• 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 device for locking a first cover and a second cover of a thrust reverser of a propulsion unit of an aircraft, said covers being mounted pivoting each around a longitudinal axis, between a closed flight position and an open maintenance position, the locking device comprising a telescopic connecting rod (20) which comprises at least one sliding rod (26), a locking means of the proximal end (34) of the rod (26). ) on the second cover, and a support (24) of connecting rod, characterized in that the support (24) of the connecting rod, or the tubular element (28) of the connecting rod (20), comprises two walls (42a, 42b) which each delimit a light (44a, 44b), and in that the tubular element (28) of the connecting rod (20), or respectively the rod support (24), carries two support fingers (48a, 48b) which each extend generally longitudinally on either side of the tubular element (28), in one of said lumens (44a, 44b), said slots being adapted to cooperate with the support fingers (48a, 48b) when the covers are open and to allow free movement of the support fingers (48a, 48b) in a closed hood configuration.
    公开号:FR3037039A1
    申请号:FR1555065
    申请日:2015-06-03
    公开日:2016-12-09
    发明作者:Vincent Peyron；Serge Bunel；Pascal Soulier；Arnaud Bonny
    申请人:Aircelle SA；
    IPC主号:
    专利说明:

    [0001] The invention relates to a device for locking a first cover and a second cover of a thrust reverser of a propulsion unit of an aircraft, to limit the transmission of forces between the covers and the rest. of the propulsion system.
    [0002] The propulsion units for the aircraft generally comprise a nacelle forming a generally circular outer envelope, comprising inside a turbojet arranged along the longitudinal axis of this nacelle. The turbojet receives fresh air from the upstream side, or before, and rejects on the downstream side, or back, the hot gases from the combustion of the fuel, which give a certain thrust. The turbofan engines have around the engine fan blades generating a large secondary flow of cold air along an annular vein passing between this engine and the nacelle, which adds a high thrust in normal operation giving a direct jet . Some nacelles comprise a thrust reversal system which closes at least part of the annular cold air duct, and rejects the secondary flow forward forming an inverted jet which generates a braking counter-thrust of the aircraft . A known type of platform, presented in particular by the document FR-A1-2920144, comprises two half-covers covering the median section surrounding the secondary flow blower, hereinafter called hoods, comprising a hinge having a longitudinal axis located in the upper part, so as to allow opening of these covers for maintenance operations. In order to guarantee the structural integrity of the two covers, there is known a locking device which comprises a telescopic connecting rod, the connecting rod comprising a rod which is slidably mounted along a generally transverse axis, in a tubular element, between a retracted position corresponding to a closed hood configuration and an extended position corresponding to an open hood configuration. The movable rod of the link has a distal end which is connected to the first cap, and a proximal end which is adapted to be connected to the second cap via a locking means. The locking means is adapted to lock the covers together in their closed position, blocking the movable rod of the connecting rod. In addition, the locking device comprises an assembly for connecting the connecting rod to a fixed part of the propulsion unit, for example on the mast of the aircraft or on the engine, this assembly comprising a fitting, a vertical rod. and a stirrup. The fitting is fixed to the mast, or to the motor, and the vertical rod is mounted in a pendular manner on the fitting about a longitudinal axis of pivoting. The stirrup is slidably mounted vertically and pivoted on the vertical shaft, about a vertical axis perpendicular to the axis of sliding of the rod. In addition, the yoke is pivotally mounted on the connecting rod about a longitudinal axis, perpendicular to the axis of sliding of the connecting rod. In order to maintain the support function of the connecting rod and the caliper in maintenance, the vertical rod is equipped with a stop which makes it possible to support the caliper, which is driven downwards in the open cowl configuration. When the caps are closed again, the connecting rod is engaged in the locking system by means of ramps which refocus the connecting rod vertically. Also, in order to stabilize the locking device in flight, the locking device comprises a spring which is interposed axially between the free end of the movable rod of the connecting rod and the tubular element of the connecting rod. A disadvantage of this type of locking device is that the connecting rod is connected, in flight phase, to both the movable covers, by the two ends of the sliding rod of the connecting rod, and the engine, or the mast, by 25 through the stirrup and the fitting. The covers, the engine and the mast have different frequencies and vibration levels, so that the connecting rod and the locking means are subjected to a severe vibration environment that may reduce the longevity of the locking device. In addition, this type of locking device is poorly adapted to a configuration