公开(公告)号：EP3156324B1

公开(公告)日：2019-11-27

申请号：EP16193727.1

申请日：2016-10-13

申请人： Goodrich Corporation

发明人： GANIS, Rony ,  BERNARD, James ,  GIANNAKOPOULOS, Ioannis ,  CHATZI, Panagiota ,  HIGGINBOTTOM, Thomas

IPC分类号： B64C25/12 ,  B64C25/18 ,  F16J1/00 ,  F16J1/12 ,  F15B15/14 ,  F16C3/02 ,  F16C7/02

公开(公告)号：EP3546349A1

公开(公告)日：2019-10-02

申请号：EP19161475.9

申请日：2019-03-08

申请人： Rolls-Royce plc

发明人： Moxon, Matthew

IPC分类号： B64C25/12 ,  B64C1/26 ,  B64C3/16

摘要： A strut (30) for an aeroplane wing (82) comprises a first part (32) adapted to be connected at one end portion (36) to a fuselage (81) of the aeroplane (80); a second part (34) connected at a first end portion (40) to a second end portion (38) of the first part (32) and adapted to be connected at a second end portion (42) to either a wing (82), a pylon or a nacelle of the aeroplane, the second part (34) being angled to the first part (32) to define an inverted gull-strut arrangement. Either the first part (32) or the second part (34) comprises a compartment (44) to house a landing gear (31) in a folded configuration (Cl).

公开(公告)号：EP3505442A1

公开(公告)日：2019-07-03

申请号：EP17210865.6

申请日：2017-12-28

申请人： Safran Landing Systems UK Ltd

发明人： Evans, Royston Alan ,  Shaw, Paul

IPC分类号： B64C25/12 ,  B64C25/22 ,  B64C25/26 ,  B64C25/18 ,  B64C25/24

摘要： An aircraft assembly (14) comprising: a first part (18a); a second part (20b), the second part being movably mounted with respect to the first part; an electro-hydraulic actuator (42) coupled between the second part and a first anchor point (18a), the actuator comprising a cylinder defining a bore and a piston and rod assembly slidably mounted within the bore and an active chamber within which an increase in fluid pressure causes the actuator to change during a first phase between first and second extension states to move the second part relative to the first part. The electro-hydraulic actuator further comprises a hydraulic fluid supply circuit comprising a piezo-electric pump operable to supply pressurised fluid to the active chamber to change the actuator between first and second extension states.

公开(公告)号：EP3492375A1

公开(公告)日：2019-06-05

申请号：EP18208796.5

申请日：2018-11-28

申请人： Sikorsky Aircraft Corporation

发明人： SATIRA, Jason A. ,  GAYAGOY, Charles ,  ALBER, Mark R.

IPC分类号： B64C25/12

摘要： A retractable landing gear system for a vertical takeoff and landing (VTOL) aircraft includes a rotational strut rotatably coupled to a fuselage of the VTOL aircraft. The rotational strut includes a first end, a second end, and an intermediate portion extending therebetween. A drag strut includes a first end portion pivotally connected to the rotational strut and a second end portion. A locking link includes a first end section pivotally connected relative to the fuselage, a second end section pivotally connected to the drag strut and an intermediate section having a hinge element. A retraction system is operatively connected to the rotational strut and the locking link. The retraction system is operable to pivot the drag strut about a first axis and rotate the rotational strut about a second axis that is distinct from the first axis.

公开(公告)号：EP3275780B1

公开(公告)日：2019-03-13

申请号：EP17174624.1

申请日：2017-06-06

申请人： Goodrich Corporation

发明人： HIMMELMANN, Richard A.

IPC分类号： B64C25/12 ,  B64C25/20

公开(公告)号：EP3418188A1

公开(公告)日：2018-12-26

申请号：EP18177729.3

申请日：2018-06-14

申请人： Airbus Operations Limited

发明人： Sakota, Nebojsa ,  Wijker, Norman

IPC分类号： B64C25/12

CPC分类号： B64C25/12 ,  B64C2025/125

摘要： A landing gear 6 comprising a main strut 8 connected at one end to an aircraft 1 via a main joint is disclosed. The landing gear 6 further comprises an inboard sidestay assembly connected to the main strut 8. The inboard sidestay assembly comprises a forward stay 30a connected at one end to the aircraft 1, a rear stay 30b connected at one end to the fuselage, and a shear web 32 extending between the forward stay 30a and the rear stay 30b and configured to resist movement of the forward stay 30a relative to the rear stay 30b. The landing gear 6 is arranged such that when the landing gear 6 is extended substantially all the landing gear loads are transferred from the landing gear 6 to the aircraft 1 via one or more of the main joint, the forward stay 30a and the rear stay 30b.

