• 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 concomitant opening or closing device for two flaps (1,1 ') of a hatch of a landing gear coming from an aircraft, as well as on an aircraft equipped with such a device . This device comprises a single actuating means (2) for opening or closing the two flaps (1,1 '), under the effect of its elongation or retraction. The actuating means (2) comprises a first end (21) linked to the structure of the aircraft, and a movable part (23). The device comprises an oscillating arm (5) having a first end (51) connected by a pivot to the structure, and a second end (52) connected to the movable part of the actuating means by a link having a degree of freedom in rotation along an axis parallel to the axis of the pivot (P1). The second end (52) of the oscillating arm (5) is further connected respectively to a first tie rod (3) connected to a first of the two flaps, and a second tie rod (3 ') connected to a second of the two flaps.
    公开号:FR3014836A1
    申请号:FR1362712
    申请日:2013-12-16
    公开日:2015-06-19
    发明作者:Didier Reynes；Jerome Phalippou
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a device for opening or closing concomitant two flaps of a landing gear entering the aircraft. It relates more particularly to a device that can be implemented to ensure the opening or closing of a hatch of a landing gear having two flaps, as commonly used for the front landing gear of an aircraft. The landing gear returning aircraft are, in a conventional manner, retractable in a volume that can be closed in flight by one or more shutters forming a hatch. It is known to operate the shutters, for opening or closing, using actuating means, such as hydraulic cylinders. It can be provided a cylinder by shutter. Nevertheless, this solution entails, for the opening of two flaps, in particular two constituent flaps of a flap with two flaps, the doubling of a certain number of parts, insofar as two jacks are necessary, as well as two mechanisms of associated opening / closing. This results in a certain mechanical complexity, and a large mass. In addition, each cylinder being typically linked to the structure of the aircraft on each side of the latter, substantially perpendicular to the axis of tilting of each of the flaps, the lever arm between the point of application of a force by the cylinder and the axis of rotation of the flap is weak. This requires the use of heavy section cylinders, so heavy, and causes significant efforts in the structure of the aircraft. Two-way hatches actuated by a single jack are also known. This is commonly the case for the hatches landing gear located at the nose of the aircraft. In known devices comprising a single actuating cylinder of the door, two tie rods are connected to the flaps, and are connected to one another at a pivot point. This pivot point is usually located at the end of a transverse arm. The other end of the transverse arm is connected to the structure of the aircraft. The raising or lowering of the pivot point, under the effect of a cylinder connected to the transverse arm on the one hand, and the structure of the aircraft on the other hand, causes the opening or closing of the shutters of the hatch. In known devices, such a device implements two zones of introduction of forces into the structure of the aircraft, on the one hand at a connection between the jack and the structure, and on the other hand at the level of the connection, typically in pivot, between the transverse arm and the structure. In addition, the introduction of transverse forces in an aircraft is not desirable, especially if they are not taken directly by a central beam of the aircraft. The known devices are therefore bulky, have a complex kinematic, and / or cause a recovery efforts in at least two points of the aircraft structure that must be reinforced. The object of the present invention is to propose a device for opening or closing two flaps of an aircraft landing gear flap, optimized as to its constitution and to the forces transmitted to the structure of the aircraft. To this end, according to a first aspect of the invention, provision is made for a concomitant opening or closing device for two flaps of a hatch of an aircraft landing gear, the two flaps pivoting around two substantially parallel longitudinal pivoting axes defining a closure plane of the flaps, the device comprising a single actuating means able to open and close the flaps by changing its length, the actuating means comprising a fixed end connected to a point of resumption of efforts to the structure of the aircraft, the actuating means further comprising a movable portion, the device comprising an oscillating arm having a first end connected by a first connection to the structure, and a second end connected by a second connection to the movable portion of the actuating means, the first link being a pivot and the second link having a degree of freedom along a parallel axis to the axis of the pivot, the device being configured so that said second end of the oscillating arm moves away from or approaches the closure plane PF of the flaps during the extension or retraction of the actuating means, the second end of the swingarm being further linked respectively to a first tie linked to a first of the two flaps, and a second tie linked to a second of the two flaps. Such a device has a simple kinematics, and can be compact and lightweight. It also makes it possible to report all or almost all the mechanical forces generated during the opening or closing of a landing gear flap at a single point of recovery of forces by the structure of the aircraft considered that is the point of connection between the fixed end of the actuating means and the structure to which it is connected.
