• 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 landing gear comprising a leg (1) intended to be mounted to move on an aircraft structure between an extended position and a retracted position, the undercarriage comprising a bracing member (10) arranged between the structure of the aircraft and the leg to stabilize the latter in the deployed position, and a maneuvering actuator for moving the leg from the deployed position to the retracted position. According to the invention, the bracing member comprises a strut arm (10) having a proximal end intended to be articulated on the structure of the aircraft, the arm having a longitudinal lumen extending to a distal end for ending with a return and in which is slidably engaged a finger secured to the leg, the actuating actuator being coupled to said strut arm.
    公开号:FR3077557A1
    申请号:FR1850904
    申请日:2018-02-02
    公开日:2019-08-09
    发明作者:Daniel Moine；Herve Rolinat
    申请人:Safran Landing Systems SAS；
    IPC主号:
    专利说明:

    The invention relates to a light strut undercarriage.
    BACKGROUND OF THE INVENTION
    Landers are known comprising a leg mounted mobile on the structure of an aircraft between a deployed position and a retracted position.
    The leg is stabilized in the deployed position by a lockable bracing member when the leg arrives in said position, but which can be unlocked to allow retraction of the leg to the retracted position.
    Different types of strut are known, including the breaker strut comprising two articulated elements which are held in aligned position by a stabilizing member forming a lock (itself often comprising two confirmed arms in position aligned by a spring member), or also the telescopic strut fitted with an internal locking member forming a lock. Locking is generally automatic when the leg arrives in the deployed position and is confirmed by a spring member.
    Such a undercarriage requires an unlocking actuator to neutralize the strut lock, and a maneuvering actuator to bring the leg back to the retracted position. Arrangements of the operating actuator are also known which allow it to ensure both the neutralization of the locking member and the raising of the leg to the retracted position, which makes it possible to eliminate
    The unlocking actuator. In the case of a breaker strut, such an arrangement leads to coupling the operating actuator to one of the arms of the stabilization member, which leads to kinematically complex solutions.
    OBJECT OF THE INVENTION
    The invention aims to propose an aircraft undercarriage with simplified bracing.
    PRESENTATION OF THE INVENTION
    With a view to achieving this goal, an aircraft undercarriage is provided comprising a leg carrying at least one wheel and intended to be movably mounted on an aircraft structure between a deployed position and a retracted position,
    The undercarriage comprising a bracing member disposed between the structure of the aircraft and the leg to stabilize the latter in the deployed position, and a maneuver actuator for moving the leg from the deployed position to the retracted position. According to the invention, the bracing member comprises an arm having a proximal end intended to be articulated on the structure of the aircraft, the arm having a longitudinal lumen extending to a distal end to end in a reference and in which a finger secured to the leg is slidably engaged, the operating actuator being coupled to said strut arm.
    Thus, the stabilization of the leg in the deployed position is ensured by the engagement of the finger of the leg in the return of the lumen of the arm of
    The bracing member.
    The action of the operating actuator on the arm of the bracing member first of all causes the finger of the reference to come out thus unlocking the leg, then the ascent of the leg by sliding of the finger in the light.
    DESCRIPTION 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 appended drawings, among which:
    - Figure 1 is a perspective view of an aircraft undercarriage according to the invention, shown in the deployed position;
    - Figure 2 is a perspective view of the undercarriage of Figure 1, shown during lifting to the retracted position;
    - Figure 3 is a perspective view of the undercarriage of Figure 1, shown in the retracted position;
    - Figures 4A to 4E are partial schematic views of the strut arm and part of the leg of the undercarriage during a lifting phase.
    DETAILED DESCRIPTION OF THE INVENTION
    FIG. 1 illustrates an aircraft undercarriage comprising a leg 1 carrying wheels 2 in its lower part and articulated in the upper part on a structure 3 of the aircraft along an axis of articulation XI. The leg is movable in rotation around said axis of articulation between a deployed position illustrated in FIG. 1 and a retracted position illustrated in FIG. 3. The leg 1 comprises a structure 4 made of two supports 5 and 6 attached to the leg 1 to form a pyramid which carries at its apex a finger 7 extending along an axis X2 parallel to the axis of articulation XI.
