公开(公告)号：US20170218928A1

公开(公告)日：2017-08-03

申请号：US15009223

申请日：2016-01-28

申请人： The Boeing Company

发明人： Morteza Safai ,  Kimberly D. Meredith

IPC分类号： F03G7/06 ,  F16G1/20 ,  G05D23/275 ,  B64C13/30

CPC分类号： F03G7/065 ,  B64C13/30 ,  F16G1/20 ,  G05D23/27535

摘要： Described herein is a motor comprising a first rotatable member and an anchor, spaced apart from the first rotatable member. The motor also comprises a belt, in tension about the first rotatable member and the anchor. The belt is co-rotatably engaged with the first rotatable member. Further, the belt is made from a shape-memory alloy. Additionally, the motor comprises a thermal regulation device, positioned between spaced-apart first and second portions of the belt. The thermal regulation device is also configured to concurrently cool the first portion of the belt to contract the first portion of the belt and heat the second portion of the belt to expand the second portion of the belt. Concurrent contraction and expansion of the first and second portions of the belt cause rotation of the belt.

公开(公告)号：US09555873B1

公开(公告)日：2017-01-31

申请号：US15092237

申请日：2016-04-06

申请人： Area- I Inc.

发明人： Nicholas Robert Alley ,  Joshua Lemming Steele ,  Jesse Owen Williams ,  Daniel Kuehme ,  Jonathan Caleb Phillips

IPC分类号： B64C3/56 ,  B64C3/54 ,  B64C39/02

CPC分类号： B64C3/40 ,  B64C1/36 ,  B64C3/54 ,  B64C3/546 ,  B64C3/56 ,  B64C5/02 ,  B64C5/12 ,  B64C5/16 ,  B64C11/28 ,  B64C13/24 ,  B64C13/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2211/00 ,  Y02T50/14 ,  Y02T50/44

摘要： An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

公开(公告)号：US20160238069A1

公开(公告)日：2016-08-18

申请号：US15042572

申请日：2016-02-12

申请人： Anthony Carl Bohm

发明人： Anthony Carl Bohm

IPC分类号： F16C23/04 ,  F16C27/06

CPC分类号： F16C23/045 ,  B64C13/30 ,  F16C11/0614 ,  F16C21/00 ,  F16C23/084 ,  F16C27/063 ,  F16C2326/43 ,  F16F1/40

摘要： A bearing assembly for coupling first and second members includes a housing coupled with, or integrally formed with the first member, a laminated bearing section and a spherical bearing section, each section disposed within a housing bore. The laminated bearing section is configured such that at least a portion of the laminated bearing section flexes when torque on the first and second members is less than a predetermined value. The spherical bearing section is configured such that a spherical bearing inner member slidably displaces within a spherical bearing outer member when torque on the first and second members is at least the predetermined value.

摘要翻译： 用于联接第一和第二构件的轴承组件包括与第一构件联接或整体形成的壳体，层压轴承部分和球形轴承部分，每个部分设置在壳体孔内。 层叠轴承部构造成使得当第一和第二构件上的扭矩小于预定值时，层压支承部分的至少一部分弯曲。 球面轴承部构造成使得当第一和第二构件上的扭矩至少为预定值时，球面轴承内部构件在球面轴承外部构件内滑动移位。

公开(公告)号：US20160052628A1

公开(公告)日：2016-02-25

申请号：US14465334

申请日：2014-08-21

申请人： Bell Helicopter Textron Inc.

发明人： Carl D. Griffith ,  Brady G. Atkins ,  Awais Raza ,  Paul M. Wilson

IPC分类号： B64C27/57 ,  B64C27/04

CPC分类号： B64C27/57 ,  B64C13/08 ,  B64C13/18 ,  B64C13/30 ,  B64C27/04 ,  B64C27/56 ,  B64C27/58

摘要： A rotorcraft autopilot system includes a series actuator connecting a cockpit control component to a swashplate of a rotorcraft, the series actuator to modify a control input from the cockpit control component to the swashplate through a downstream control component. The rotorcraft autopilot system also includes a differential friction system connected to the cockpit control component, the differential friction system to control the series actuator to automatically adjust a position of the cockpit control component during rotorcraft flight based, in part, on a flight mode of the rotorcraft.