    [0002] In a first embodiment, the movable portion of the actuating means may be advantageously connected to the swinging arm by a universal joint. According to the actuating means in question, this makes it possible to bind the movable part to the tie rods at a point other than the end of said movable part, which makes it possible to use shorter and therefore lighter and / or more resistant tie rods. In a second embodiment, the movable portion of the actuating means comprises a movable end connected to the oscillating arm. A pivot link can be provided for this purpose. This second embodiment allows the use of a simple connection between the oscillating arm and the actuating means, but requires the use of longer tie rods than in the first embodiment. The actuating means may be a jack. When the link between the oscillating arm and the actuating means is formed by a universal joint, the body of the jack advantageously constitutes the movable part of the actuating means.
    [0003] The device is advantageously symmetrical on both sides of a longitudinal plane, orthogonal to the closure plane. This allows a good distribution of forces in the device, and also avoids the generation and transmission of transverse forces in the structure of an aircraft equipped with the device.
    [0004] Each tie may be linked to a flap at a distance from its pivot axis. Thus, the approximation or removal of the second end of the swing arm relative to the closure plane of the flaps causes the pivoting of the flap. Advantageously, each tie is linked to a flap by a ball joint.
    [0005] In one embodiment of the invention, each flap comprises a panel and an actuating part rigidly connected to the panel, the tie rod being connected to the actuating part. According to a first variant of the invention, an extension of the actuating means causes the shutters to close.
    [0006] According to a second variant of the invention, an extension of the actuating means causes the flaps to open. According to a second aspect of the invention, the invention also relates to an aircraft comprising a concomitant opening or closing device for two flaps of a landing gear that it comprises according to the first aspect of the invention. In such an aircraft, the actuating means is advantageously linked to the structure of the aircraft so that the vertical component of the forces generated during the opening or closing of the hatch is entirely taken up at the recovery point of the aircraft. effort by the structure. The point of recovery efforts can be located on a structural cross member of the fuselage. The point of recovery efforts can be located at a lock housing of the hatch. Other features and advantages of the invention will become apparent in the description below. In the accompanying drawings, given by way of non-limiting examples: FIG. 1 is a diagrammatic perspective view of the front part of an aircraft comprising a retracting landing gear; - Figure 2 shows schematically in perspective a device for opening and closing a hatch of an aircraft landing gear and its immediate environment, as known in the state of the art; - Figure 3 shows schematically a device for opening and closing a hatch of a landing gear entering the aircraft and its immediate environment according to a first embodiment of the invention, the hatch being open; - Figure 4 shows schematically the device shown in Figure 3, according to the same view, the hatch being closed; FIG. 5 shows a detailed view of the device shown in FIGS. 3 and 4. FIG. 6 shows, in a view similar to that of FIGS. 3 and 4, a device for opening and closing a trapdoor of a aircraft landing gear and its immediate environment according to a second embodiment of the invention, the hatch being open; - Figure 7 schematically shows the device shown in Figure 6, according to the same view, the hatch being closed. FIG. 1 and FIG. 3 shows, for better readability, an orthogonal reference (x, y, z), in which: the axis (x) corresponds to a direction parallel to the main longitudinal axis the aircraft, typically an elongated fuselage of an aircraft, said axis corresponding to an axis between the front (nose) and the rear (tail) of the aircraft, generally substantially horizontal the aircraft being placed; - The axis (y) is a transverse axis, orthogonal to the axis (x) generally also horizontal and typically parallel to the plane of the wings of the aircraft; - The axis (z), orthogonal to (x) and (y), is generally substantially vertical. An aircraft A, in this case an airplane, generally comprises one or more incoming landing gear TA. A landing gear, typically the landing gear equipping a front portion of an aircraft as shown in Figure 1, is retracted in flight in a volume closed by a hatch. The hatch comprises two flaps 1, 1 ', open and closed under the action of actuating means. The actuating means are typically cylinders. The hatch may also include additional flaps actuated by the output or retraction of the train. The opening and closing systems of the hatches actuated by the most commonly used actuating means comprise a flap actuating cylinder 1, 1 '. These devices are generally heavy, bulky, and do not mechanically guarantee the concomitant opening of the shutters 1, 1 '. Devices employing a single jack V are also known. FIG. 2 schematically shows such a device for opening and closing a hatch of an aircraft landing gear and its immediate environment. In the device shown in Figure 2, two tie rods 3, 3 'are