in which the stirrup must be fixed to the motor, which may be the case when the mast is too far from the locking means or is not accessible. because masked by equipment. Indeed, the motor is arranged under the locking means, while the mast is arranged above the locking means, so that the vertical rod, which is pivotally mounted on the stirrup, will tend to rotate naturally. forward or backward under the effect of gravity. To limit the tilting of the vertical rod, the addition of angular stops will be necessary, these stops having to maintain a latitude of movement of the stirrup along the longitudinal longitudinal axis relative to the connecting rod during flight phases. The position of the connecting rod in open hood configuration will therefore be uncertain, which will require to provide more substantial recentering ramps to ensure engagement of the connecting rod with the locking means when closing the covers. The present invention aims in particular to solve these disadvantages and relates for this purpose to a device for locking a first cover and a second cover of a thrust reverser of a propulsion unit of an aircraft, said covers being each pivoting about a longitudinal axis, between a closed flight position and an open maintenance position, the locking device comprising: - a telescopic connecting rod which comprises at least one rod which is slidably mounted along a generally transverse axis, in a tubular element, between a retracted position corresponding to a configuration of closed hoods and an extended position corresponding to an open hood configuration, and which has a distal end connected to the first hood and a proximal end adapted to be connected to the second hood a means for locking the proximal end of the rod on the second hood, which is designed for to lock said covers together in their closed position; - a connecting rod support which is mounted on a fixed part of the propulsion unit and which is designed to support the connecting rod at least in an open cowl configuration, characterized in that the rod support, or the tubular element of the connecting rod, comprises two walls which each extend on either side of the tubular element of the connecting rod, and which each delimit a light, and in that the tubular element of the connecting rod, or respectively the connecting rod support, carries two support fingers which each extend generally longitudinally on either side of the tubular element, in one of said slots, 3037039 4 said lights being adapted to cooperate with the support fingers when the covers are open and to allow free movement of the support fingers in a closed hood configuration. Thus, in closed hood flight configuration, the telescopic rod 5 is not in contact with the connecting rod support, whereby the rod does not transmit force or vibration to the fixed part of the propulsion unit. More precisely, in this configuration of closed flight hoods: either the support fingers of the connecting rod are carried by the tubular element of the connecting rod and are not in contact with the walls delimiting the lights carried by the connecting rod support, thanks to which the support fingers of the rod do not transmit effort to the fixed part of the propulsion unit; either the support fingers of the connecting rod are carried by the connecting rod support and are not in contact with the walls delimiting the lights then carried by the tubular element of the connecting rod, thanks to which the support fingers of the connecting rod do not transmit effort to the fixed part of the propulsion unit. According to another characteristic, the locking device comprises a first centering means of the connecting rod comprising at least one centering pin which extends perpendicularly to the connecting rod, from the tubular element of the connecting rod, and a first associated seat and which has a V-notch adapted to cooperate with the centering pin in order to guide the connecting rod in a position centered with respect to the locking means and for locking the tubular element of the connecting rod in transverse translation and in rotation about the axis of the connecting rod in a closed hood configuration. The rotational lock prevents the rod from rotating during flight and the fingers from coming into contact with the walls defining the lights. Advantageously, the first centering means promotes the engagement of the movable rod of the connecting rod in the locking means, during the closing of the covers. According to a preferred embodiment, the first seat of the first centering means and the locking means are integral with the second movable cover. In addition, the tubular member of the connecting rod has a proximal end which has a ring, said ring carrying the centering pin and the two supporting fingers. According to an alternative embodiment, the centering pin of the first centering means is formed by one of said fingers of the connecting rod support. This variant makes it possible to eliminate the centering pin. The device comprises a second centering means of the connecting rod 5 comprising a second seat which is integral with a fixed part of the propulsion unit and which has a generally V-shaped longitudinal section face adapted to cooperate with the tubular element of the connecting rod to guide the connecting rod in a centered position relative to the locking means, in an open hood configuration.
