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1. 发明申请

WO2018095934A1 ACTIONNEUR À MONTAGE FACILITÉ 审中-公开
公开(公告)号：WO2018095934A1
公开(公告)日：2018-05-31
申请号：PCT/EP2017/079978
申请日：2017-11-21
申请人： SAFRAN ELECTRONICS & DEFENSE
发明人： MERCIER, Guillaume , MEHEZ, Jérôme , BEZIVIN, Philippe
IPC分类号： B64C13/34 , B64C13/38
摘要： Actionneur (10) pour au moins une surface mobile de vol (3.1, 3.2, 4.1, 4.2) d' un aéronef, comprenant au moins deux organes d' actionnement (30) de la surface mobile de vol entre deux positions extrêmes et un moteur (20 ) relié aux organes d' actionnement par au moins une ligne de transmission de mouvement rotatif, chaque organe d' actionnement comprend un pignon d'entraînement (31.1, 31.2) et l' actionneur étant agencé pour que la ligne de transmission ait une amplitude angulaire de moins d'un tour lors du déplacement de la surface mobile de vol entre ses deux positions et la ligne de transmission de mouvement est agencé pour autoriser une position angulaire unique entre les pignons d'entraînement de l'organe d' actionnement.

2. 发明申请

WO2009065597A4 LANDING FLAP MECHANISM DRIVEN BY PINION GEARS 审中-公开
标题翻译：通过SPROCKET DRIVE驱动的LANDEKLAPPENKINEMATIK
公开(公告)号：WO2009065597A4
公开(公告)日：2009-08-06
申请号：PCT/EP2008009884
申请日：2008-11-21
申请人： AIRBUS GMBH , GARTELMANN RAINER
发明人： GARTELMANN RAINER
IPC分类号： B64C9/16 , B64C9/20 , B64C13/34 , B64C13/38
CPC分类号： B64C9/20 , B64C9/16
摘要： The invention relates to a device for moving a trailing edge flap (10) on an aircraft wing (2), wherein the trailing edge flap comprises one or more flap segments (4, 6, 8), a first flap segment (4) being movably mounted on the wing (2) and connected to a first toothed moving element (22) driven by a first pinion (16).
摘要翻译：本发明涉及一种装置，用于移动飞机机翼（2）的后缘襟翼（10），具有在该后缘襟翼，一个或多个折板段（4,6，8），其特征在于，第一翼片部分（4）可动上窗框（2）存储和连接到由第一小齿轮（16）移动的第一带齿的移动元件（22）。

3. 发明申请

WO2013007987A3 LEADING EDGE RIB ASSEMBLY 审中-公开
公开(公告)号：WO2013007987A3
公开(公告)日：2013-01-17
申请号：PCT/GB2012/051581
申请日：2012-07-06
申请人： AIRBUS OPERATIONS LIMITED , TOPPING, Simon , PAYNE, Christopher , WILLIAMS, Llifon , MAYNEORD, Martin , BELFOURD, David , HUE, Xavier , AIRBUS OPERATIONS GMBH
发明人： TOPPING, Simon , PAYNE, Christopher , WILLIAMS, Llifon , MAYNEORD, Martin , BELFOURD, David , HUE, Xavier
IPC分类号： B64C9/24 , B64C9/22 , B64C13/34
摘要： An aircraft wing comprising a main wing element with a spar and a leading edge rib (4a, 5a, 6a) which is supported by the spar and extends forward of the spar; a high lift device (10) which is movably mounted to the main wing element; and an actuation mechanism comprising a drive shaft (20a, 20b) and a gear train. The gear train comprising a drive cog (21) which is carried by the drive shaft, an actuator cog (22) which is coupled to the high lift device, and one or more intermediate cogs (23-29) which are mounted to the rib (4a, 5a, 6a) and coupled in series with the drive cog (21) and the actuator cog (22) so as to transmit torque from the drive cog (21) to the actuator cog (22) which moves the high lift device (10) between a retracted position and an extended position in which the high lift device increases the camber of the wing. The sizes of the cogs in the gear train are selected so that the drive shaft (20a, 20b) rotates at a higher rate than the high lift device.