respectively connected to the flaps 1, 1', and are connected to one another at a pivot point PI. The pivot point PI is located at the end of a transverse arm 4. The other end of the transverse arm 4 is connected to the structure of the aircraft. The arm is said transversal because it extends generally parallel to the axis (y). The raising or lowering of the pivot point PI, under the effect of the jack V connected to the transverse arm 4 on the one hand, and to the structure of the aircraft on the other hand, causes the opening or closing flaps 1.1 'of the hatch. Nevertheless, such a system is heavy and bulky, and further introduces transverse forces (in a direction parallel to the axis (y)) in the structure of the aircraft, at two points of recovery efforts E1, E2. However, the structure of an aircraft is generally poorly adapted to undergo transverse forces. The connection zones between the structure of the aircraft and the jack 3 on the one hand, and the transverse arm 4 on the other hand, must therefore generally be reinforced, which weighs down the aircraft. A concomitant opening or closing device for two flaps 1.1 'of an aircraft landing gear according to a first embodiment of the invention is shown in FIGS. 3 and 4. In FIG. the landing gear door is open. In Figure 4, the landing gear door is closed. The landing gear is not shown. The flaps 1, 1 'pivot about two substantially parallel longitudinal pivot axes (AP) defining a closure plane (PF) of the flaps. The pivot axes (AP) are therefore substantially parallel to the axis (x). The plane (PF) is substantially parallel to the plane (x, y). The device comprises a single actuating means 2, in this case a hydraulic cylinder. The actuating means is of the variable length type, a modification of its length causing the simultaneous opening or closing of the shutters 1, 1 '. A so-called fixed end 21 of the actuating means is linked to the structure of the aircraft. The fixed end may in particular be fixed at a locking housing 9 of the hatch. The efforts can be taken up by a structural cross member 8 of the aircraft.
    [0007] The fixed end 21 is said to be fixed because its point of connection with the structure of the aircraft is fixed. The connection between the fixed end 21 and the structure of the aircraft may, however, be of the pivot or ball-and-socket type. The fixed end 21 may be the end of a fixed portion 22 of the actuating means 2. The actuating means 2 further comprises a movable portion 23. The concept of mobile is understood vis-à-vis the structure of the aircraft. In the embodiment shown here, the single actuating means 2 is a jack which comprises a rod and a body. The fixed end 21 is advantageously the end of the rod. The rod constitutes the fixed part 22. The body of the jack constitutes the mobile part 23.
    [0008] The device comprises an oscillating arm 5. The oscillating arm 5 comprises a first end 51 linked by a first connection to the structure, and a second end 52 linked by a second connection to the movable part 23 of the actuating means 2. The first link is a pivot P1. The second link having a degree of freedom along an axis parallel to the axis of the pivot P1. The second link may therefore include a second pivot P2. The device is configured so that said second end 52 of the oscillating arm 5 moves away from or approaches the closure plane PF of the flaps 1, 1 'during the extension or retraction of the actuating means 2. For this purpose, the actuating means is advantageously oriented so that its moving part moves substantially orthogonally to the closure plane PF of the flaps, that is to say substantially orthogonal to the plane (x, y), or parallel to the axis (z). It remains substantially oriented thus during its extension and its retraction. This does not prevent a slight tilting of the actuating means 2 and / or its movable portion 23 about the axis (z). The oscillating arm 5 is advantageously movable in a longitudinal plane of symmetry of the device. This plane is parallel to the plane (x, z).
    [0009] In the embodiment shown here, the guiding of the movable part 23, that is to say the cylinder body, is achieved by the oscillating arm 5 connecting the structure to the movable part 23 of the actuating means 2. This guidance is obtained by the fact that, as previously mentioned, in the embodiment represented here, the oscillating arm 5 is pivotally connected to the structure by a pivot connection P1. The oscillating arm 5 is connected to the moving part 23, by a second link having a pivot axis P2 parallel to the axis of the pivot link P1. Advantageously, the axes of the pivot links P1, P2 are parallel to the axis (y). The oscillating arm 5 is advantageously substantially parallel to the plane (x, y) or to the closure plane PF of the flaps 1, 1 ', when the actuating means is halfway between a retracted position and an extended position. Thus, during the extension or retraction of the actuating means, that is to say during the displacement of the movable part 23, the second end of the oscillating arm connected to the movable part 23 guides the latter substantially through vertical translation. In all rigor, the actuating means 2 tilts slightly in a plane parallel to the plane (x, z) during its extension or retraction. The moving part 23 describes a translational movement and rotation in this plane, with a majority component along an axis parallel to the axis (z), orthogonal to the closure plane of the first and second flaps 1,1 '.