摘要翻译： 旋翼飞行器自动驾驶仪系统包括将驾驶舱控制部件连接到旋翼航空器的旋转斜盘的串联致动器，该串联致动器通过下游控制部件修改从驾驶舱控制部件到斜盘的控制输入。 旋翼飞行器自动驾驶仪系统还包括连接到驾驶舱控制部件的差速摩擦系统，差速摩擦系统，用于控制串联致动器，以在旋翼飞行器飞行期间部分地基于飞行模式来自动调整驾驶舱控制部件在旋翼飞行器飞行期间的位置 旋翼航空器

公开(公告)号：US09199742B2

公开(公告)日：2015-12-01

申请号：US13694334

申请日：2012-11-21

申请人： Pavlos Giannakopoulos

发明人： Pavlos Giannakopoulos

IPC分类号： B64D17/00 ,  B64D17/24 ,  B64C13/30 ,  B64C25/30 ,  B64D17/36 ,  B64D17/80 ,  B64D25/04 ,  B64D37/26

CPC分类号： B64D17/24 ,  B64C13/30 ,  B64C25/30 ,  B64C2201/185 ,  B64D17/36 ,  B64D17/80 ,  B64D25/04 ,  B64D37/26 ,  Y02T50/44

摘要： From the dynamic shock of the parachute canopy applied to an aircraft and unmanned aerial vehicle-(UAV) in an emergency, there is unlimited mechanical force available for exploitation through Bowden cables connected to the ends of the parachute straps, and transfer of the force in the form of a pull onto the emergency safety systems of the aircraft for the safety of passengers, and onto the aerial vehicle-(UAV).

摘要翻译： 从紧急情况下应用于飞机和无人机（UAV）的降落伞的动态冲击，通过连接到降落伞带末端的鲍登电缆可以获得无限的机械力，并将力传递到 将飞机的紧急安全系统拉到乘客的安全以及飞机（UAV）上的形式。

公开(公告)号：US09150308B2

公开(公告)日：2015-10-06

申请号：US13763590

申请日：2013-02-08

申请人： Merlin Technology, Inc.

发明人： John E. Mercer ,  Marc Feifel ,  Mark Marvin ,  Nicolas Albion

IPC分类号： H02K7/14 ,  B64C27/68 ,  B64C27/59 ,  B64C13/04 ,  B64C13/30 ,  B64C27/57 ,  B64C27/58

CPC分类号： B64C27/68 ,  B64C13/04 ,  B64C13/18 ,  B64C13/30 ,  B64C27/57 ,  B64C27/58 ,  B64C27/59 ,  F16F15/121 ,  Y02T50/44

摘要： An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.

摘要翻译： 自动驾驶执行器包括第一和第二电动机，每个电动机包括可旋转的电动机输出轴，使得电动机中的一个或两个可以驱动致动器输出轴。 自动驾驶仪主机壳体可拆卸地安装在靠近循环控制的直升机上，并且通常容纳自动驾驶执行器以及主要的自动驾驶仪电子装置。 循环式隔振器由致动器轴可拆卸地支撑，用于共同旋转并且耦合到循环控制器，以在致动器轴处衰减循环振动频率，同时致动器轴的低于谐振频率的转速耦合到循环控制。 力限制连杆包括第一和第二端以及两者之间的可变长度。 当施加小于放开力的力时，力限制连杆具有松弛的长度，并且当施加的力超过转动力以允许引导超驰时，可变长度改变。

公开(公告)号：US20140326828A1

公开(公告)日：2014-11-06

申请号：US14358651

申请日：2012-11-21

申请人： SAGEM DEFENSE SECURITE

发明人： David Senegas ,  Jerome Mehez ,  Maxime Jestin ,  Bertrand Sevagen

IPC分类号： B64C13/30 ,  F16H21/22

CPC分类号： B64C13/30 ,  B64C13/24 ,  B64C13/28 ,  F16H21/22 ,  F16H35/00 ,  F16H2035/005 ,  Y10T74/18184 ,  Y10T74/18696 ,  Y10T74/18792

摘要： An electromechanical actuator for a movable flight control surface of an aircraft, the actuator comprising an electric motor having an outlet shaft with first and second directions of rotation, a movement transmission arranged to connect the outlet shaft of the motor to the movable flight control surface, and a control unit for controlling the motor. The transmission incorporates a pawl device arranged to oppose the transmission of movement in the first direction of rotation, and the control unit is connected to a pawl declutching member for declutching the pawl and enabling movement to be transmitted in the first direction of rotation.