    [0003] The second centering means promotes the engagement of the movable rod of the connecting rod in the locking means, maintaining the rod in a centered position in open hood configuration. In another aspect, the locking device comprises an elastic return means which is interposed transversely between the sliding rod 15 and the associated tubular member of the connecting rod. The elastic return means makes it possible to stabilize the connecting rod in closed hood flight configuration. According to an exemplary embodiment, the locking device comprises a fuse element which is interposed between the connecting rod and the fixed part of the propulsion unit and which is designed to yield more than a certain effort in the event of blockage of the connecting rod during the opening or closing of the movable covers. According to an exemplary embodiment, the fixed part of the propulsion assembly, on which the connecting rod support is mounted, is a mast for connecting the nacelle to the aircraft. According to another embodiment, the fixed part of the propulsion assembly, on which the connecting rod support is mounted, belongs to a motor of the propulsion unit. Other features and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the appended drawings in which: FIG. 1 is a diagrammatic view of the rear assembly, which illustrates a first hood and a second hood in the closed position, a turbojet engine nacelle equipped with a locking device, according to the invention; FIG. 2 is a schematic overall rear view, which illustrates the covers of FIG. 1 in the open maintenance position; - Figure 3 is a schematic perspective detail view, which illustrates the telescopic rod of the locking device according to the invention, in a closed hood configuration; FIG. 4 is a schematic perspective detail view illustrating the telescopic connecting rod of the locking device according to the invention in an open hood configuration; - Figure 5 is a schematic rear view, which illustrates the telescopic rod in a closed hood configuration and the first centering means of the rod; Figure 6 is a schematic top view illustrating the telescopic rod in a closed hood configuration and the first centering means of the rod; - Figure 7 is a schematic rear view, which illustrates the telescopic rod deployed in an open hood configuration; FIG. 8 is a schematic rear view illustrating in detail the connecting rod support of FIG. 7; - Figure 9 is a schematic side view in longitudinal section which illustrates the second centering means of the rod in an open hood configuration; - Figure 10 is a schematic rear view illustrating an alternative embodiment of the invention. In the description and the claims, the terms "upper", "lower" and "low", "high" and their derivatives with reference to the upper part and the lower part of FIG. 1, respectively, will be used without implying any limitation. In addition, to clarify the description and the claims, the longitudinal, vertical and transverse terminology will be adopted by way of nonlimiting reference with reference to the trihedron L, V, T indicated in the figures, whose longitudinal axis L is parallel to the axis. of the nacelle. In all of these figures, identical or similar references represent identical or similar members or sets of members. FIG. 1 shows a first hood 10 and a second hood 12 of a propulsion unit, the propulsion unit comprising a nacelle 35 which carries a turbojet and which is supported by a pylon 14, or mast, fixed under wing of an aircraft. The nacelle comprises a front section comprising a profiled air inlet, a central section which surrounds the cold air blower and which comprises the two covers 10, 12, carrying shutters of the thrust reverser. Without limitation, the invention also applies to a nacelle 5 without a thrust reverser. The nacelle forms an external profiling of the annular vein guiding the flow of cold air, and an aerodynamic exterior fairing. The two covers 10, 12 are arranged symmetrically with respect to a vertical axial plane, and can open laterally by pivoting around a hinge 16 each comprising a longitudinal axis arranged in the upper part. The hoods 10, 12 are pivotally mounted between a closed flight position, illustrated in FIG. 1, and an open maintenance position, illustrated in FIG. 2. The platform is equipped with a locking device 18 which comprises a connecting rod 20, a locking means 22 of the rod 20 and a support rod 24. The rod 20 comprises a telescopic rod 26, which is schematically shown in a single part in the figures for the sake of simplification, and which is slidably mounted along a generally transverse axis in a complementary tubular element 28, between a retracted position corresponding to a closed hood configuration, shown in Figures 3, 5, and 6, and an extended position corresponding to an open hood configuration, shown in Figures 4, 7, 8 and 9.
