公开(公告)号：US08684314B2

公开(公告)日：2014-04-01

申请号：US13417667

申请日：2012-03-12

申请人： Bruno Chaduc ,  Patrick Hellio ,  Bernard Gemmati ,  Karsten Krok

发明人： Bruno Chaduc ,  Patrick Hellio ,  Bernard Gemmati ,  Karsten Krok

IPC分类号： G05D1/00

CPC分类号： B64C13/30 ,  B64C13/42 ,  B64C27/58 ,  Y02T50/44

摘要： For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).

摘要翻译： 对于飞机（1）的手动飞行控制系统（7）的紧急驾驶，在弹性连接装置（26）断开的情况下，上游控制装置（8）对系列的电子控制单元（29）进行授权 致动器（21）。 输出枢转象限（25）由定心杆（22）承受阻塞和定心作用。 在系统断裂的情况下，输出枢转象限（25）形成用于串联致动器（21）的轴承点，使得紧急控制致动翼面（11）。

公开(公告)号：US20140001313A1

公开(公告)日：2014-01-02

申请号：US13885630

申请日：2011-11-15

申请人： Michael Lam

发明人： Lawrence Lam ,  Michael Lam

IPC分类号： B64C13/04 ,  B64C13/28

CPC分类号： B64C13/04 ,  B64C13/28 ,  B64C13/30 ,  Y10T74/20012

摘要： A mechanical control mixer configured to couple to an aircraft is provided. An axle is mounted to a frame of the mechanical control mixer, and a barrel is configured to rotate about the axle. A central rod is disposed within the barrel. The central rod is configured to rotate with respect to the barrel. A roll control input is connected to the central rod. The roll control input is configured to cause the central rod to rotate within the barrel. Output control rods are connected to the central rod. The output control rods are connected to at least one control surface of the aircraft. An air brake input is connected to the barrel. The air brake input is configured to cause the barrel to rotate about the axle to move at least one of the output control rods

摘要翻译： 提供了一种配置成耦合到飞行器的机械控制混合器。 轴安装到机械控制混合器的框架上，并且筒构造成围绕轴旋转。 中心杆设置在枪管内。 中心杆构造成相对于筒旋转。 辊控制输入连接到中心杆。 辊控制输入被配置为使得中心杆在筒内旋转。 输出控制杆连接到中心杆。 输出控制杆连接到飞行器的至少一个控制表面。 空气制动器输入端连接到枪管。 空气制动器输入被配置为使得筒绕轴旋转以移动至少一个输出控制杆

公开(公告)号：US20130345907A1

公开(公告)日：2013-12-26

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

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：US20130153713A1

公开(公告)日：2013-06-20

申请号：US13714701

申请日：2012-12-14

申请人： AIRBUS OPERATIONS LIMITED

发明人： James WILSON ,  Paul HADLEY ,  Alexandru TEODORU

IPC分类号： B64C13/30

CPC分类号： B64C13/30 ,  B64C9/22 ,  B64D15/12 ,  Y02T50/32 ,  Y02T50/44

摘要： An aircraft wing assembly, comprising a wing having a fixed leading edge, a slat mounted for movement between a retracted position and an extended position with respect to the fixed leading edge, and a translating cable device for electrically connecting the slat to the wing and having a strut coupled at one end to the slat, the fixed leading edge having an aperture to accommodate the strut, and a seal assembly for sealing between the strut and the aperture.

摘要翻译： 一种飞机机翼组件，包括具有固定前缘的机翼，安装成相对于固定前缘在缩回位置和延伸位置之间运动的板条;以及平移电缆装置，用于将板条电连接到机翼并具有 在一端连接到板条的支柱，固定的前缘具有用于容纳支柱的孔，以及用于密封支柱和孔之间的密封组件。

公开(公告)号：US08371520B2

公开(公告)日：2013-02-12

申请号：US12846882

申请日：2010-07-30

申请人： William Craig Easter

发明人： William Craig Easter

IPC分类号： B64C37/00 ,  B64C27/24 ,  B64C3/56 ,  B64C9/34

CPC分类号： B64C39/04 ,  B60F5/02 ,  B64C3/56 ,  B64C5/02 ,  B64C13/30 ,  B64C25/405 ,  B64C37/02 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/823

