• 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:
    A method of locking an aircraft movable member (101) such as a cargo hatch or landing gear, wherein the movable member is moved between an extended position and a closed or retracted position by means of a actuator (200) having a sliding rod (3) coupled to the movable member, the rod being slidably mounted in a body (1) of the actuator between an extended position corresponding to the deployed position of the movable member and a position retraction corresponding to the closed or retracted position of the movable element. The method of the invention comprises the step of positively locking the sliding rod of the actuator in the retracted position.
    公开号:FR3019523A1
    申请号:FR1453122
    申请日:2014-04-08
    公开日:2015-10-09
    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 the manner in which aircraft bunkers, in particular hatches closing the bunkers of the undercarriages, are operated and kept closed, but also in the manner in which the undercarriages are maneuvered and held in the retracted position in their hold. . BACKGROUND OF THE INVENTION On an aircraft whose landing gear is movable between an extended position and a retracted position in which they are received in respective bunkers, there are two types of hatches closing said bunkers: the traps coupled to the bolster landing gear, which move in concert with said undercarriage and which close when the landing gear arrives in the retracted position, and the independent hatches which are not coupled to the undercarriage, whose movement is independent of that of the undercarriage. The hitched hatches do not need an actuator, since they are maneuvered directly by the undercarriage, while the independent doors require a dedicated actuator. In flight, the landing gear is held in the retracted position by means of a locking hook adapted to hook an olive fixed to the undercarriage. The hatch or hatches coupled to this undercarriage are therefore also maintained in the closed position. On the other hand, the independent hatches must be kept in the closed position by dedicated locking hooks adapted to pick olives integral with the independent hatches. It is often difficult to hook all hatches to the undercarriage. Indeed, some hatches must be able to close while the undercarriage is in the deployed position, to minimize aerodynamic disturbances due to air rushing into the cargo hold.
    [0002] In this case, it is appropriate to associate a specific actuator and locking hook, which multiplies the interfaces between the hatch and the structure of the aircraft, not to mention the multitude of electrical or hydraulic connections to control the actuator and the locking hook. Regarding the undercarriages, it is also necessary to ensure their maneuver and their retention in the retracted position, which also requires a locking hook in the retracted position. OBJECT OF THE INVENTION The object of the invention is to propose a method of locking a hatch or undercarriage in the closed or retracted position.
    [0003] PRESENTATION OF THE INVENTION With a view to achieving this object, a locking method is proposed for an aircraft moving element such as a hatch or undercarriage, the movable element being moved between an extended position and a closed position. or retracted by means of an actuator having a sliding rod coupled to the movable member, the rod being slidably mounted in a body of the actuator between an extended position corresponding to the deployed position of the movable member and a corresponding retracted position in the closed or retracted position of the movable element. According to the invention, the locking method of the movable element in the closed or retracted position comprises the step of positively locking the sliding rod of the actuator in the retracted position. Thus, the locking of the movable element is obtained by blocking the sliding rod of the actuator in the retracted position, which avoids the use of an external locking hook.
    [0004] According to a particular mode of implementation adapted to selectively block an element of a kinematic chain between a drive member of the sliding rod and the sliding rod. It should be noted that the electromechanical actuators usually proposed for operating hatches or undercarriages generally comprise a back-up control enabling the sliding rod to be released axially in order to allow the sliding of the latter to slide freely, for example in the event of engine failure. actuator or seizure of the driveline linking the engine to the rod. By integrating according to the invention the locking of the movable element in the closed position directly in the actuator, it is unnecessary to provide a specific emergency oc-mand that would mitigate the failure of the internal lock, since the possibility of release of the rod already existing then takes place. It is thus possible to provide a hatch actuator / locker, having a backup operation adapted to overcome the failure of the maneuver or lock. Preferably, the telescopic actuator for carrying out the method comprises - a body comprising means for coupling it to a first external element; a rod mounted to slide telescopically in the body along a sliding axis and comprising means for coupling it to a second external element; - A mother screw rotatably mounted on the body 30 around the sliding axis and extending inside the rod to cooperate with a nut secured to the rod, so that a rotation of the lead screw causes a sliding of the rod; - Drive means for rotating the lead screw; - Axial retaining means of the lead screw which axially retain a bearing of the lead screw, said axial retaining means being cornmandables to axially release the lead screw and thus allow the free sliding of the sliding rod in the body; a positive locking member for selectively locking the lead screw in rotation and thus ensuring the locking of the actuator in position.