    The undercarriage also comprises a strut arm 10 having a proximal end articulated on the structure of the aircraft along an axis of articulation X3 parallel to the axis of articulation XI, and the distal part of which is hollowed out at its center. to leave two parallel flanks 11 extending substantially along a plane normal to the axis of articulation X3 and each comprising a longitudinal lumen 12 oriented substantially in a direction concurrent with the axis of articulation
    X3. Each lumen is terminated by a reference 13 extending substantially perpendicular to the rest of the lumen 12. The apex of the structure 4 of the leg 1 extends between the parallel sides 11 and the finger 7 is engaged in the lumens 12. Thus, the strut arm 10 and the leg 1 are kinematically connected by a sliding connection of the finger 7 in the slots 12. The respective rotations of the strut arm 10 and of the leg 1 are therefore linked. Finally, a maneuver actuator 20, here a jack, is coupled to the strut arm 10.
    The raising of the undercarriage is now explained with reference to FIGS. 4A to 4E. In the deployed position illustrated in FIG. 4A (also in FIG. 1), it is visible that the finger 7 is kept engaged at the bottom of the reference 13, thus preventing the leg 1 from pivoting about the articulation axis XI, which therefore has the effect of bracing and therefore stabilizing the leg 1 in the deployed position. This holding of the finger 7 at the bottom of the reference 13 ensures the locking of the leg 1 in the deployed position and can be ensured by the operating actuator 20 which remains activated to confirm the finger 7 at the bottom of the reference 13, or by any spring member acting on the strut arm 10 to maintain the latter in the position illustrated in FIG. 4A. To raise the leg 1, and as illustrated in FIG. 4B, the operating actuator 20 is activated to pull on the strut arm 10 and rotate it (in the direction of the arrow), which has for first effect of removing the finger 7 from the reference 13. The leg 1 is then unlocked and can pivot around its axis of articulation XI. Continuing the rotation of the strut arm 10 under the action of the operating actuator 20, the finger 7 engages in the slots 12 as illustrated in FIG. 4C, thus initiating the lifting of the leg 1 towards its retracted position. Then the finger 7 slides in the slots 12 until a maximum excursion illustrated in FIG. 4D which occurs when the slots 12 converge towards the articulation axis XI of the leg 1. The rotation of the strut arm 10 continuing, the leg 1 continues its race towards the retracted position, but the finger 7 now starts again in the direction of the reference 13, until one of the ends of the finger 7 projecting from one of the lights 12 is hooked by a locking hook 30 integral with the structure of the aircraft. The leg 1 is then immobilized in the retracted position. The finger therefore performs a double sliding linkage function with the strut arm and attachment member for locking the leg in the retracted position.
    To lower the leg 1 to the deployed position, it suffices to order the hook 30 so that it releases the finger 7. The leg 1 then descends under the effect of its own weight and aerodynamic forces, the actuator lifting 20 which can be used to regulate the speed of descent of the leg 1. The leg descends by itself to the deployed position in which the finger 7 engages automatically at the bottom of the return 13. The leg is then locked in the deployed position. A spring member (not shown here) acts on the strut arm 10 so that the finger 7 remains engaged in the bottom of the reference 13, which has the effect of confirming the locking of the leg 1 in the deployed position.
    The invention is not limited to what has just been described but on the contrary encompasses any variant coming within the scope defined by the claims. In particular, a lander has been shown here, the leg and the bracing member of which are articulated on the structure of the aircraft along parallel axes of articulation. More generally, the invention applies to a lander whose leg is movable between a deployed position and a retracted position, and whose bracing member is linked in its movement to that of the leg by sliding a leg finger in a lumen of the brace. In addition, although here the lights are carried by parallel sides so that the finger-carrying structure extends between the sides of other known forms of light / finger connection can be used, such as for example a central light s extending between two supports of the leg carrying the finger. This could possibly be split into two parts.
    Although here the light is essentially straight, the light can take other configurations to facilitate the ascent of the leg. However, it is important that the light is terminated by a reference capable of providing a leg lock at least in the deployed position.
    Although here the finger also serves to lock the leg in the retracted position, this locking can be ensured by other means, for example by a hooking olive secured to the leg or the strut arm which is hooked by a hook when the leg reaches the retracted position.
    Finally although here the operating actuator illustrated is a linear actuator coupled to the bracing member r we can use any other type of operating actuator, such as a rotary electromechanical actuator disposed on the articulation of the bracing.