摘要翻译： 一种用于飞行器的可移动飞行控制表面的机电致动器，所述致动器包括具有第一和第二旋转方向的出口轴的电动机，布置成将马达的出口轴连接到可移动飞行控制表面的运动传动装置， 以及用于控制电动机的控制单元。 传动装置包括一个棘爪装置，该棘爪装置被布置成与第一旋转方向上的运动相对抗，并且该控制单元连接到一个棘爪释放构件，用于释放棘爪并使运动能够沿第一旋转方向传递。

公开(公告)号：US20140288731A1

公开(公告)日：2014-09-25

申请号：US14275102

申请日：2014-05-12

申请人： Textron Innovations Inc.

发明人： Steven G. Hagerott ,  James L. Hammer ,  Phillippe A. Ciholas ,  Mark W. Palmer

IPC分类号： B64C19/00

CPC分类号： B64C13/30 ,  B64C9/04 ,  B64C9/10 ,  B64C13/04 ,  B64C13/42 ,  B64C13/503

摘要： A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces.

摘要翻译： 公开了一种用于控制具有由手动控制的飞行控制表面和由计算装置控制的飞行器的系统和方法。 本发明通过减少机械飞行控制表面部件同时在机械或电力相关故障的情况下提供足够的后备控制能力来改进总体飞行控制操作。 通过本发明，自动反馈从机械飞行控制表面提供给操作者，该机械飞行控制表面独立于计算机辅助飞行控制表面操作。 此外，通过本发明，对从飞行员接收的力输入信号进行滤波，以改善计算机辅助飞行控制表面的操作。

公开(公告)号：US08812178B2

公开(公告)日：2014-08-19

申请号：US13917487

申请日：2013-06-13

申请人： Thales

发明人： Yannick Meret ,  Arnaud Bonnafoux ,  Christophe Simon

IPC分类号： B64C13/16 ,  B64C13/18 ,  B64C13/30

CPC分类号： B64C13/16 ,  B64C13/18 ,  B64C13/30 ,  G05D1/0808

摘要： A method for automatic yaw axis control in aircraft with mechanical controls, said aircraft including a yaw actuator to control orientation of a yaw control surface and deliver a measured value of the torque on the control surface, a yaw trim actuator driving movement of a yaw trim control surface limiting the force applied by the yaw actuator to orient the yaw control surface, and sensors supplying an estimate of a lateral yaw force, includes calculating a setpoint value for the position of the yaw control surface determined by the estimated lateral force, an estimated torque of the yaw actuator determined by the measured value of the torque of the yaw actuator and a measured position of the yaw control surface, the estimated torque calculated having a lower oscillation dynamic range than the measured torque, and a trim command for activating/deactivating the yaw trim actuator determined by the estimated torque.

摘要翻译： 一种用于具有机械控制的飞行器中的自动偏航轴控制的方法，所述飞行器包括偏航致动器，以控制偏航控制表面的方位并将扭矩的测量值传递到控制表面上;偏航调整致动器驱动偏航装饰 控制表面限制由偏航致动器施加的力以定向偏航控制表面，以及提供横向偏转力的估计的传感器包括计算由所估计的横向力确定的偏航控制表面的位置的设定值，估计 由偏航致动器的扭矩的测量值和偏航控制表面的测量位置确定的偏航致动器的扭矩，计算出的具有比测量的扭矩更低的振动动态范围的估计转矩以及用于激活/停用的修剪命令 由所估计的扭矩确定的偏航修正致动器。

公开(公告)号：US20140138480A1

公开(公告)日：2014-05-22

申请号：US13832483

申请日：2013-03-15

申请人： AIRBUS OPERATIONS GMBH

发明人： Martin Richter

IPC分类号： B64C13/28

CPC分类号： B64C13/28 ,  B64C13/30 ,  B64D45/0005 ,  B64D2045/001 ,  Y02T50/44

摘要： A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves.

摘要翻译： 提供飞机机翼上的高升程系统。 机翼包括右手和左手翼半部，其具有可移动的高举襟翼，右侧和左侧翼半部连接到飞机机身，从而形成翼根。 靠近翼根的区域中的每个翼半部包括驱动单元。 在每种情况下，该驱动单元连接到机械地连接到相应驱动单元的传动轴，该传动轴从驱动单元沿着相应的翼半部的端部的方向延伸，并被设计成机械地移动高升降翼 布置在相应的翼半部。 通过这种布置，可以在没有偏转齿轮装置的情况下从中心驱动单元到单个翼片半部进行。