) with two articulated elements, one of which is articulated on the leg, and the other is articulated on the structure of the aircraft, so that when the leg is in the deployed position, the two elements of the strut are locked in a substantially aligned position, the undercarriage is furthermore equipped with a rotary actuator (10; 110) having an output shaft acting on one of the elements of the strut to cause the leg to pivot between the two positions, characterized in that the operating actuator is pivotally mounted on the aircraft structure around an axis of rotation (X3) of the output shaft, the operating actuator having a housing (12; 112) connected by a reaction rod ( 13; 113) on the leg to take up a torque developed by the maneuvering actuator during a maneuver of
    The lander.
    [2" id="c-fr-0002]
    2. Landing gear according to claim 1, wherein the output shaft of the operating actuator (12) is directly connected to one of the bracing elements (3a, 3b).
    [3" id="c-fr-0003]
    3. undercarriage according to claim 2, wherein the output shaft of the operating actuator (112) is connected to the bracing elements via locking elements (120a, 120b) of the strut elements in the aligned position when 1 ' undercarriage is in the deployed position.
    [4" id="c-fr-0004]
    4. Landing gear according to claim 1, wherein the axis of rotation of the output shaft of the actuator coincides with a pivot axis (X3) of the strut (3) on the structure of the aircraft.
    1/6
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3053311A1|2018-01-05|AIRCRAFT AIR TERMINATOR WITH ROTARY ACTUATOR
    CA2764219C|2014-09-23|Method for operating a landing gear assembly with a breaker strut
    FR2990412A1|2013-11-15|LANDING TRAIN FOR AIRCRAFT
    EP2571760B1|2015-04-08|Landing gear with gear unlock device
    EP0555121A1|1993-08-11|Retractable landing gear equipped with an articulated, double diagonal brace
    CA3031825C|2020-07-14|Landing gear with lighted brace
    WO2014083170A1|2014-06-05|Landing gear with realigning lock link assembly
    CA1226258A|1987-09-01|Nose type landing gear for aircraft
    CA2767857C|2014-11-18|Nose gear of an aircraft comprising a single control device for retraction and steering
    EP3539867B1|2020-09-16|Maneuvering method for a landing gear between a deployed and a retracted position
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    FR3048954A1|2017-09-22|LOCK ACTUATOR DISENGAGING SYSTEM ON AN AIRCRAFT ENGINEER.
    EP0855361A1|1998-07-29|Telescopic mast for a tower crane
    CA1139286A|1983-01-11|Landing gear
    EP0676328A2|1995-10-11|Vertically retractable landing gear for wide-body aircraft
    EP1279591A1|2003-01-29|Vertically retractable landing gear for transport aircraft
    FR2812613A1|2002-02-08|Aircraft landing gear with directional axle which pivots either side median position, axle directional control comprises two actuators articulated on axle and on selector connected to lever arm
    EP0615901A1|1994-09-21|Aircraft landing gear with lateral retraction
    FR2464883A1|1981-03-20|Retractable undercarriage for aircraft - has locking toggle released by initial movement of actuating jack
    FR3078943A1|2019-09-20|METHOD FOR MANEUVERING AN AIRCRAFT ENGINEER BETWEEN A DEPLOYED POSITION AND A RETRACTED POSITION
    FR3110543A1|2021-11-26|Aircraft retractable landing gear fitted with an integrated actuator strut
    EP0635426A1|1995-01-25|Aircraft landing gear with lateral retraction
    BE408511A|
    FR2485471A2|1981-12-31|Retractable undercarriage for aircraft - has locking toggle released by initial movement of actuating jack
    同族专利:
    公开号 | 公开日
    CN107554756B|2020-08-18|
    EP3263450B1|2019-10-09|
    ES2755874T3|2020-04-24|
    US20180001997A1|2018-01-04|
    US10479486B2|2019-11-19|
    EP3263450A1|2018-01-03|
    FR3053311B1|2018-08-17|
    CN107554756A|2018-01-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2946319A1|2009-06-05|2010-12-10|Messier Dowty Sa|METHOD FOR MANEUVERING A BREAKER COUNTERFRAME|
    US20130299633A1|2012-05-10|2013-11-14|Ge Aviation Systems Limited|Landing gear for an aircraft|
    FR3022886A1|2014-06-25|2016-01-01|Messier Bugatti Dowty|DEVICE FOR UNLOCKING A LICENSOR IN A DEPLOYED POSITION AND LIGHTER EQUIPPED WITH SUCH A DEVICE|
    FR2960215B1|2010-05-18|2012-06-08|Messier Dowty Sa|DEVICE FOR UNLOCKING A LICENSOR IN A DEPLOYED POSITION AND LIGHTER EQUIPPED WITH SUCH A DEVICE|
    WO2014201225A1|2013-06-14|2014-12-18|Bombardier Inc.|Apparatus and method for controlling landing gear|FR3080894B1|2018-05-04|2021-11-26|Latecoere|PROCESS AND SYSTEM FOR MAINTAINING A SHAFT IN BISTABLE POSITIONING|
    FR3080893B1|2018-05-04|2020-05-15|Latecoere|METHOD AND SYSTEM FOR SPRING HOLDING OF A SHAFT IN BISTABLE POSITIONING|
    FR3080895B1|2018-05-04|2021-11-26|Latecoere|METHOD AND SYSTEM FOR HOLDING A BISTABLE BLADE OF A SHAFT ACCORDING TO TWO STATE POSITIONS|
    CN109774922B|2019-01-22|2022-01-18|南京航空航天大学|Main land playing device of variable grounding point|
    FR3110543A1|2020-05-20|2021-11-26|Safran Landing Systems|Aircraft retractable landing gear fitted with an integrated actuator strut|
    法律状态:
    2017-04-26| PLFP| Fee payment|Year of fee payment: 2 |
    2018-01-05| PLSC| Publication of the preliminary search report|Effective date: 20180105 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 3 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 4 |
    2021-04-09| ST| Notification of lapse|Effective date: 20210305 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1656315A|FR3053311B1|2016-07-01|2016-07-01|AIRCRAFT AIR TERMINATOR WITH ROTARY ACTUATOR|
    FR1656315|2016-07-01|FR1656315A| FR3053311B1|2016-07-01|2016-07-01|AIRCRAFT AIR TERMINATOR WITH ROTARY ACTUATOR|
    US15/633,884| US10479486B2|2016-07-01|2017-06-27|Aircraft undercarriage with a rotary drive actuator|
    EP17178220.4A| EP3263450B1|2016-07-01|2017-06-27|Aircraft undercarriage with a rotary drive actuator|
    ES17178220T| ES2755874T3|2016-07-01|2017-06-27|Aircraft landing system with a rotary maneuver actuator|
    CN201710522847.XA| CN107554756B|2016-07-01|2017-06-30|Aircraft landing gear with rotary drive actuator|
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