摘要： A hybrid fixed wing aircraft converts into a roadworthy vehicle in a matter of seconds therefore operating efficiently in both air and ground transportation systems. The single piece wing is mounted on a skewed pivot that is on the lower portion of the fuselage and is operated by a pushbutton operating system. The aircraft includes telescopic twin boom tail design that when extended allows good pitch stability and damping. The aircraft's wing area may be increased with additional telescopic wing tip segments. This allows an increase in aspect ratio, hence improving efficiency at high loads. This feature also creates a reduction in induced drag at cruise speed by simply retracting the tips in flight. The vehicle has a unique synchronized control system that switches from flight to ground mode without input from the operator, thereby providing a natural interface for the operator.

摘要翻译： 混合型固定翼飞机在几秒钟内就能转换成有用的车辆，从而在空中和地面运输系统中有效运行。 单件翼安装在位于机身下部的倾斜枢轴上，并由按钮操作系统操作。 该飞机包括伸缩式双桅杆尾部设计，当延伸时允许良好的俯仰稳定性和阻尼。 飞机的机翼区域可能会增加额外的伸缩翼尖段。 这允许增加纵横比，从而提高高负载下的效率。 该功能还通过简单地缩回飞行中的尖端而在巡航速度下产生诱导阻力的减小。 车辆具有独特的同步控制系统，从飞行到地面模式切换，无需操作人员的输入，从而为操作员提供自然界面。

公开(公告)号：US20120080557A1

公开(公告)日：2012-04-05

申请号：US13376819

申请日：2010-06-10

申请人： Fernand Rodrigues

发明人： Fernand Rodrigues

IPC分类号： B64C13/30

CPC分类号： B64C13/30 ,  B64C13/28 ,  Y02T50/44

摘要： The invention relates to a device (4) for actuating a control surface (2) of an aircraft, comprising:-a frame intended to be mounted fixed in relation to a structure of an aircraft, -a bell crank part (7) mobile in rotation in relation to the frame around an axis of rotation (X, X′) and adapted in order to be connected to a mechanical unit (1) for displacement of the control surface (2), -a slider (6) intended to be connected to a drive member (5), the slider (6) being mobile in translation in relation to the frame according to a direction of translation, parallel to the axis of rotation (X, X′) of the bell crank part (7), -first connecting means (61) between the slider (6) and the bell crank part (7) in order to convert a displacement in translation of the slider (6) generated by the drive member (5) into a displacement in rotation of the bell crank part (7), in order to actuate the mechanical unit (1) for displacement of the control surface (2),an input part (53, 16) able to be driven in rotation by the motor, -a control rod mounted fixed in relation to the frame and extending parallel to the axis of rotation (X) of the input part and at a distance from the latter, in order to block in rotation the slider in relation to the frame and authorize a translation of the slider in relation to the frame, the control rod extends through the slider (6). Application specific to the actuating of control surfaces incorporated into a thin airfoil.

摘要翻译： 本发明涉及一种用于致动飞行器的控制表面（2）的装置（4），包括： - 一个相对于飞行器结构固定的框架， - 一个可在 相对于围绕旋转轴线（X，X'）的框架的旋转，并且适于连接到用于控制表面（2）的位移的机械单元（1）， - 用于使控制表面（2）移动的滑块（6） 连接到驱动构件（5）上，滑块（6）根据平行于曲柄曲柄部分（7）的旋转轴线（X，X'）的平移方向相对于框架移动平移， 为了将由驱动构件（5）产生的滑动件（6）的平移位移转换成旋转位移，在滑块（6）和钟形曲柄部分（7）之间的第一连接装置（61） 所述钟形曲柄部分（7）为了致动用于所述控制表面（2）的位移的所述机械单元（1），能够为d的输入部分（53,16） 通过电动机旋转， - 控制杆，其相对于框架固定并且平行于输入部分的旋转轴线（X）延伸并且与其相距一定距离，以便将滑块阻挡在 关于框架并授权滑块相对于框架的平移，控制杆延伸穿过滑块（6）。 专用于结合到薄翼型中的控制表面的致动应用。

