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31. 发明申请

US20160281826A1 LOWER ATTACHMENT FOR TRIMMABLE HORIZONTAL STABILISER ACTUATOR 审中-公开
标题翻译：降低水平稳定器执行器的附着力
公开(公告)号：US20160281826A1
公开(公告)日：2016-09-29
申请号：US15080791
申请日：2016-03-25
申请人： Goodrich Actuation Systems SAS
发明人： Raphael Medina , Anh-Vu Abdul-Bari
IPC分类号： F16H25/20 , B64C5/10 , B64C13/28 , F16H25/22 , F16H25/24
CPC分类号： F16H25/2204 , B64C5/10 , B64C13/28 , B64C13/341 , F16H25/205 , F16H25/2454 , F16H25/2472
摘要： A lower attachment system for a trimmable horizontal stabiliser actuator (THSA) includes a screwshaft forming a part of or coupled to a main screw of the actuator, the screwshaft having an axial direction and a primary ballnut disposed on the screwshaft and forming a part of a primary load path of the lower attachment system. The THSA also includes a lower secondary nut and an upper secondary nut as well as a secondary connection arranged for axial and rotational movement and coupled to each of the lower secondary nut and the upper secondary nut. The secondary connection is arranged to be loaded when the secondary load path is loaded and the secondary load path also includes the upper and lower secondary nuts.
摘要翻译：用于可调整水平稳定器致动器（THSA）的下部附接系统包括形成致动器的主螺杆的一部分或联接到致动器的主螺杆的螺钉轴，所述螺杆轴具有轴向方向和设置在螺钉轴上的主要球轴并形成下连接系统的主负载路径。 THSA还包括下部次级螺母和上部次级螺母以及被布置成用于轴向和旋转运动并且连接到每个下部次级螺母和上部次级螺母的次级连接件。次级连接被布置成在加载次级负载路径时被加载，并且次级负载路径还包括上部和下部次级螺母。

32. 发明申请

US20160280356A1 UPPER ATTACHMENT FOR TRIMMABLE HORIZONTAL STABILISER ACTUATOR 审中-公开
标题翻译：用于可逆式水平稳定器执行器的上装
公开(公告)号：US20160280356A1
公开(公告)日：2016-09-29
申请号：US15080813
申请日：2016-03-25
申请人： Goodrich Actuation Systems SAS
发明人： Raphael Medina , Anh-Vu Abdul-Bari
IPC分类号： B64C5/10 , F16H25/24 , F16H25/22 , B64C5/02 , B64C9/02
CPC分类号： B64C5/10 , B64C5/02 , B64C9/02 , B64C13/28 , F16H25/205 , F16H25/2204 , F16H25/2209 , F16H25/2454 , F16H2025/2037
摘要： An upper attachment system for a trimmable horizontal stabiliser actuator (THSA) comprises: a housing, holding a yoke and a ballscrew; a nut coupled to the housing and cooperating with the ballscrew such that rotation of the ballscrew relative to the nut results in linear motion of the ballscrew; a recess formed between the yoke and the ballscrew and arranged to receive, in use, an upper part of a tie bar of the secondary load path of the actuator; and a biasing mechanism arranged such that, in use, when no axial load is applied to the tie bar, the yoke and the ballscrew are held by balanced forces from the biasing mechanism in a position within the recess.
摘要翻译：用于可调整水平稳定器致动器（THSA）的上部附接系统包括：壳体，保持轭和滚珠丝杠; 螺母，其联接到壳体并与滚珠丝杠配合，使得滚珠丝杠相对于螺母的旋转导致滚珠丝杠的直线运动; 形成在所述轭和所述滚珠丝杠之间并设置成在使用中接收所述致动器的次级负载路径的连杆的上部的凹部; 以及偏置机构，其被设置为使得在使用中，当没有轴向载荷施加到拉杆上时，轭和滚珠丝杠通过来自偏置机构的平衡力保持在凹部内的位置。

