公开(公告)号：EP1941332A1

公开(公告)日：2008-07-09

申请号：EP06826522.2

申请日：2006-10-24

申请人： THE BOEING COMPANY

发明人： ENGLUND, Norman J. ,  FINIGAN, John S.

IPC分类号： G05B19/19 ,  F16F15/027

CPC分类号： G05B19/19 ,  B64C25/22 ,  F15B2211/6336 ,  F15B2211/6656

摘要： A force compliant mechanism (750) for a force control system (600) includes a housing (752). A force compliant volute spring member (754) that has an input end (790) and an output end (792) is disposed within the housing (752). A force actuator input shaft (798) operates in response to a force induced thereon. An output shaft (800) is coupled to the output end (792) and to a test object (802). A force transducer (780) is in operative coupling with the force actuator input shaft (798) and generates a force signal in response to the induced force. A method of reducing force transients and increasing stability within a force control system (660) includes applying a force on a test object (666). A force actuator (669) is decoupled from the test object (666). The overall stiffness of the force control system is reduced and dynamic energy is absorbed via a force compliant member (662) coupled to the test object (666) and the force actuator (669).

公开(公告)号：EP1914164A1

公开(公告)日：2008-04-23

申请号：EP07291158.9

申请日：2007-09-27

申请人： MESSIER-BUGATTI

发明人： Leutard, David ,  Felemez, Eric ,  Fremiot, Sébastien

IPC分类号： B64C25/22

CPC分类号： B64C25/22 ,  F15B20/004 ,  F15B20/008 ,  F15B2211/6309 ,  F15B2211/7053 ,  F15B2211/7128 ,  F15B2211/8633 ,  F15B2211/8636 ,  F15B2211/8752

摘要： L'invention concerne une architecture de système hydraulique de manoeuvre des atterrisseurs d'un aéronef comportant au moins une source de pression et un retour hydraulique, avec un circuit hydraulique comportant une première ligne hydraulique ("DESCENTE") dont la pressurisation provoque la descente des atterrisseurs, et une deuxième ligne hydraulique ("RELEVAGE" 5) dont la pressurisation provoque le relevage des atterrisseurs, ces lignes étant sélectivement pressurisées au moyen d'un organe de distribution hydraulique (10,12) comportant au moins une vanne d'isolation (10) et un sélecteur (12) pour mettre en communication l'une des lignes avec la pression, et l'autre des lignes avec le retour. Selon l'invention, l'architecture comporte des moyens de mise au retour forcée (53) pour forcer la vanne d'isolation (10) à isoler le circuit de la pression de l'aéronef et mettre la ligne d'admission au retour.

摘要翻译： 该结构具有用于迫使隔离阀（10）将液压回路与飞行器的压力隔离并且返回在阀和选择器（12）之间延伸的进气管线（20）的继电器（53）。 压力通常通过进气管线。 电路具有下降液压管路（6），其加压引起起落架下降，以及上升液压管路（5），其加压引起齿轮的上升。 选择器通信压力之一。

公开(公告)号：EP1070110B1

公开(公告)日：2005-09-14

申请号：EP99916508.7

申请日：1999-04-08

申请人： Goodrich Corporation

发明人： LEE, Biing-Lin ,  HYUSCH, Louis, C.

IPC分类号： C10M107/50 ,  C08L83/04 ,  B01J13/00 ,  F16F9/30 ,  B64C25/58

CPC分类号： C10M107/50 ,  B64C25/22 ,  C10M2229/02 ,  C10M2229/025 ,  C10M2229/0405 ,  C10M2229/041 ,  C10M2229/0415 ,  C10M2229/042 ,  C10M2229/0425 ,  C10M2229/0435 ,  C10M2229/0445 ,  C10M2229/0455 ,  C10M2229/0465 ,  C10M2229/0475 ,  C10M2229/0485 ,  C10M2229/05 ,  C10M2229/0505 ,  C10M2229/0515 ,  C10M2229/0525 ,  C10M2229/0535 ,  C10M2229/0545 ,  C10N2220/02 ,  C10N2240/02 ,  C10N2240/04 ,  C10N2240/042 ,  C10N2240/044 ,  C10N2240/046 ,  C10N2240/08

摘要： A novel energy hydraulic media is disclosed comprising a microgel dispersion. The microgel dispersion is a Non-Newtonian fluid. This microgel dispersion is useful in devices that utilize a hydraulic fluid, such as hydraulic energy transmission systems and mechanical energy absorbing devices. Examples include hydraulic brake systems, liquid springs, and dynamic damping devices such as aircraft landing gear shock struts, car bumpers, and automobile shock absorbers. Methods of transmitting hydraulic energy and for dissipating kinetic energy using this microgel dispersion are also disclosed.