    [0010] The second end of the oscillating arm is furthermore linked respectively to a first tie rod connected to a first of the two flaps, and to a second tie rod connected to a second of the two flaps, the oscillating arm 5 thus simultaneously ensuring the connection between the moving part 23 and the first and second tie rods 3, 3 ', and the connection between the movable part and the structure of the aircraft. Nevertheless, in the configuration of the invention shown here, all or almost all the forces generated during the opening or closing of the flaps 1, 1 'is taken up at the level of the connection between the fixed part 22 and the structure, in this case at the fixed end 21 of the actuating means 2. As shown in Figure 5, the connection between the oscillating arm 5 and the movable part 23 is made using a cardan 6. The use of a cardan 6 has several advantages. It allows the pivot connection between the oscillating arm 5 and the movable portion 23 of the actuating means 2. The universal joint 6 typically allows the connection between a cylinder body and the oscillating arm 5 other than at the end of said body. cylinder. This reduces the size and therefore the mass of tie rods 3, 3 ', and lower the position of the swingarm in the device. The tie rods 3, 3 'are respectively linked to the flaps 1, 1' away from their respective pivot axis (AP). Thus, the movement of the movable part and the second end of the oscillating arm with respect to the closure plane (PF) of the flaps 1, 1 'during extension or retraction of the actuating means 2, causes the pivoting flaps 1, 1 'and therefore their opening or closing. In the variant of the invention shown, the flaps 1, 1 'each comprise a panel and an actuating part 7, 7' rigidly connected to the panel. Each tie rod 3,3 'is connected to an actuating part 7,7'. The connection is a ball joint. The actuating part 7 makes it possible to define the position of the panel of the flap 1 with respect to the axis of pivoting (AP) of the flap on the one hand, and the point of application of the movement by the tie rod 3, 3 'on the other hand. This allows the panels to be rotated as they open and close.
    [0011] A concomitant opening or closing device of two flaps 1.1 'of an aircraft landing gear according to a second embodiment of the invention is shown in FIGS. 6 and 7. In FIG. the landing gear door is open. In Figure 7, the landing gear door is closed. The landing gear is not shown.
    [0012] The second embodiment represented here is distinguished from the first in particular by the fact that the oscillating arm 5 is connected to the movable end 3014 836 of the movable part 23 of the actuating means 2 by a pivot P2 of parallel axis to the axis of the pivot link P1. In the example illustrated here, and contrary to the example shown to illustrate the first embodiment, the movable portion 23 of the actuating means 5 is the rod of a jack, while its fixed part 22 is the body of said cylinder. Functionally, the mounting of the cylinder in this direction or in the other is unimportant, its elongation causing the movement of the hatches. Nevertheless, the fact that the fixed end 21 is the end of the cylinder body facilitates the hydraulic supply of said cylinder.
    [0013] This embodiment simplifies the connection between the actuating means 2 and the oscillating arm 5. Nevertheless, it requires the use of tie rods 3, 3 'of greater length than a device corresponding to the first embodiment described in FIG. 3 and 4. In the first and second embodiments of the invention shown, the extension of the actuating means 2 causes the shutters to close. This is particularly advantageous when the actuating means 2 is a jack, because it allows to take advantage of the maximum force of the cylinder when closing the shutters. Indeed, the application section of the hydraulic pressure offered by the piston of a double-acting cylinder is greater in extension than retraction of the cylinder. Nevertheless, the device may, in another embodiment, include an actuating means whose retraction causes the closure of the flaps 1,1 ', without departing from the scope of the invention. Typically, the actuating means could be linked to the structure remote from the closure plane 25 PF. The figures illustrate by way of example a non-limiting embodiment of the invention. Other embodiments can be envisaged. In particular, the actuating means 2 may be of any other type having a length change, for example, in addition to the cylinder illustrated, a screw pusher. The invention thus developed allows the concomitant opening of the flaps of a landing gear of an aircraft. It applies in particular to aircraft. It is particularly suitable for landing gear before aircraft. The concomitant opening is obtained using a single actuating means, and guaranteed by a mechanical connection between the flaps of the equipped hatch. The developed device is lightweight and simple kinematic. It also makes it possible to recover all or almost all the forces generated by the opening or closing of the flaps at a single point in the structure of the aircraft equipped.