    [0004] The sliding rod 26 has a distal end 30 connected to the first cap 10 via a hinge 32, and a proximal end 34 adapted to be connected to the second cap 12 via the locking means 22. L The hinge 32 has the shape of a yoke which is fixed on the first cap 10 and which is pivotally mounted on the distal end 30 of the rod 26 about a longitudinal pivot axis 36. The locking means 22 is mounted on the second cap 12, the locking means 12 being adapted to lock the proximal end 34 of the rod 26 to the second cap 12, in order to lock the covers 10, 12 between them in their housing. closed position. For this purpose, the locking means 22 is for example a latch which cooperates with the proximal end 34 of the rod 26. The rod support 24 is mounted on a fixed part of the propulsion unit, here on the engine. 38 which is shown in Figure 1 and which is arranged 5 below the rod 20. Not limited to, the fixed part on which is mounted the support rod 24 can be the mast 14 which is arranged above the connecting rod 20. Referring to Figure 3, the support rod 24 has a U-shaped which comprises a sole 40 attached to the motor 38, sole 40 10 from which two walls 42a, 42b extend vertically vis-à-vis symmetrically in a vertical plane, on either side of the tubular element 28 of the rod 20. Each wall 42a, 42b delimits a light 44a, 44b, each delimited by a peripheral edge 46a, 46b respectively. In a complementary manner, the proximal end of the tubular element 28 of the connecting rod 20 is equipped with a ring 47 which comprises two support fingers 48a, 48b. As can be seen in FIG. 3, the support fingers 48a, 48b each extend generally longitudinally on either side of the tubular element 28, through one of the apertures 44a, 44b respectively. The lights 44a, 44b and the associated support fingers 48a, 48b are designed to allow free movement of the rod 20 along the three longitudinal, transverse and vertical directions. In another aspect, the locking device 18 comprises a first centering means 50 of the connecting rod 20, shown in FIGS. 5 and 6, which comprises a centering pin 52 cooperating with a first seat 54. The centering pin 52 extends perpendicularly to the connecting rod 20, along a vertical axis, from the ring 47 of the tubular element 28 of the connecting rod 20.
    [0005] The first seat 54 is formed in a plate 56 which is fixed on the locking means 22, the plate 56 delimiting a notch 58 in V. The notch 58 in V is arranged facing the associated centering pin 52, the notch 58 having two convergent ramps which are adapted to cooperate with the centering pin 52 to guide the link 20 in a position centered axially with respect to the locking means 22.
    [0006] According to another aspect of the invention, the locking device 18 comprises a second centering means 60 of the connecting rod 20, shown in FIG. 4. The second centering means 60 comprises a second seat 62 which is formed by the soleplate 40 of the connecting rod support 24 and which has a generally V-shaped longitudinal section upper face adapted to cooperate with the tubular element 28 of the connecting rod 20 in order to guide the connecting rod 20 in a position centered with respect to the locking means 22 , in an open hood configuration.
    [0007] In addition, the locking device 18 comprises a helical spring 64 forming elastic return means, which is interposed transversely between the distal end 30 of the sliding rod 26 and the associated tubular element 28 of the connecting rod 20. The spring 64 makes it possible to elastically constrain the pin 52 of centering of the tubular element 28 against the plate 56 of the first centering means 50, to stabilize the connecting rod 20 in a closed flight configuration. Also, the locking device 18 comprises a fuse element (not shown) which is interposed between the connecting rod 20 and the motor 38 and which is designed to yield more than a certain amount of force if the connecting rod 20 is blocked. during the opening or closing of the covers 10, 12 mobiles. Thus, the fuse element can damage neither the motor nor the first cover 10 which is connected to the distal end 30 of the connecting rod 20. The fuse element can for example be integrated in the support rod 24. The implementation of the locking device 18 is described below. In an open cowl configuration, shown in Figure 2, the rod 26 of the rod 20 is deployed and the tubular member 28 of the rod 20 rests on the support 24 of the rod. More precisely, as can be seen in FIGS. 4, 7 and 8, the two support fingers 48a, 48b, integral with the connecting rod 20, bear against the peripheral edge 46a, 46b of the slots 44a, 44b respectively. Also, still in open hood configuration, with reference to FIG. 9, the proximal end of the tubular element 28 of the connecting rod 20 rests vertically on the second seat 62 of the second centering means 60, the second seat 62 enabling centering the connecting rod 20 with respect to the locking means 22, to promote the engagement of the rod 26 of the connecting rod 20 in the locking means 22, during the closing of the covers 10, 12. When the covers 10, 12 are driven from their open position towards their closed position, the spring 64 is compressed between the tubular element 28 of the connecting rod and the hinge 32, then the free proximal end 34 of the rod 26 engages in the locking means 22. To promote the engagement of the rod 26 in the locking means 22, at the end of the covers 10, 12, the centering pin 52 slides on the V-notch 58 of the first centering means 50, until 10 the rod 26 itself The first centering means 50 blocks the tubular element 28 of the connecting rod 20 in transverse translation, which allows the spring 64 to compress the connecting rod 20. Moreover, by pressing against the notch 58, the centering pin 52 makes it possible to recenter the support fingers 48a, 48b generally in the middle of the associated lumens 44a, 44b. Once the covers 10, 12 closed, the link 20 is stabilized in transverse translation and in rotation under the effect of the spring 64 which pushes the centering pin 52 on the notch 58.