4. 发明申请

WO2012045796A1 HIGH-LIFT SYSTEM FOR A WING OF AN AIRCRAFT 审中-公开
标题翻译：飞机高空作战系统
公开(公告)号：WO2012045796A1
公开(公告)日：2012-04-12
申请号：PCT/EP2011/067422
申请日：2011-10-05
申请人： AIRBUS OPERATIONS GMBH , WINKELMANN, Christoph
发明人： WINKELMANN, Christoph
IPC分类号： B64C13/34 , B64D45/00
CPC分类号： B64C13/34 , B64D45/0005 , B64D2045/001 , Y02T50/44
摘要： A high-lift system (2) for a wing (6) of an aircraft comprises movably held high-lift flaps (4), at least one drive unit (20), at least one transmission shaft (8) connected to the drive unit, and several actuator devices (12a-121), distributed on the transmission shaft and connected to the high- lift flaps, for moving the high- lift flaps. The actuator devices each comprise a driven element (14a- 141) and a torque limiting means (13). According to the invention the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with the use of a separate torque transmitting means (16a-16d, 19a-19b). If one actuator device is blocked, for example as a result of a defective tooth arrangement or some other defect, the torque to be produced by the intact actuator device increases and triggers its torque limiting means. This ensures synchronous operation and in the case of malfunction prevents damage to or detachment of a flap.
摘要翻译：一种用于飞机机翼（6）的高升力系统（2）包括可移动地保持的高升力翼片（4），至少一个驱动单元（20），至少一个传动轴（8），连接到驱动单元和多个致动器装置（12a-121），其分布在传动轴上并且连接到高升降翼板上，用于移动高提升襟翼。致动器装置各自包括从动元件（14a- 141）和扭矩限制装置（13）。根据本发明，两个相邻致动器装置的从动元件以非旋转方式与单独的扭矩传递装置（16a-16d，19a-19b）相互连接。如果一个致动器装置被阻挡，例如由于缺陷齿布置或某些其它缺陷，则由完整致动器装置产生的扭矩增加并触发其转矩限制装置。这样可以确保同步运行，并且在故障的情况下，可防止挡板的损坏或拆卸。

5. 发明申请

WO2010026410A2 SLAT SUPPORT ASSEMBLY 审中-公开
标题翻译： SLAT支持组件
公开(公告)号：WO2010026410A2
公开(公告)日：2010-03-11
申请号：PCT/GB2009/051078
申请日：2009-08-27
申请人： AIRBUS OPERATIONS LIMITED , PARKER, Simon, John
发明人： PARKER, Simon, John
IPC分类号： B64C9/02 , B64C9/22 , B64C13/34
CPC分类号： B64C9/22 , B64C9/02 , B64C13/34 , Y02T50/44
摘要： A slat support assembly is disclosed. It comprises a slat support arm having a plurality of bearing surfaces extending along its length, the slat support arm being movable to deploy a slat attached to one end of said slat support arm from a leading edge of an aircraft wing, and a plurality of bearings mountable within the wing, each bearing being in rolling contact with an associated bearing surface to support the slat support arm and guide it during deployment and retraction of the slat. At least some of the bearing surfaces and associated bearings are configured so that each bearing counteracts load applied to the slat support arm in more than one direction.
摘要翻译：公开了一种板条支撑组件。它包括具有沿其长度延伸的多个轴承表面的板条支撑臂，所述板条支撑臂可移动以展开从所述板条支撑臂的一端附接到飞机机翼的前缘的多个轴承可安装在机翼内，每个轴承与相关联的轴承表面滚动接触，以支撑板条支撑臂，并在板条的展开和缩回期间引导它们。至少一些轴承表面和相关联的轴承被构造成使得每个轴承抵抗沿多于一个方向施加到板条支撑臂的负载。

6. 发明申请

WO2004092520A3 ARRANGEMENT AND ASSOCIATED SYSTEM HAVING AN ACTUATOR AND A TUBULAR FLAP-DRIVE MEMBER ABOUT THE ACTUATOR 审中-公开
标题翻译：具有执行机构的安排和相关系统以及关于执行器的管状翼片驱动器
公开(公告)号：WO2004092520A3
公开(公告)日：2004-12-09
申请号：PCT/US2004011301
申请日：2004-04-13
申请人： CURTISS WRIGHT CONTROLS INC , MAYER EDWARD , DEGENHOLTZ ARTHUR , VAGHELA NARESH P
发明人： MAYER EDWARD , DEGENHOLTZ ARTHUR , VAGHELA NARESH P
IPC分类号： B64C9/02 , B64C13/34 , B64C13/50 , B64C9/00 , B64C3/58
CPC分类号： B64C13/50 , B64C9/02 , B64C13/34
摘要： An arrangement, and an associated system, in which an actuator is utilized to move a flap. Within the arrangement, an actuator conveys motive force from a motor to cause movement of the flap relative to a supporting structure. A tube of the arrangement is operatively connected to the actuator and movable relative to the support structure in response to motive force conveyed by the actuator. The tube is for operative connection to the flap and is for moving of the flap. The actuator is located radially within an envelope of the tube. Within the system, a controller controls the motor.
摘要翻译：一种布置和相关联的系统，其中致动器用于移动翼片。在该布置中，致动器传递来自马达的动力以引起翼片相对于支撑结构的运动。该装置的管可操作地连接到致动器并且响应于由致动器传送的动力而相对于支撑结构可移动。该管用于与翼片的操作连接并且用于移动翼片。致动器径向位于管的外壳内。在系统内，控制器控制电机。