33. 发明授权

US09434468B2 Wing control system 有权
标题翻译：翼控系统
公开(公告)号：US09434468B2
公开(公告)日：2016-09-06
申请号：US13817987
申请日：2011-07-14
申请人： Louwrens Hermias Van Zyl
发明人： Louwrens Hermias Van Zyl
IPC分类号： B64C13/28 , B64C13/34 , B64C9/00
CPC分类号： B64C13/34 , B64C9/00 , B64C13/28
摘要： The invention provides a wing control system aimed at countering the aeroelastic effect of twisting of a length of wing of an aircraft due to dynamic air pressure acting on an aileron of the wing. The wing control system includes a shaft extending along the length of wing and actuation means responsive to aileron control inputs to induce a variable torque T in the shaft. Outboard of the length of wing, the system operatively transfers T partially to the aileron to pivot the aileron and partially to the wing at an outboard end of the length of wing to counter twisting of the length of wing due to dynamic air pressure on the aileron. Inboard of the length of wing, the system operatively transfers T to the aircraft, e.g. to its fuselage, thereby effectively balancing the sum of the moments transferred respectively to the aileron and the wing.
摘要翻译：本发明提供了一种机翼控制系统，其旨在抵抗由于作用在机翼的副翼上的动态空气压力而使飞机机翼长度的扭转的气动弹性效应。机翼控制系统包括沿着翼的长度延伸的轴和响应于副翼控制输入以在轴中感应可变转矩T的致动装置。在机翼长度的外侧，系统可操作地将T部分地转移到副翼以使副翼枢转，并且在机翼长度的外侧端部分地转向机翼，以抵抗由于副翼上的动态空气压力引起的机翼长度的扭转。在翼的长度的内侧，系统可操作地将T传送到飞机，例如，到机身，从而有效地平衡了分别转移到副翼和机翼的时刻的总和。

34. 发明申请

US20160194075A1 Apparatus and Method for Arrestment of a Flight Control Surface 有权
标题翻译：用于控制飞行控制面的装置和方法
公开(公告)号：US20160194075A1
公开(公告)日：2016-07-07
申请号：US14299625
申请日：2014-06-09
申请人： The Boeing Company
发明人： Lior Ungar , Randall E. Anderson , Sergey N. Skobyak
IPC分类号： B64C13/28 , F16H21/44 , B64C9/00
CPC分类号： B64C13/28 , B64C9/00 , B64C13/42 , F16H21/44
摘要： A secondary actuation mechanism for arresting movement of a control surface may include a secondary actuator, a drive link coupled to the secondary actuator, and a secondary connecting rod coupled between the drive link and the control surface, wherein the control surface is movable to a default position in response to actuation of the secondary actuator, and the secondary actuator retains the control surface at the default position
摘要翻译：用于阻止控制表面的运动的辅助致动机构可以包括辅助致动器，联接到次级致动器的驱动连杆以及耦合在驱动连杆和控制表面之间的辅助连接杆，其中控制表面可移动到默认响应于辅助致动器的致动而位置，并且次级致动器将控制表面保持在默认位置

35. 发明申请

US20160152322A1 MULTI-SLICE ROTARY ELECTROMECHANICAL ACTUATOR 有权
标题翻译：多级旋转电动执行器
公开(公告)号：US20160152322A1
公开(公告)日：2016-06-02
申请号：US14558012
申请日：2014-12-02
申请人： Hamilton Sundstrand Corporation
发明人： Derick S. Balsiger , Nicholas R. Van De Veire
IPC分类号： B64C13/28 , H02K7/10
CPC分类号： B64C13/28 , B64C9/00 , B64C13/50 , B64C2009/005 , H02K7/14 , H02K16/02 , H02K41/06
摘要： A multi-slice electromechanical hinge-line rotary actuator includes a motor stator configured to generate rotational motion about a rotational axis. The multi-slice electromechanical hinge-line rotary actuator further includes a plurality of layers rotatably coupled to the motor stator. Each layer includes an output arm slice configured to rotate about the rotational axis in response to the rotational motion.
摘要翻译：多切片机电铰链旋转致动器包括被配置为产生围绕旋转轴线的旋转运动的马达定子。多切片机电铰链旋转致动器还包括可旋转地联接到电动机定子的多个层。每个层包括输出臂切片，其配置成响应于旋转运动围绕旋转轴线旋转。