    [0005] According to a particular embodiment, the drive means of the telescopic actuator comprise: a shaft of non-circular section, preferably a splined shaft (7) rotatably mounted on the body about the sliding axis and extending inside the screw for rotating the latter by a splined connection; - a drive member (9) for rotating the splined shaft; and wherein the axial retaining means (20) is operable to selectively release a bearing (11) from the lead screw. BRIEF DESCRIPTION OF THE FIGURES The invention will be better understood in the light of the following description with reference to the figures of the attached drawings, in which: FIG. 1 is a perspective view of a landing gear bunker of an aircraft, showing one of the traps of the hold equipped with an actuator according to the invention; FIG. 2 is a longitudinal section of an actuator according to a particular embodiment of the invention.
    [0006] DETAILED DESCRIPTION OF THE FIGURES In FIG. 1 is illustrated an aircraft undercarriage 100 in the deployed position. In flight, the undercarriage is normally retracted in its hold closed by doors 101. The hatches comprise hinges 102 gooseneck for their articulation on the structure of the aircraft. Each of the hatches 101 is associated with an actuator 200 which will be detailed later and which allows the operation of the hatch between an open position, illustrated here, and a desired position. Each actuator is coupled on the one hand to the structure of the aircraft, and on the other hand to the associated hatch. It will be noted that the hatch has no hooking hook, and no hook is provided for hooking the hatch when it is brought back into closed position by the actuator 200, according to the invention. Referring now to Figure 2, and in accordance with a particular embodiment of the invention, the actuator 200 comprises: - a body 1 carrying at one of its ends a clevis 2 provided with a ball joint for its coupling an external element, for example the structure of the aircraft, the other end of the body being open; - A rod 3 mounted to telescopically slide in the body along the axis of sliding X, and carrying at its end a yoke 4 carrying a ball joint for coupling to a second outer member, here one of the hatches 101; - A mother screw 5 extending inside the rod 3 and which cooperates with it by a helical connection by means of a nut 6 integral with the rod 3 which forms a bearing of the rod and which and engaged on an external thread of the mother screw 5, so that a rotation of the mother screw 5 causes a sliding of the rod 3; a shaft with a non-circular section, for example a splined shaft 7 which extends inside the mother screw 5 and which cooperates with it by a prismatic connection by means of grooves 8 (shown here in part, but extending over the entire length of the splined shaft 7 cooperating with flutes homologous to the mother screw 5 - a motor 9 adapted to drive a toothed wheel 7a integral with the spline shaft 7 to drive the latter in rotation by the intermediate of a reduction stage 9a, said rotation of the splined shaft 7 causing rotation of the lead screw 5. The lead screw 5 has an end bearing a bearing 11 which forms the outer cage of a ball bearing 12 and which is retained axially in the body 1 by means of retaining means 20, here of the claw type, It will be recalled for the record that this type of retaining means comprises a ferrule in which claws having hooked ends 23 are cut out and may bend ra In the illustrated situation, the bearing 11 is trapped by the claws 20, the latter being prevented from flexing by means of the claw 20. a rotating sleeve 24 which carries on its internal face a succession of balls 25 arranged circumferentially opposite the ends of the claws and separated from each other by spaces.
    [0007] When the sleeve 24 is placed in a first angular locking position (as illustrated here) in which the balls 25 are directly opposite the ends 23 of the claws 20, the claws 20 are prevented from bending, and the bearing 11 is held prisoner by the claws 20. When the sleeve 24 is placed in a second angular position of release in which the spaces between the balls 25 are brought facing the ends 23 of the claws 20, they can bend radially, and the bearing can, under the effect of a pull on the rod 3, escape from the claws 20 to thereby allow a sliding of the lead screw driven by the rod 3. To move the sleeve 24 from the locking position to the release position, the sleeve is here secured to a lever 26 which is operated by an eccentric 27 itself actuated by a motor 28. The rotation of the motor 28 causes the rotation of the eccentric 27, and therefore the rocking lever 26 which drives the sleeve 24 in rotation.
    [0008] In an emergency, for example in case of failure of the engine 9 or in case of seizure of the drive train linking the motor to the sliding rod, it is then possible by turning the sleeve 24 to release the bearing 11 and so allow the mother screw 5 to move with the rod 3 under an external action (for example the landing gear pushing on the door hitched to the rod). Such an arrangement ensures the free sliding of the rod 3 even if the motor 9 is faulty or no longer supplied.