    [0008] With reference to FIGS. 3 and 5, it will be noted that the locking device 18 is designed so that, in the closed hood configuration, the support fingers 48a, 48b and the walls 42a, 42b of the connecting rod support 24 are not in position. contact and allow a travel of the rod 20, despite the geometric tolerances and the relative displacement of the motor 38 and the covers 10, 12.
    [0009] It will also be noted that the connecting rod support 24 can be fixed to the mast, the walls 42a, 42b pointing downwards, without prejudice to the proper functioning of the locking device 18. In another aspect, to allow disassembly of the first cover 10 which is attached to the connecting rod 20, several solutions can be envisaged. A first solution consists of an interface which connects the support rod 24 on the motor 38 and which is quickly removable, this interface may be constituted by a plurality of screws and nuts for example. A second solution is to make the two support fingers 48a, 48b removable.
    [0010] Finally, a third solution is to arrange an opening in the upper part of the lights 44a, 44b for disengaging the support fingers 48a, 48b. According to an alternative embodiment of the invention shown in FIG. 10, the first centering means 50 of the connecting rod 20 is offset on the side of the locking means 22 in order to eliminate the vertical centering pin 52. For this purpose, the plate 56 extends vertically on one side of the locking means 22, the plate 56 delimiting a V-shaped notch 58 which is arranged facing the first support finger 48a, in closed cowl configuration, so that the first support finger 48a cooperates with the notch 58 to guide and center the rod 20 during the closing of the covers 10, 12. The present description of the invention is given by way of non-limiting example. It will be understood that simple mechanical inversions are covered by the invention, the lights 46a, 46b may for example be formed by the tubular element 28 of the rod 20 and the associated support fingers 48a, 48b may extend from the walls 42a, 42b of the support 24 of 20 connecting rod 20.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Device (18) for locking a first cover (10) and a second cover (12) of a thrust reverser of a propulsion unit of an aircraft, said covers (10, 12) being pivotally mounted each around a longitudinal axis (16), between a closed flight position and an open maintenance position, the locking device (18) comprising: - a telescopic connecting rod (20) which comprises at least one rod (26) which is slidably mounted along a generally transverse axis, in a tubular element (28), between a retracted position corresponding to a closed hood configuration and an extended position corresponding to an open hood configuration, and which has a distal end (30) connected to the first cover (10) and a proximal end (34) adapted to be connected to the second cover (12), - a locking means (22) for the proximal end (34) of the stem (26) on the second cover ( 12), which is designed to lock s covers together in their closed position, and - a rod support (24) which is mounted on a fixed part (38) of the propulsion unit and which is designed to support the connecting rod (20) at least 20 in a configuration open hoods, characterized in that the connecting rod support (24), or the tubular element (28) of the connecting rod (20), comprises two walls (42a, 42b) which extend on either side of the tubular element (28) of the connecting rod (20), each of which delimits a lumen (44a, 44b), and in that the tubular element (28) of the connecting rod (20), or respectively the support (24) ) of connecting rod, carries two support fingers (48a, 48b) which each extend generally longitudinally on either side of the tubular element (28), in one of said slots (44a, 44b), said slots being adapted to cooperate with the support fingers (48a, 48b) when the covers (10, 12) are open and to allow free movement of the fingers (48a, 48b) of the sup port in a closed hood configuration.