36. 发明授权

US09352825B2 Aircraft 有权
标题翻译：飞机
公开(公告)号：US09352825B2
公开(公告)日：2016-05-31
申请号：US14341033
申请日：2014-07-25
申请人： Liebherr-Aerospace Lindenberg GmbH
发明人： Bernhard Hauber
IPC分类号： B64C13/42 , B64C13/34 , B64C13/36 , B64C13/50 , B64C13/28 , B64C3/38 , B64C9/02
CPC分类号： B64C13/34 , B64C3/38 , B64C9/02 , B64C13/28 , B64C13/36 , B64C13/42 , B64C13/50
摘要： The invention relates to an aircraft having at least one high lift system which is arranged at the wing of the aircraft and which comprises a drive for converting electrical or hydraulic energy into a speed-controlled rotational movement, wherein the aircraft furthermore has at least one control unit which controls the high lift system, wherein the drive comprises in accordance with the invention a main drive and an alternative drive, wherein the alternative drive is fed by a decentralized energy source.
摘要翻译：本发明涉及一种具有至少一个高升程系统的飞行器，其布置在飞行器的机翼处，并且包括用于将电能或液压能量转换成速度控制的旋转运动的驱动器，其中飞机还具有至少一个控制控制高升程系统的单元，其中驱动器根据本发明包括主驱动器和替代驱动器，其中替代驱动器由分散的能源馈送。

37. 发明授权

US09347535B1 Fault tolerant electro-mechanical acutator 有权
标题翻译：容错机电式电动机
公开(公告)号：US09347535B1
公开(公告)日：2016-05-24
申请号：US13932253
申请日：2013-07-01
申请人： The Boeing Company
发明人： James L. Sheahan, Jr. , Chalres E. Morris , David E. Blanding , James L. Peck, Jr.
IPC分类号： F16H25/20
CPC分类号： F16H25/20 , B64C13/28 , F16D11/16 , F16D28/00 , F16D2023/123 , F16H2025/2071 , F16H2025/2081 , Y10T74/186 , Y10T74/18696 , Y10T74/18704 , Y10T74/19735
摘要： An electromechanical actuator incorporates a drive housing connected to a motor for rotational motion. A screw is employed with an actuating nut having protruding engagement bosses and a drive coupling is concentrically received within the drive housing having segments equal to the number of engagement bosses. Each segment has a cavity to receive a respective one of the engagement bosses and the segments are cooperatively positionable from an active position radially compressed to engage the bosses within the cavities to a released position radially expanded to disengage the bosses from the cavities.
摘要翻译：机电致动器包括连接到电动机用于旋转运动的驱动壳体。使用具有突出接合凸台的致动螺母的螺钉，并且驱动联接器同心地容纳在驱动器壳体内，其具有等于接合凸起的数量的段。每个段具有用于接收相应的一个接合凸台的空腔，并且所述段可从径向压缩的有源位置配合定位以将空腔内的凸起接合到径向扩张的释放位置以使凸起与空腔脱离。

38. 发明申请

US20160129990A1 ROTARY ACTUATOR FOR CONTROLLING A FLIGHT CONTROL SURFACE 审中-公开
标题翻译：用于控制飞行控制面的旋转执行机构
公开(公告)号：US20160129990A1
公开(公告)日：2016-05-12
申请号：US14933016
申请日：2015-11-05
申请人： GOODRICH ACTUATION SYSTEMS SAS
发明人： Laurent Schwartz
IPC分类号： B64C13/28
CPC分类号： B64C13/28 , F16H35/10 , F16H2035/005
摘要： A rotary actuator for controlling a flight control surface and a flight control surface actuation assembly including the rotary actuator. The actuator comprises a rotary output shaft for driving a flight control surface, a locking mechanism for selectively preventing rotation of the rotary output shaft and a torque limiter for allowing the locking mechanism to be bypassed upon the locking mechanism experiencing a torque above a predetermined limit.
摘要翻译：用于控制飞行控制表面的旋转致动器和包括旋转致动器的飞行控制表面致动组件。致动器包括用于驱动飞行控制表面的旋转输出轴，用于选择性地防止旋转输出轴的旋转的锁定机构和用于允许锁定机构在经历超过预定极限的转矩的锁定机构旁路的扭矩限制器。