    权利要求:
    Claims (4)
    [1" id="c-fr-0001]
    1. aircraft undercarriage comprising a leg (1) carrying at least one wheel (2) and intended to be movably mounted on an aircraft structure between a deployed position and a retracted position, the undercarriage comprising a bracing member ( 10) disposed between the structure of the aircraft and the leg to stabilize the latter in the deployed position, and a maneuver actuator (20) for moving the leg from the deployed position to the retracted position, characterized in that the member brace comprises a strut arm (10) having a proximal end intended to be articulated on the structure of the aircraft, the arm having a longitudinal lumen (12) extending to a distal end and ending in a reference (13) and in which a finger (7) integral with the leg is slidably engaged, the operating actuator being coupled to said strut arm.
    [2" id="c-fr-0002]
    2. aircraft undercarriage according to claim 1, wherein the leg (1) and the strut arm (10) are articulated on the structure of the aircraft along parallel axes of articulation (XI, X3).
    [3" id="c-fr-0003]
    3. Landing gear according to claim 1, wherein the finger (7) forms a hooking member for a hook holding the leg in the retracted position.
    1/4
    2/4
    3/4
    Fig. 3
    [4" id="c-fr-0004]
    4/4
    FRENCH REPUBLIC irai - I NATIONAL INSTITUTE
    PROPERTY
    INDUSTRIAL
    PRELIMINARY SEARCH REPORT based on the latest claims filed before the start of the search
    National registration number
    FA 848921
    FR 1850904
    EPO FORM 1503 12.99 (P04C14)
    DOCUMENTS CONSIDERED AS RELEVANT Relevant claim (s) Classification attributed to the invention by ΙΊΝΡΙ Category Citation of the document with indication, if necessary, of the relevant parts ATATAT W0 2010/139756 Al (MESSIER DOWTY SA [FR]; KELLER NICOLAS [FR]; DE PINDRAY ALBERT [FR]; CA) December 9, 2010 (2010-12-09)* pages 2-7; figures 1-5 *EP 1 988 015 Al (MESSIER DOWTY SA [FR])November 5, 2008 (2008-11-05)* pages 2-3; figures 1-3 *FR 2 928 623 Al (MESSIER DOWTY SA SA [FR]) September 18, 2009 (2009-09-18)* pages 4-7; figures 1-3 * 1-31-31-3 B64C25 / 26B64C25 / 10 TECHNICAL AREAS SOUGHT (IPC) B64C Research Completion Date ExaminerMay 18, 2018 Carlier, François CATEGORY OF DOCUMENTS CITED T: theory or principle underlying the inventionE: patent document with an earlier date X: particularly relevant on its own at the filing date and which was not published until that dateY: particularly relevant in combination with a deposit or at a later date.other document of the same category D; cited in requestA: technological background L: cited for other reasonsO: unwritten disclosureP: interlayer document &: member of the same family, corresponding document
    ANNEX TO THE PRELIMINARY RESEARCH REPORT
    RELATING TO THE FRENCH PATENT APPLICATION NO. FR 1850904 FA 848921
    EPO FORM P0465
    This appendix indicates the members of the patent family relating to the patent documents cited in the preliminary search report referred to above.