    [0002]
    2. Device (18) for locking according to claim 1, characterized in that it comprises a first centering means (50) of the connecting rod (20) having at least one centering pin (52) which extends perpendicularly to the connecting rod (20), from the tubular element (28) of the connecting rod 3037039 13 (20), and a first seat (54) associated which has a notch (58) V adapted to cooperate with the pin (52) centering device for guiding the connecting rod (20) in a position centered with respect to the locking means (22) and for locking the tubular element (28) of the connecting rod (20) in transverse translation and rotating about the axis of the connecting rod (20), in a closed hood configuration.
    [0003]
    3. Device (18) for locking according to claim 2, characterized in that the first seat (54) of the first centering means (50) and the locking means (22) are integral with the second movable cover (12). 10
    [0004]
    4. Device (18) for locking according to any one of the preceding claims, characterized in that the tubular element (28) of the rod (20) has a proximal end which comprises a ring (47), said ring (47). ) carrying the centering pin (52) and the two supporting fingers (48a, 48b). 15
    [0005]
    5. Device (18) for locking according to claim 2 or 3, characterized in that the centering pin of the first centering means (50) is formed by one of said fingers (48a, 48b) of the support (24) connecting rod.
    [0006]
    6. Device (18) for locking according to any one of the preceding claims, characterized in that it comprises a second centering means (60) of the connecting rod (20) having a second seat (62) which is secured to a fixed part (38) of the propulsion unit and which has a generally V-shaped longitudinal section face adapted to cooperate with the tubular element (28) of the connecting rod (20) in order to guide the connecting rod (20) in a position centered with respect to the locking means (22) in an open hood configuration.
    [0007]
    7. Device (18) for locking according to any one of the preceding claims, characterized in that it comprises an elastic return means (64) which is interposed transversely between the rod (26) sliding and the tubular element (28). ) associated with the connecting rod (20).
    [0008]
    8. Device (18) for locking according to any one of the preceding claims, characterized in that it comprises a fuse element which is interposed between the connecting rod (20) and the fixed part (38) of the propulsion unit and which is designed to yield more than a certain amount of effort if the connecting rod (20) is blocked during the opening or closing of the movable covers (10, 12). 3037039 14
    [0009]
    9. Device (18) for locking according to any one of the preceding claims, characterized in that the fixed part of the propulsion assembly, on which the support (24) rod is mounted, is a mast (14) for connect the nacelle on the aircraft. 5
    [0010]
    10. Device (18) for locking according to any one of claims 1 to 8, characterized in that the fixed part of the propulsion assembly, on which the support (24) connecting rod is mounted, belongs to the motor (38) of the propulsion system.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3037039A1|2016-12-09|DEVICE FOR LOCKING PIVOTING HOODS OF A PUSH INVERTER
    EP2084062B1|2010-07-07|Side-opening jet engine nacelle
    EP0357494B1|1992-06-03|Thrust reverser with auxiliary flaps for a jet engine
    EP2651764B1|2016-12-14|Nacelle for a bypass turbojet engine
    EP2178760B1|2011-11-30|Jet engine nacelle intended to equip an aircraft
    EP0828934A1|1998-03-18|Double door thrust reverser assembly
    EP3247635B1|2018-05-16|System for mounting a propulsion assembly onto a pylon of an aircraft and dismounting same therefrom
    FR2953490A1|2011-06-10|REPLACEMENT OF NACELLE FOR TURBOJET ENGINE