39. 发明申请

US20160104331A1 METHODS AND APPARATUS FOR OPERATING FLIGHT CONTROL SYSTEMS OF AIRCRAFTS 有权
标题翻译：运行飞机飞行控制系统的方法和装置
公开(公告)号：US20160104331A1
公开(公告)日：2016-04-14
申请号：US14511036
申请日：2014-10-09
申请人： The Boeing Company
发明人： Neal V. Huynh , Robert S. Eick , Thomas G. Heineman , Michael D. Bills , Patrick M. Fahey , John C. Nicholas
IPC分类号： G07C5/08 , B64C13/50 , B64C13/28 , B64C13/16
CPC分类号： G07C5/0808 , B64C13/10 , B64C13/16 , B64C13/28 , B64C13/503 , B64D45/00 , B64D2045/001 , B64D2045/0085 , Y02T50/44
摘要： Methods and apparatus for operating flight control systems of aircrafts are disclosed. An example apparatus includes a flight control system including a first sensor and a second sensor. The example apparatus also includes a processor to, based on data from the first and second sensors, determine first and second input values and, based the input values, determine an approximate location of a jam in the flight control system of an aircraft.
摘要翻译：公开了飞机运行飞行控制系统的方法和装置。一种示例性装置包括包括第一传感器和第二传感器的飞行控制系统。示例性装置还包括处理器，其基于来自第一和第二传感器的数据确定第一和第二输入值，并且基于输入值确定飞行器的飞行控制系统中的卡纸的大致位置。

40. 发明授权

US09261150B2 Drive system for a high lift system of an aircraft and method for detecting a misalignment between a transmission shaft and an opening in a drive system for a high lift system of an aircraft 有权
标题翻译：用于飞机高升力系统的驱动系统和用于检测传动轴与用于飞机高升力系统的驱动系统中的开口之间的未对准的方法
公开(公告)号：US09261150B2
公开(公告)日：2016-02-16
申请号：US14269331
申请日：2014-05-05
申请人： Airbus Operations GmbH
发明人： Mark Heintjes
IPC分类号： F16D43/02 , B64C13/28 , B64D45/00
CPC分类号： F16D43/02 , B64C13/28 , B64D2045/001
摘要： An arresting apparatus for arresting a rotational motion of two components relative to each other is provided. The arresting apparatus includes a first arresting means having a longitudinal axis and at least one first engaging element, and a second arresting means having an opening and at least one second engaging element. In a first mode of operation, the first arresting means extends through a first section of the opening of the second arresting means such that it is freely rotatable and the first engaging element and the second engaging element are distanced from each other. In a second mode of operation, the first arresting means is misaligned and extends through a second section of the opening of the second arresting means such that the first engaging element and the second engaging element engage and arrest the first arresting means relative to the second arresting means.
摘要翻译：提供了用于阻止两个部件相对于彼此的旋转运动的止动装置。止动装置包括具有纵向轴线和至少一个第一接合元件的第一止动装置和具有开口和至少一个第二接合元件的第二止动装置。在第一操作模式中，第一止动装置延伸穿过第二止动装置的开口的第一部分，使得其可自由旋转，并且第一接合元件和第二接合元件彼此远离。在第二操作模式中，第一止动装置不对准并且延伸穿过第二止动装置的开口的第二部分，使得第一接合元件和第二接合元件相对于第二止动装置接合并阻止第一止动装置手段。

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