公开(公告)号：EP1064193B1

公开(公告)日：2003-08-06

申请号：EP99916147.4

申请日：1999-03-19

申请人： Goodrich Corporation

发明人： HRUSCH, Louis, C.

IPC分类号： B64C25/34 ,  B64C25/22 ,  F16F9/18 ,  F15B15/14

CPC分类号： F15B15/1409 ,  B64C25/22 ,  B64C25/34 ,  B64C25/60 ,  F16F9/18

摘要： The invention is in the field of hydraulic actuating devices for positioning aircraft landing gear components, and more particularly relates to a dual mode positioner (100) for an aircraft landing gear axle beam (12). The dual mode positioner (100) serves to position an aircraft landing gear axle beam (12) relative to an aircraft strut (14) dependent alternatively for taxi and retraction into the aircraft, and also provides a predetermined amount of damping of the axle beam (12) during taxi.

公开(公告)号：EP0884239A3

公开(公告)日：2001-03-21

申请号：EP98304589.9

申请日：1998-06-10

申请人： TEIJIN SEIKI COMPANY LIMITED

发明人： Koizumi, Takashi, c/o Teijin Seiki Co., Ltd. ,  Miyajima, Kiyoshi, c/o Teijin Seiki Co., Ltd.

IPC分类号： B64C25/22 ,  B64C25/26 ,  F15B15/18 ,  F15B15/26 ,  F15B7/00

CPC分类号： B64C25/22

摘要： A hydraulic system for retracting into and extending out of the body of an aircraft a landing gear for use in taking off and landing, comprises a housing unit (11) which has a hydraulic pump (20), a hydraulic actuator (35), a shuttle valve (42), an emergency valve (36), an actuator pressure releasing mechanism (60) and a mechanically locking mechanism (65) accommodated therein. The hydraulic actuator (35) has a piston rod assembly (36) received therein to be reciprocably moved by the hydraulic pump (20) to assume a retraction position (Pr) and an extended position (Pe). The shuttle valve (42) is movable with respect to the housing unit (11) for selectively changing the flow of the hydraulic fluid between the hydraulic pump (20) and the hydraulic actuator (35). The emergency valve (46) is movable with respect to the housing unit (11) to assume two different positions for selectively changing the flow of the hydraulic fluid between the hydraulic pump (20) and the hydraulic actuator (35) and the flow of the hydraulic pump (20) and the fluid pressure reservoir (71). The actuator pressure releasing mechanism (60) serves to release the hydraulic pressure in the hydraulic actuator (35) to allow the piston rod assembly (36) to be freely moved with respect to the housing unit (11) toward the extended position of the piston rod assembly (36). The mechanically locking mechanism (65) is provided selectively to lock the piston rod assembly (36) with the housing unit (11) and to unlock the piston rod assembly (36) from the housing unit (11) to be freely moved.

公开(公告)号：EP4393816A2

公开(公告)日：2024-07-03

申请号：EP24176460.4

申请日：2021-01-11

申请人： Goodrich Corporation

发明人： ALLEN, Jason Bradley

IPC分类号： B64C25/22

CPC分类号： B64C25/22 ,  B64D41/00 ,  B64C25/16 ,  B64C25/24 ,  Y02T50/50 ,  Y02E10/20 ,  Y02T50/80

摘要： A system for extracting energy for landing gear retraction, comprising: a first landing gear assembly including a first wheel (100); a first actuator (150;152;154;156) configured to control retraction of the first landing gear assembly; a first wheel pump (112) rotationally coupled to the first wheel, the first wheel pump comprising at least one of a first hydraulic pump or a first wheel powered electric motor, wherein the at least one of the first hydraulic pump or the first wheel powered electric motor is configured to generate an output in response to rotation of the first wheel, and wherein the output of the at least one of the first hydraulic pump or the first wheel powered electric motor is configured to actuate the first actuator; a second landing gear assembly including a second wheel; a second actuator configured to control retraction of the second landing gear assembly; and a second wheel pump rotationally coupled to the second wheel, the second wheel pump comprising at least one of a second hydraulic pump or a second wheel powered electric motor..