7. 发明申请

WO99018367A1 LOAD LIMITER 审中-公开
标题翻译：负载限制
公开(公告)号：WO99018367A1
公开(公告)日：1999-04-15
申请号：PCT/US1998/020694
申请日：1998-10-01
IPC分类号： B64C13/34 , F16H1/16 , F16H25/20 , F16H35/10
CPC分类号： F16H35/10 , B64C13/34 , F16H1/16 , F16H25/2021 , Y02T50/44 , Y10T74/18792
摘要： A load limiter for preventing stall torque from being transmitted from a power drive unit to the flight control surfaces of an aircraft. The present invention provides such a load limiter in a package having lower weight and smaller spacial requirements than has been heretofore possible. The power drive unit of the aircraft generates torque which is transmitted from a rotating input shaft (24) to a worm gear (32), to a helical gear (38), to a ball screw, and to the flight control surface of the aircraft. If the flight control surface becomes jammed or otherwise prevented from movement, the ball screw, and consequently the helical gear (38), stop rotating. However, the stall torque of the power drive unit will continue to cause the input shaft (24) to rotate, which will in turn cause the worm gear (32) to rotate and interact with the helical gear (38). Since the helical gear (38) cannot move, the helical gear (38) will cause the worm gear (32) to axially translate relative to the input shaft (24). The worm gear (32) is normally prevented from such movement by compression and tension springs (58, 60) laterally flanking the worm gear (32), but by sizing the springs (58, 60) to be overcome by the level of the stall torque, one of the springs (58, 60) depending on the direction of rotation of the input shaft (24), will compress to allow the worm gear (32) to axially move and thus cause a toothed plate (44) attached to the worm gear (32) to engage a mating toothed plate (50, 52) fixed to the actuator housing. The engaged plates therefore ground the stall torque to the housing to prevent damage to the flight control surface and its transmission. The load limiter is disengaged by reversing the direction of rotation of the input shaft (24).
摘要翻译：用于防止失速扭矩从动力驱动单元传递到飞机的飞行控制表面的负载限制器。本发明提供了一种具有比以前更小的重量和更小的空间要求的包装中的这种负载限制器。飞行器的动力驱动单元产生从旋转输入轴（24）传递到蜗轮（32）到斜齿轮（38）到滚珠丝杠和飞行器飞行控制表面的扭矩。如果飞行控制表面卡住或以其他方式阻止运动，则滚珠丝杠以及因此的斜齿轮（38）停止转动。然而，动力驱动单元的失速转矩将继续导致输入轴（24）旋转，这又将导致蜗轮（32）旋转并与斜齿轮（38）相互作用。由于斜齿轮（38）不能移动，斜齿轮（38）将使蜗轮（32）相对于输入轴（24）轴向平移。蜗杆（32）通常通过横向于蜗轮（32）侧面的压缩和拉伸弹簧（58,60）而不受这种运动的限制，而是通过使弹簧（58,60）的尺寸调整以克服档位的水平扭矩，根据输入轴（24）的旋转方向的一个弹簧（58,60）将被压缩，以允许蜗轮（32）轴向移动，从而导致附接到该齿轮的齿板（44）蜗轮（32）接合固定到致动器壳体上的配合齿板（50,52）。因此，接合板将失速扭矩接地到外壳上，以防止飞行控制表面及其传动损坏。负载限制器通过反转输入轴（24）的旋转方向而脱离。