    权利要求:
    Claims (14)
    [0001]
    REVENDICATIONS1. Concomitant opening or closing device for two flaps (1,1 ') of a hatch of an aircraft landing gear, the two flaps (1,1') pivoting about two pivot axes ( AP) substantially parallel defining a closure plane (PF) of the flaps (1,1 '), the device comprising a single actuating means (2) able to open and close the flaps (1,1') by modification of its length, the actuating means (2) comprising a fixed end (21) connected at a point of stress recovery to the structure of the aircraft, the actuating means (2) further comprising a movable part ( 23), characterized in that the device comprises an oscillating arm (5) having a first end (51) joined by a first connection to the structure, and a second end connected by a second connection to the movable part of the actuating means , the first link being a pivot (P1) and the second link having a degree of liber rotating along an axis parallel to the axis of the pivot (P1), the device being configured so that said second end (52) of the oscillating arm (5) moves away from or approaches the closure plane (PF) of the flaps during extension or retraction of the actuating means (2), the second end (52) of the swing arm (5) being furthermore respectively connected to a first tie rod (3) connected to a first of the two flaps , and a second tie (3 ') linked to a second of the two flaps.
    [0002]
    2. Device according to claim 1, wherein the movable portion (23) of the actuating means (2) is connected to the swing arm (5) by a universal joint (6).
    [0003]
    3. Device according to claim 1, wherein the movable portion (23) of the actuating means comprises a movable end (24) connected to the oscillating arm (5).
    [0004]
    4. Device according to one of claims 1 to 3, wherein the actuating means (2) is a jack.
    [0005]
    5. Device according to any one of the preceding claims, characterized in that it is symmetrical on either side of a longitudinal plane, orthogonal to the closure plane (PF).
    [0006]
    6. opening or closing device according to any one of the preceding claims, wherein each tie rod (3,3 ') is connected to a flap (1,1') away from its pivot axis (AP).
    [0007]
    7. An opening or closing device according to one of the preceding claims, wherein each tie rod (3,3 ') is connected to a flap (1,1') by a ball joint.
    [0008]
    8. Opening or closing device according to any one of the preceding claims, wherein each flap (1,1 ') comprises a panel and an actuating part (7,7') rigidly connected to the panel, the pulling (3,3 ') being connected to the actuating part (7,7').
    [0009]
    9. An opening or closing device according to any one of the preceding claims, wherein an extension of the actuating means (2) causes the shutters (1,1 ') to close.
    [0010]
    10. An opening or closing device according to any one of claims 1 to 8, wherein an extension of the actuating means (2) causes the opening of the flaps (1,1 ').
    [0011]
    11. Aircraft comprising a concomitant opening or closing device of two flaps (1) of a landing gear that it comprises, according to one of the preceding claims.
    [0012]
    12. Aircraft according to claim 11, wherein the actuating means (2) is connected to the structure of the aircraft, so that the vertical component of the forces generated during the opening or closing of the hatch is resumed in full at the point of stress recovery by the structure.
    [0013]
    13. Aircraft according to claim 11 or claim 12, wherein the stress recovery point is located on a structural cross member (8) of the fuselage.
    [0014]
    14. Aircraft according to any one of claims 11 to 13, wherein the stress recovery point is located at a locking housing 9 of the hatch.