公开(公告)号：EP4386214A2

公开(公告)日：2024-06-19

申请号：EP24159776.4

申请日：2021-03-19

申请人： Airbus Operations Limited

发明人： KERR, Sean ,  MARLES, David ,  L'ALLIER, Paul Gordon

IPC分类号： F15B15/22

CPC分类号： B64C25/22 ,  F15B15/224 ,  F15B2211/705220130101 ,  F15B15/204 ,  F15B15/149 ,  F15B15/17 ,  F15B11/024

摘要： A single acting actuator (1) for an aircraft landing gear assembly having a piston (3) mounted in a cavity (60) and moveable relative to a housing (2) between a retracted position and an extended position, the piston dividing the cavity into first and second pressure chambers (5a, 5b). At least one of the pressure chambers is associated with first and second outlets (8a, 9a, 8b, 9b), with the actuator being arranged such that, in respect of the relative movement in which the pressure chamber is the decreasing volume pressure chamber, in a first stage of the relative movement the first and second outlets are open thereby allowing actuator fluid to flow out of the pressure chamber through the first and second outlets and in a second stage of the relative movement the second outlet is open but the first outlet is closed, thereby acting to slow the relative movement of the piston with respect to the housing.

公开(公告)号：EP3418189A1

公开(公告)日：2018-12-26

申请号：EP18179489.2

申请日：2018-06-25

申请人： Airbus Operations Limited

发明人： HOWELL, George ,  CRANE, Nicholas

IPC分类号： B64C25/22 ,  B64C25/30 ,  B64C25/42

CPC分类号： B64C25/22 ,  B64C25/30 ,  B64C25/42

摘要： Disclosed is a hydraulic system (300) for an aircraft. The hydraulic system (300) comprises a backup hydraulic pressure source (216) to provide hydraulic pressure to a brake (222) in the event of a failure condition of a primary hydraulic brake pressure source. The hydraulic system (300) also comprises a landing gear backup system to provide hydraulic pressure to enable extension and/or retraction of landing gear (100). The backup hydraulic pressure source (216) is arranged to provide hydraulic pressure to the landing gear backup system in the event of a failure condition of a primary landing gear hydraulic pressure source.

公开(公告)号：EP3336378A1

公开(公告)日：2018-06-20

申请号：EP16205169.2

申请日：2016-12-19

申请人： Safran Landing Systems UK Ltd

发明人： SIMONNEAUX, Yann

IPC分类号： F16F9/36 ,  B64C25/60

CPC分类号： F15B15/1461 ,  B64C25/22 ,  B64C25/58 ,  B64C25/60 ,  F15B15/1438 ,  F15B15/1476 ,  F16F9/06 ,  F16F9/36

摘要： A centre seeking actuator (10) comprising: an outer cylinder (102); a slave cylinder (14) slidably disposed within the outer cylinder; a rod assembly (120, 122), the piston (122) of which is slidably disposed within the slave cylinder and the rod (120) of which extends from the outer cylinder; one or more first dynamic seals (121) arranged to act on a side wall of the rod to inhibit working fluid leaking from the outer cylinder; and one or more second dynamic seals (12) arranged to act on a sidewall of the slave cylinder to inhibit working fluid leaking from the outer cylinder.

公开(公告)号：EP3241744A1

公开(公告)日：2017-11-08

申请号：EP16752174.9

申请日：2016-01-14

申请人： Sumitomo Precision Products Co., Ltd.

发明人： HAGIHARA, Shogo

IPC分类号： B64C25/26 ,  B64C25/22 ,  B64C25/24 ,  F15B11/028 ,  F15B11/04

CPC分类号： B64C25/22 ,  B64C25/24 ,  B64C25/26 ,  F15B11/028 ,  F15B11/04

摘要： An electro-hydrostatic actuator system (1) for raising/lowering a landing gear (11) of an aircraft includes: at least one hydraulic actuator (21, 22) configured to retract and extend the landing gear (11); a hydraulic circuit (33); a hydraulic pump (32); an electric motor (31); a controller (4) configured to control the operation of the electric motor at receiving a command to retract or extend the landing gear; and a sensor (34) detecting the discharge pressure of the hydraulic pump. The controller, when receiving the command, feeds back the discharge pressure detected by the sensor, and controls the operation of the electric motor such that the discharge pressure of the hydraulic pump reaches a target discharge pressure.

摘要翻译： 一种用于升起/降低飞行器的起落架（11）的电动 - 静压致动器系统（1），包括：至少一个液压致动器（21,22），其被配置为缩回并且延伸起落架（11）; 一个液压回路（33）; 一个液压泵（32）; 电动机（31）; 控制器（4），所述控制器（4）被配置为在接收命令以缩回或延伸所述起落架时控制所述电动机的操作; 和检测液压泵的排出压力的传感器（34）。 当接收到该指令时，控制器反馈传感器检测到的排出压力，并且控制电动机的操作，使得液压泵的排出压力达到目标排出压力。