    [0009] According to the invention, the actuator 200 is equipped with positive locking means of the sliding rod. Here, these means comprise a wheel 30 secured to the spline shaft 7 having peripheral notches 31 in which a finger 32 actuated by an electromagnet 33 is housed to lock the wheel 30 in rotation, which has the effect of blocking the blade angularly. splined shaft, and thus axially locking the sliding rod 3. Advantageously, when closing the hatch, the motor 9 is energized to cause the retraction of the sliding rod 3, and thus the closing of the hatch. When the latter comes into abutment, a sensor generates a signal triggering the actuation of the finger 32. The assembly is adjusted so that no notch 31 is facing the finger when the door reaches the stop. The motor 9 must then continue to rotate to bring the nearest notch under the finger 32, which induces a preload in the hatch before it is locked in position by locking the sliding rod 3 in the retracted position . If the finger 32 could never be retracted, following a failure of the electromagnet 33, it remains the resource to control the axial retaining means 20 to release the bearing 11, which allows the free sliding of the sliding rod 3. The door 101 can then open, for example under the thrust of the wheels of the undercarriage 100 which unfolds. The invention is not limited to what has just been described, but on the contrary covers any variant within the scope defined by the claims. In particular, although here the retaining member controllable to selectively release the bearing of the lead screw is of the claw type, it will be possible to use other retaining members, such as for example a finger or segment retaining member. retractable. Similarly, although the positive blocking member of the sliding rod in position is here of the finger type entering into the notches of a wheel, it will be possible to use other types of positive locking member, such as for example a dog. Finally, the actuator and the method of the invention also apply to the operation of a landing gear and its retention in the retracted position, and more generally to any movable member of a mobile aircraft between an extended position and a retracted position. lockable.
    权利要求:
    Claims (5)
    [0001]
    REVENDICATIONS1. A method of locking an aircraft movable member (101) such as a cargo hatch or undercarriage, the movable member being moved between an extended position and a closed or retracted position by an actuator (200) having a sliding rod (3) coupled to the movable element, the rod being slidably mounted in a body (1) of the actuator between an extended position corresponding to the deployed position of the movable element and a retracted position corresponding to the position closed or retracted of the movable element, characterized in that it comprises the step of positively locking the sliding rod of the actuator in the retracted position.
    [0002]
    2. The method of claim 1, wherein the actuator is controlled to install a preload in the movable member while the latter is in the closed or retracted position before locking the sliding rod in position.
    [0003]
    3. Telescopic actuator specially adapted to the implementation of the method according to one of the preceding claims, comprising: - a body (1) having means of its coupling (2) a first outer member; - A rod (3) telescopically sliding in the body according to a sliding axis (X) and having means of its coupling (4) to a second outer member; - A mother screw (5) rotatably mounted on the body about the sliding axis and extending inside the rod to cooperate with a nut (6) integral with the rod, so that a rotation of the mother screw causes a sliding of the rod; - Rotational drive means (7, 9) of the mother screw (5); - Axial retaining means (20) of the lead screw, said axial retaining means being controllable to axially release the lead screw and thus allow free sliding of the sliding rod in the body; a positive locking member (30; 31; 32) for selectively locking the lead screw in rotation and thus ensuring the locking of the actuator in position.
    [0004]
    4. telescopic actuator according to claim 3, wherein the drive means in rotation of the lead screw comprise: a shaft of non-circular section, preferably a splined shaft (7) rotatably mounted on the body around the axis of sliding and extending inside the screw to drive the latter in rotation by a splined connection; - a drive member (9) for rotating the splined shaft; and wherein the axial retaining means (20) is controllable to selectively release a bearing (11) from the lead screw.
    [0005]
    5. Telescopic actuator according to claim 4, wherein the positive locking member comprises a finger (32) operable to angularly lock a wheel (30) integral with the spline shaft (7).