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    同族专利:
    公开号 | 公开日
    FR3014836B1|2016-02-05|
    US9499258B2|2016-11-22|
    CN104709462A|2015-06-17|
    US20150166173A1|2015-06-18|
    CN104709462B|2018-07-06|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2397516A|1944-08-05|1946-04-02|Curtiss Wright Corp|Safety locking device|
    US2604281A|1948-08-11|1952-07-22|Glenn L Martin Co|Actuating mechanism and support for bomb bay doors|
    GB784929A|1954-11-22|1957-10-16|Armstrong Whitworth Co Eng|Closing doors for a bomb bay of an aircraft|
    EP1129939A2|2000-03-03|2001-09-05|The Boeing Company|Rotary door assembly for landing gear|
    FR2911321A1|2007-01-11|2008-07-18|Airbus Sa Sa|SYSTEM FOR OPENING AND CLOSING AN AIRCRAFT LANDING TRAIN BOX|
    US2222975A|1938-02-24|1940-11-26|Brewster Aeronautical Corp|Retractable landing gear|
    US2452251A|1942-03-19|1948-10-26|North American Aviation Inc|Retractable landing gear fairing|
    US2406710A|1943-10-04|1946-08-27|Glenn L Martin Co|Landing gear housing door|
    US2750929A|1951-08-27|1956-06-19|Douglas Aircraft Co Inc|Cycle control valve for hydraulic motors|
    US2677515A|1951-12-21|1954-05-04|Lockheed Aircraft Corp|Combined landing gear operating mechanism, side strut and down lock|
    US2692097A|1951-12-22|1954-10-19|North American Aviation Inc|Retractable aircraft landing gear|
    GB1347690A|1970-10-10|1974-02-27|British Aircraft Corp Ltd|Doors|
    JP3147539B2|1992-10-05|2001-03-19|本田技研工業株式会社|Aircraft landing gear|
    US6345786B1|2000-03-03|2002-02-12|The Boeing Company|Linked multi-segment landing gear door for aircraft|
    GB0208963D0|2002-04-19|2002-05-29|Bae Systems Plc|Landing gear door assembly|
    FR2866313B1|2004-02-13|2007-04-20|Airbus France|ARTICULATED TRAPPER FOR AIRCRAFT LANDING TRAIN|
    JP2006036169A|2004-07-30|2006-02-09|Nabtesco Corp|Door opening/closing device|
    FR2886620B1|2005-06-07|2008-12-19|Airbus France Sas|TRAPPING OPENING AND CLOSING SYSTEM FOR LANDING TRAIN BOX OF AN AIRCRAFT|
    FR2947526B1|2009-07-03|2012-04-20|Messier Dowty Sa|DEVICE FOR MANEUVERING TRAPPES CLOSING THE REACH OF AN AIRCRAFT AIRCRAFT|
    US8746616B2|2011-10-19|2014-06-10|The Boeing Company|Mid-wing multi-deck airplane|
    CN103061641B|2013-01-05|2015-06-24|中国商用飞机有限责任公司|Position adjusting method for eliminating mounting out-of-tolerance of front cabin door of front undercarriage of airplane|FR3025492A1|2014-09-05|2016-03-11|Airbus Operations Sas|AIRCRAFT COMPRISING TWO DOORS OF LANDING TRAIN AND A SYSTEM FOR MANEUVERING SAID DOORS|
    FR3039131B1|2015-07-24|2019-06-07|Airbus Operations|LANDING TRAIN BOX REAR TRAP COMPRISING AN AIR PASSAGE ORIFICE AND A SHUT OFF MEMBER THEREOF|
    CN105000197A|2015-08-11|2015-10-28|中国航空工业集团公司西安飞机设计研究所|Rotating part loading mechanism|
    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|
    EP3929075A4|2020-06-24|2021-12-29|Airbus Operations Slu|Landing gear door system and operation method|
    法律状态:
    2015-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2016-12-22| PLFP| Fee payment|Year of fee payment: 4 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-10| ST| Notification of lapse|Effective date: 20210805 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1362712A|FR3014836B1|2013-12-16|2013-12-16|DEVICE FOR OPENING OR CLOSING CONCOMITANTS OF TWO SHUTTERS OF A TRAPPER OF A LANDING TRAIN|FR1362712A| FR3014836B1|2013-12-16|2013-12-16|DEVICE FOR OPENING OR CLOSING CONCOMITANTS OF TWO SHUTTERS OF A TRAPPER OF A LANDING TRAIN|
    US14/567,527| US9499258B2|2013-12-16|2014-12-11|Device for concomitant opening or closing of two flaps of a landing gear door|
    CN201410858233.5A| CN104709462B|2013-12-16|2014-12-16|Open or close device while two baffles of undercarriage door|
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