    EP2188178B1|2013-12-25|Jet engine nacelle intended to equip an aircraft
    EP3732360A1|2020-11-04|Grid-type thrust reverser for turbojet engine
    EP3247634B1|2019-01-09|Rear nacelle assembly for a turbojet comprising a cradle for a pylon
    EP3247633B1|2018-08-01|Rear nacelle assembly for a turbojet comprising a suspension cradle
    EP2178761B1|2012-04-25|Locking device
    WO2014033398A1|2014-03-06|Assembly for holding the interface of a front frame of a nacelle and a turbojet casing
    FR2997925A1|2014-05-16|GUIDE ASSEMBLY FOR A MOBILE NACELLAL UNIT FOR A TURBOJET ENGINE
    EP3155252B1|2018-04-04|Thrust reverser for nacelle of aircraft turbofan
    FR3009542A1|2015-02-13|AIRCRAFT ASSEMBLY COMPRISING A ACCESS PANEL TO THE JOINTS OF A MONO SWIVEL NACELLE HOOD ON AN AIRCRAFT ENGINE HANDLING DEVICE
    WO2018011486A1|2018-01-18|Rear assembly for a jet engine nacelle, comprising a fireproof seal device
    FR3085352A1|2020-03-06|NACELLE FOR AN AIRCRAFT ENGINE COMPRISING MEANS FOR PREVENTING THE DEFORMATION OF THE ARTICULATED BLOWER HOODS
    同族专利:
    公开号 | 公开日
    WO2016193641A1|2016-12-08|
    FR3037039B1|2017-06-02|
    US20180079517A1|2018-03-22|
    US10745140B2|2020-08-18|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    FR2771710A1|1997-12-03|1999-06-04|Aerospatiale|OPENING DEVICE COMMON TO TWO ADJACENT HOODS FOR AN AIRCRAFT NACELLE|
    FR2920144A1|2007-08-20|2009-02-27|Aircelle Sa|NACELLE EQUIPPED WITH A DEVICE FOR DETECTING THE LATCHING STATE OF A LATCHING DEVICE|
    FR2920177A1|2007-08-20|2009-02-27|Aircelle Sa|CONNECTING DEVICE FOR CONNECTING FIRST AND SECOND MOVING ELEMENTS TO ONE ANOTHER|
    FR2920178A1|2007-08-20|2009-02-27|Aircelle Sa|CONNECTING DEVICE FOR CONNECTING FIRST AND SECOND ARTICULATED ELEMENTS RELATIVE TO EACH OTHER|
    FR2920174A1|2007-08-20|2009-02-27|Aircelle Sa|CONNECTION DEVICE BETWEEN THE TWO HALF SHELLS OF AN AIRCRAFT ENGINE NACELLE, AND NACELLE EQUIPPED WITH SUCH A DEVICE|EP3473549A1|2017-10-20|2019-04-24|Hamilton Sundstrand Corporation|Actuator with vibration attenuation using visco elastic materials|US4629146A|1985-01-30|1986-12-16|Rohr Industries, Inc.|Hold open rod for hinged section of nacelle system|
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    FR3014842B1|2013-12-17|2017-12-01|Sagem Defense Securite|TELESCOPIC ACTUATOR AND AIRCRAFT ENGINE COMPRISING SUCH ACTUATOR|
    GB201322380D0|2013-12-18|2014-02-05|Rolls Royce Plc|Gas turbine cowl|
    US10670063B2|2014-09-04|2020-06-02|Hartwell Corporation|Hold open rod locking mechanism|
    ES2673562T3|2014-09-29|2018-06-22|Airbus Defence And Space, S.A.|Alignment and safety device for the gondola hoods of aircraft engines|WO2014164238A1|2013-03-13|2014-10-09|United Technologies Corporation|Gas turbine engine hydraulically operated nacelle latch|
    US10081434B2|2015-03-12|2018-09-25|Rohr, Inc.|Track mounted hold open rod|
    USD930457S1|2017-07-11|2021-09-14|C&D Zodiac, Inc.|Door latch|
    US10612491B2|2017-09-25|2020-04-07|Rohr, Inc.|Mounting device with pin actuator|
    法律状态:
    2016-06-09| PLFP| Fee payment|Year of fee payment: 2 |
    2016-12-09| PLSC| Search report ready|Effective date: 20161209 |
    2017-06-08| PLFP| Fee payment|Year of fee payment: 3 |
    2018-03-02| CD| Change of name or company name|Owner name: SAFRAN NACELLES, FR Effective date: 20180125 |
    2018-06-14| PLFP| Fee payment|Year of fee payment: 4 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1555065A|FR3037039B1|2015-06-03|2015-06-03|DEVICE FOR LOCKING PIVOTING HOODS OF A PUSH INVERTER|FR1555065A| FR3037039B1|2015-06-03|2015-06-03|DEVICE FOR LOCKING PIVOTING HOODS OF A PUSH INVERTER|
    PCT/FR2016/051336| WO2016193641A1|2015-06-03|2016-06-03|Device for locking pivoting cowlings of a thrust reverser|
    US15/829,131| US10745140B2|2015-06-03|2017-12-01|Locking device for pivoting cowls of a thrust reverser|
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