公开(公告)号：EP3351474A1

公开(公告)日：2018-07-25

申请号：EP18151901.8

申请日：2018-01-16

申请人： Goodrich Corporation

发明人： ACKS, James ,  REBER, Korey Michael

IPC分类号： B64C25/10 ,  B64C25/12 ,  B64C25/26

摘要： A locking actuator arrangement (200) may comprise an actuator housing (230) defining a retaining cavity (238), an actuator piston (232) comprising a piston head (236) and a piston rod (234) extending from the piston head (236), a receptacle body (241) defining a receiving cavity (242), wherein the receiving cavity (242) is configured to receive at least a portion of the piston rod (234), and the piston rod (234) is configured to be received by the receiving cavity (242) in response to alignment of at least two coupled links (202, 204).

公开(公告)号：EP3127806B1

公开(公告)日：2018-05-23

申请号：EP16182411.5

申请日：2016-08-02

申请人： Goodrich Corporation

发明人： LUCE, William E.

IPC分类号： B64C25/02 ,  B64C25/12

CPC分类号： B64C25/10 ,  B64C25/02 ,  B64C25/12 ,  B64C2025/125

摘要： A landing gear is provided. The landing gear includes a composite strut tube (116) having a first lug (122a) and a second lug (122b) thereon. A first brace (112) is coupled to the composite strut tube (116) with a first two-force member (128) via the first lug (122a) and a second brace (114) is coupled to the composite strut tube (116) with a second two-force member (128) via the second lug (122b). A method for assembling the landing gear is also provided.

公开(公告)号：EP3109154A1

公开(公告)日：2016-12-28

申请号：EP15173404.3

申请日：2015-06-23

申请人： Messier-Dowty Limited

发明人： Simonneaux, Yann ,  Paddock, Andrew

IPC分类号： B64C25/12 ,  B64F5/00

CPC分类号： B64C25/10 ,  B64C25/12 ,  B64F5/10 ,  B64F5/60

摘要： A method (40) of preloading an aircraft assembly (1) involving a step of operating an extendible preloading tool (20) to move a main strut (15) to decrease the distance between first and second link attachment joints (C2, C3) for attachment of a preloading linkage (12b).

摘要翻译： 飞机组件的预加载的（1）涉及在可延伸的预加载工具（20）操作的步骤的方法，（40）来移动主支柱（15）以降低（C2，C3），用于第一和第二连杆附接关节之间的距离 预加载的联动附件（12B）。

公开(公告)号：EP2450277A2

公开(公告)日：2012-05-09

申请号：EP11250883.3

申请日：2011-11-04

申请人： Goodrich Corporation

发明人： Acks, James P. ,  Martin, Dennis

IPC分类号： B64C25/12

CPC分类号： B64C25/12 ,  B64C25/20 ,  B64C25/34 ,  B64C2025/125

摘要： A side articulating main landing gear assembly (100) for an aircraft (10) is disclosed which includes a wheel axle fitting (150) oriented in a horizontal plane when the landing gear is in an extended condition deployed from a landing gear bay (12) of the aircraft, a tire supported on the wheel axle fitting (150) and oriented in a vertical plane when the landing gear is in the extended condition, a shock absorber (120) adapted to stroke between an extended state and a compressed state upon landing the aircraft, a set of articulating links connected to the wheel axle fitting (150), the shock absorber (120) and the aircraft (10), and configured to maintain the tire (160) in a vertical plane as the shock absorber (120) strokes between the extended state and the compressed state, a set of tire planing links connected to the wheel axle fitting (150) and the articulating links (140,142,144), and configured to maintain the wheel axle fitting (150) in a horizontal plane as the shock absorber (120) strokes between the extended state and the compressed state, and a drive crank (130) connected to the shock absorber (120), the tire planing links, the articulating links (140,142,144) and the aircraft (10), for moving the landing gear assembly (100) between the extended condition and an inverted retracted condition stowed in the landing gear bay (12).

摘要翻译： 公开了一种用于飞机（10）的侧面关节式主起落架组件（100），其包括当起落架处于从起落架舱（12）展开的延伸状态时在水平面中定向的轮轴配件（150） ，当起落架处于伸展状态时，支撑在所述轮轴配件（150）上并且在垂直平面中定向的轮胎，适于在着陆时在延伸状态和压缩状态之间行进的减震器（120） 飞行器，连接到车轮轴配件（150），减震器（120）和飞行器（10）的一组铰接连杆，并且构造成将轮胎（160）保持在垂直平面中作为减震器（120 ）在延伸状态和压缩状态之间的冲程，连接到轮轴配件（150）和铰接连杆（140,142,144）的一组轮胎平整链接，并且被配置为将轮轴配件（150）保持在水平面中， 减震器（1 20）在延伸状态和压缩状态之间的行程，以及连接到减震器（120）的驱动曲柄（130），轮胎平整连杆，铰接连杆（140,142,144）和飞行器（10），用于移动着陆 齿轮组件（100）处于延伸状态和收起在起落架舱（12）中的倒置收缩状态之间。