8. 发明申请

WO98042567A1 AIRCRAFT SPOILER BLOW-DOWN MECHANISM 审中-公开
标题翻译：飞机搅拌机吹瓶机
公开(公告)号：WO98042567A1
公开(公告)日：1998-10-01
申请号：PCT/US1998/002200
申请日：1998-02-04
IPC分类号： B64C13/34
CPC分类号： B64C13/34 , Y10T74/18576
摘要： An electrical mechanical blow-down mechanism for use with an aircraft spoiler avoids possible damage due to high inertial loading when a power failure occurs as the spoiler (10) is moving toward or is at an extended position by means of a structure including a ball screw mechanism (18) adapted to be connected to the spoiler (10) and including an input gear (34) adapted for rotation about an axis (36). The mechanism is ultimately driven by an electrical motor (20) having a rotary output (22) with at least one gear (26, 28) interconnecting the input gear (34) and the rotary output (22). A pawl (36) is mounted for movement between positions engaged with and disengaged from the input gear (34) and a spring (78) is utilized to normally bias the pawl (36) toward the engaged position. A solenoid (50) is operable to move the pawl (36) against the spring (78) toward the disengaged position and a motion sensor (90) is associated with the input gear (34) to determine the direction of rotation thereof. A latch (42, 106) is provided for holding the pawl (36) in the disengaged position for one direction of movement of the input gear (34) and releasing the pawl (36) for the other direction of rotation of the input gear (34). Motion sensor (90) controls movement of latch (42, 106) to prevent pawl (36) engagement after a power failure until such engagement will not damage the spoiler actuator.
摘要翻译：与飞机扰流板一起使用的电气机械排气机构当由于扰流器（10）通过包括滚珠丝杠的结构朝向或处于延伸位置而发生停电时，避免了由于高惯性载荷引起的可能的损坏机构（18）适于连接到扰流板（10）并且包括适于围绕轴线（36）旋转的输入齿轮（34）。该机构最终由具有连接输入齿轮（34）和旋转输出（22）的至少一个齿轮（26,28）的旋转输出（22）的电动机（20）驱动。安装棘爪（36）以在与输入齿轮（34）接合和分离的位置之间移动，并且弹簧（78）用于将棘爪（36）朝向接合位置正常地偏置。螺线管（50）可操作以将棘爪（36）抵靠弹簧（78）移向分离位置，并且运动传感器（90）与输入齿轮（34）相关联以确定其旋转方向。提供一个闩锁（42,106），用于将棘爪（36）保持在分离位置，用于输入齿轮（34）的一个运动方向，并释放用于输入齿轮的另一个旋转方向的棘爪（36） 34）。运动传感器（90）控制闩锁（42,106）的运动，以防止在停电之后的棘爪（36）接合，直到这种接合不会损坏扰流器致动器。

9. 发明申请

WO2020254560A1 ACTUATION UNIT FOR ACTUATING A FOLDABLE WING TIP PORTION OF A WING FOR AN AIRCRAFT 审中-公开
公开(公告)号：WO2020254560A1
公开(公告)日：2020-12-24
申请号：PCT/EP2020/067073
申请日：2020-06-19
申请人： AIRBUS OPERATIONS GMBH
发明人： LORENZ, Christian
IPC分类号： B64C3/56 , B64C9/00 , B64C23/06 , B64C13/34 , F16H19/04
摘要： Disclosed is an actuation unit (15) for actuating a foldable wing tip portion (9) of a wing (3) for an aircraft (1), the actuation unit (15) comprising a motor (17) configured to be mounted to a fixed wing (5) for an aircraft (1), a drive pinion (19) driven rotationally by the motor (17), a first rack (21) configured to be mounted to the fixed wing (5), a second rack (23) configured to be mounted to the foldable wing tip portion (9), a third rack (25) configured to be mounted to the fixed wing (5) movably along a defined first movement path (31) and drivingly engaged by the drive pinion (19), and a transfer pinion (27) mounted to the third rack (25) rotatably about an axis of rotation (33) extending perpendicular to the first movement path (31), wherein the first rack (21) engages the transfer pinion (27) at a first side (37) and the second rack (23) engages the transfer pinion (27) at an opposite second side (39) of the transfer pinion (27), such that, when the drive pinion (19) drives the third rack (25) along the first movement path (31), the transfer pinion (27) drives the second rack (23) along a second movement path (41).

10. 发明申请

WO2019139654A1 DUAL RACK AND PINION ROTATIONAL INERTER SYSTEM AND METHOD FOR DAMPING MOVEMENT OF A FLIGHT CONTROL SURFACE OF AN AIRCRAFT 审中-公开
公开(公告)号：WO2019139654A1
公开(公告)日：2019-07-18
申请号：PCT/US2018/055361
申请日：2018-10-11
申请人： THE BOEING COMPANY
发明人： FOX, Michael Thomas , ROACH, Jeffrey Michael , HOWELL, Eric Anton
IPC分类号： B64C9/02 , B64C13/34 , F16F7/10 , B64C13/40
CPC分类号： B64C9/02 , B64C13/34 , B64C13/40 , F16F7/1022 , F16F9/12 , F16F2232/06
摘要： There is provided a dual rack and pinion rotational inerter system (500) for damping movement (694) of a flight control surface (122) of an aircraft (100). The system (500) has a flexible holding structure (506) disposed between the flight control surface (122) and a support structure (116) of the aircraft (100). The system (500) has a dual rack and pinion assembly (550) held by and between the flexible holding structure (506). The dual rack and pinion assembly (550) has a first rack (552a), a second rack (552b), and a pinion (596) engaged to and between the racks (552a, 552b). The system (500) has a first terminal (502) coupled to the first rack (552a) and coupled to the flight control surface (122), via a pivot element (127), and a second terminal (503) coupled to the second rack (552b), and coupled to the support structure (116). The system (500) has a pair of inertia wheels (660) adjacent the flexible holding structure (506). The system (500) has an axle element (612) inserted through the inertial wheels (660), the flexible holding structure (506), and the pinion (596).

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