    The said members are contained in the computer file of the European Patent Office on the date dulo - üb - 2ülo
    The information provided is given for information only and does not engage the responsibility of the European Patent Office or the French Administration
    Patent document cited in the research report Publication date Patent family member (s) Publication date wo 2010139756 al 09-12-2010 BR PI 1012895 A2 13 03-2018 IT 2764219 al 09 12-2010 CN 102448821 AT 09 05-2012 EP 2437978 al 11 04-2012 FR 2946319 al 10 12-2010 JP 5457551 B2 02 04-2014 JP 2012528759 AT 15 11-2012 UK 2011153325 AT 20 07-2013 US 2012080559 al 05 04-2012 WO 2010139756 al 09 12-2010 EP 1988015 al 05-11-2008 AT 497465 T 15 02-2011 IT 2630110 al 03 11-2008 EP 1988015 al 05 11-2008 ES 2360477 T3 06 06-2011 FR 2915731 al 07 11-2008 HE 191116 AT 30 11-2011 US 2009057485 al 05 03-2009 FR 2928623 al 18-09-2009 AT 526236 T 15 10-2011 BR PI0909704 A2 06 10-2015 IT 2717944 al 24 09-2009 CN 101970295 AT 09 02-2011 EP 2265493 A2 29 12-2010 ES 2371821 T3 10 01-2012 FR 2928623 al 18 09-2009 JP 5276127 B2 28 08-2013 JP 2011513138 AT 28 04-2011 UK 2010142009 AT 20 04-2012 US 2011163202 al 07 07-2011 WO 2009115713 A2 24 09-2009
    For any information concerning this annex: see Official Journal of the European Patent Office, No.12 / 82
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20190241256A1|2019-08-08|
    CA3031825C|2020-07-14|
    EP3521159A1|2019-08-07|
    EP3521159B1|2020-09-16|
    CN110127039A|2019-08-16|
    CA3031825A1|2019-08-02|
    US11142305B2|2021-10-12|
    FR3077557B1|2020-02-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1988015A1|2007-05-03|2008-11-05|Messier-Dowty SA|Bracing locking device for an aircraft landing gear|
    FR2928623A1|2008-03-14|2009-09-18|Messier Dowty Sa Sa|UNLOCKING AN AIRCRAFT AIRCRAFT BREAKER STABILIZATION BODY|
    WO2010139756A1|2009-06-05|2010-12-09|Messier-Dowty Sa|Method for operating a landing gear assembly with a breaker strut|
    GB463739A|1935-11-04|1937-04-06|Bristol Aeroplane Co Ltd|Improvements in retractable landing gear or the like for aircraft|
    GB518020A|1938-08-06|1940-02-15|Stone J & Co Ltd|Improvements in retractible undercarriages for aircraft|
    US2355210A|1940-10-02|1944-08-08|Brewster Aeronautical Corp|Airplane retractible tail wheel or skid mount|
    GB628324A|1946-03-07|1949-08-26|Morane Saulnier Sa|Retractable landing gear for aircraft|
    US2661171A|1951-10-11|1953-12-01|Glenn L Martin Co|Up and down lock mechanism for retractable landing gear for aircraft|
    GB806024A|1956-05-02|1958-12-17|British Messier Ltd|Improvements in or relating to aircraft undercarriages|
    GB2161202A|1984-07-05|1986-01-08|Dowty Rotol Ltd|Locking means for retractable devices|
    GB0511417D0|2005-06-03|2005-07-13|Airbus Uk Ltd|Landing gear|
    US20150203192A1|2013-05-02|2015-07-23|Goodrich Corporation|System and method for spring assisted landing gear operation|
    FR3015427B1|2013-12-19|2016-01-29|Airbus Operations Sas|LANDING TRAIN FOR AN AIRCRAFT|
    EP3135581B1|2015-08-25|2018-03-21|Safran Landing Systems UK Limited|Aircraft landing gear assembly|
    US10124884B2|2015-10-09|2018-11-13|Goodrich Aerospace Services Private Limited|Powerless self operated landing gear uplock system|US11230370B2|2019-01-23|2022-01-25|Goodrich Corporation|Upper side stay with monolithic unlock actuator|
    CN111470034B|2020-04-29|2021-09-07|江苏工程职业技术学院|Linkage mechanism of follow-up switch of landing gear cabin door of airplane|
    US20210362841A1|2020-05-21|2021-11-25|The Boeing Company|Nose landing gear assembly for use with an aircraft|
    法律状态:
    2019-01-23| PLFP| Fee payment|Year of fee payment: 2 |
    2019-08-09| PLSC| Publication of the preliminary search report|Effective date: 20190809 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 3 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 4 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1850904|2018-02-02|
    FR1850904A|FR3077557B1|2018-02-02|2018-02-02|LIGHT COUNTERFEIT LANDER|FR1850904A| FR3077557B1|2018-02-02|2018-02-02|LIGHT COUNTERFEIT LANDER|
    CA3031825A| CA3031825C|2018-02-02|2019-01-28|Landing gear with lighted brace|
    CN201910090807.1A| CN110127039A|2018-02-02|2019-01-30|Has the undercarriage of slotted strut|
    US16/265,041| US11142305B2|2018-02-02|2019-02-01|Undercarriage having a slotted strut|
    EP19155150.6A| EP3521159B1|2018-02-02|2019-02-01|Landing gear with brace with light|
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