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3019523B1|2018-02-02|
    EP2930104B1|2016-09-28|
    US20150285350A1|2015-10-08|
    EP2930104A1|2015-10-14|
    CN104973239A|2015-10-14|
    CN104973239B|2017-07-18|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB2428457A|2005-07-19|2007-01-31|Titan Holdings Ltd|A self-locking screw actuator driven by a hydraulic / pneumatic motor|
    EP2107273A2|2008-04-03|2009-10-07|Goodrich Actuation Systems Limited|Actuator|
    US3053104A|1959-08-06|1962-09-11|Creusot Forges Ateliers|Device for producing regulated rectilinear movements|
    FR2895483B1|2005-12-23|2008-10-24|Messier Bugatti Sa|TELESCOPIC ACTUATOR WITH MAIN ROD AND AUXILIARY ROD, AND METHOD USING THE SAME|
    GB0604520D0|2006-03-07|2006-04-12|Smiths Group Plc|Actuators|
    ITTO20060706A1|2006-10-02|2008-04-03|Arol Spa|"HEAD OF SCREWING AND ROLLING FOR THE APPLICATION OF PRE-THREADED CAPS"|
    FR2913080B1|2007-02-22|2009-04-03|Aircelle Sa|VERIN WITH INTEGRATED LOCKING DEVICE|
    US7533591B2|2007-03-03|2009-05-19|T-Motion Technology Co., Ltd.|Fast-releasing controlling device of actuator for electric sickbed|
    FR2921976B1|2007-10-08|2009-12-04|Aircelle Sa|ACTUATOR FOR MOBILE STRUCTURE OF AN AIRCRAFT NACELLE, AND NACELLE COMPRISING AT LEAST ONE ACTUATOR|
    EP2141311B1|2008-07-02|2012-12-05|Ojmar S.A.|Electronic blocking module for closing systems|
    FR2946319B1|2009-06-05|2012-11-30|Messier Dowty Sa|METHOD FOR MANEUVERING A BREAKER COUNTERFRAME|
    FR2968375B1|2010-12-06|2013-08-02|Messier Bugatti|ELECTROMECHANICAL TELESCOPIC ACTUATOR.|
    US8733192B2|2011-03-11|2014-05-27|Timotion Technology Co., Ltd.|High-load linear actuator|
    FR2981910B1|2011-10-26|2013-12-27|Eurocopter France|LANDFILL, AIRCRAFT AND METHOD|
    US8794087B2|2012-06-08|2014-08-05|Timotion Technology Co., Ltd.|Gear motor having safety mechanism|
    TWM459317U|2013-03-28|2013-08-11|Timotion Technology Co Ltd|Linear transmission device with double screws|
    TWI550214B|2014-06-27|2016-09-21|第一傳動科技股份有限公司|Linear actuator and cushion mechanism for the same|
    JP6374782B2|2014-12-12|2018-08-15|株式会社ショーワ|Steering device for vehicle|
    WO2016134746A1|2015-02-24|2016-09-01|Schukra Gerätebau Gmbh|Actuator and method of actuating a latch|
    DE102015104111A1|2015-03-19|2016-09-22|Witte Automotive Gmbh|Drive mechanism with twin worm gear|CN107521670B|2017-07-28|2020-06-16|中国航空工业集团公司西安飞机设计研究所|Truss type main landing gear butt-joint frame|
    CN109723314A|2017-10-30|2019-05-07|北京精密机电控制设备研究所|A kind of airplane cargo doors electro-mechanical driving device based on FPGA control|
    CN107878734B|2017-11-10|2020-10-09|中国航空工业集团公司西安飞机设计研究所|Double-channel steel cable mechanism and aircraft landing gear cabin door with same|
    CN108116666A|2017-11-28|2018-06-05|北京特种机械研究所|The reliable locking method of electric retractable actuating cylinder|
    CN109292078B|2018-11-21|2020-09-29|周纯|Aircraft landing gear assembly of anti low energy damage of new forms of energy|
    法律状态:
    2016-04-21| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-19| 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 |
    2018-04-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1453122|2014-04-08|
    FR1453122A|FR3019523B1|2014-04-08|2014-04-08|METHOD FOR OPERATING AIRCRAFT SAIL TRAPPERS, AND ACTUATOR APPLYING THE SAME|FR1453122A| FR3019523B1|2014-04-08|2014-04-08|METHOD FOR OPERATING AIRCRAFT SAIL TRAPPERS, AND ACTUATOR APPLYING THE SAME|
    EP15160646.4A| EP2930104B1|2014-04-08|2015-03-24|Method for manoeuvring doors of bays of aircraft, and actuator used therefor|
    US14/670,586| US20150285350A1|2014-04-08|2015-03-27|Method for maneuvering doors of bays of aircraft, and actuator used therefor|
    CN201510160914.9A| CN104973239B|2014-04-08|2015-04-07|Method and its actuator used for operating aircraft cabin door|
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