公开(公告)号：US20110276202A1

公开(公告)日：2011-11-10

申请号：US13102238

申请日：2011-05-06

申请人： Cédric Carlavan ,  Pascal Leguay

发明人： Cédric Carlavan ,  Pascal Leguay

IPC分类号： G05D1/00 ,  B64C13/12 ,  G05D1/10 ,  B64C13/04

CPC分类号： B64C13/10 ,  B64C13/30 ,  B64C27/59 ,  G05G5/08 ,  G05G5/22 ,  Y02T50/44

摘要： The present invention relates to a friction device (11) for maintaining a control member (2, 8) in a determined position. The device comprises a contact part (16) movable between a declutched stable position and a clutched stable position, and vice versa. The clutched stable position corresponds to a position in which the contact part (16) bears against the control member (2, 8) in such a manner as to establish a determined friction force. An electromechanical drive means moves the contact part (16) between the two stable positions. The device includes remote control means for activating and deactivating the drive means.

摘要翻译： 本发明涉及一种用于将控制构件（2,8）保持在确定位置的摩擦装置（11）。 该装置包括可在可解除的稳定位置和离合的稳定位置之间移动的接触部分（16），反之亦然。 离合稳定位置对应于接触部分（16）以确定摩擦力的方式抵靠控制构件（2,8）的位置。 机电驱动装置使接触部分（16）在两个稳定位置之间移动。 该装置包括用于激活和去激活驱动装置的遥控装置。

公开(公告)号：US20110036939A1

公开(公告)日：2011-02-17

申请号：US12846882

申请日：2010-07-30

申请人： William Craig Easter

发明人： William Craig Easter

IPC分类号： B64C37/02 ,  B64C3/48

CPC分类号： B64C39/04 ,  B60F5/02 ,  B64C3/56 ,  B64C5/02 ,  B64C13/30 ,  B64C25/405 ,  B64C37/02 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/823

摘要： A hybrid fixed wing aircraft converts into a roadworthy vehicle in a matter of seconds therefore operating efficiently in both air and ground transportation systems. The single piece wing is mounted on a skewed pivot that is on the lower portion of the fuselage and is operated by a pushbutton operating system. The aircraft includes telescopic twin boom tail design that when extended allows good pitch stability and damping. The aircraft's wing area may be increased with additional telescopic wing tip segments. This allows an increase in aspect ratio, hence improving efficiency at high loads. This feature will also creates a reduction in induced drag at cruise speed by simply retracting the tips in flight. The vehicle has a unique synchronized control system that switches from flight to ground mode without input from the operator, thereby providing a natural interface for the operator.

摘要翻译： 混合型固定翼飞机在几秒钟内就能转换成有用的车辆，从而在空中和地面运输系统中有效运行。 单件翼安装在位于机身下部的倾斜枢轴上，并由按钮操作系统操作。 该飞机包括伸缩式双桅杆尾部设计，当延伸时允许良好的俯仰稳定性和阻尼。 飞机的机翼区域可能会增加额外的伸缩翼尖段。 这允许增加纵横比，从而提高高负载下的效率。 该功能还将通过简单地缩回飞行中的尖端而在巡航速度下产生诱导阻力的减小。 车辆具有独特的同步控制系统，从飞行到地面模式切换，无需操作人员的输入，从而为操作员提供自然界面。

公开(公告)号：US06929216B2

公开(公告)日：2005-08-16

申请号：US10689972

申请日：2003-10-20

申请人： David L. Bath ,  Salvatore Carta ,  Kelly T. Jones ,  Brian J. Kramer ,  Chester P. Nelson ,  Pieter S. Penhall ,  Joseph R. Pineda ,  Andrew Sheppard

发明人： David L. Bath ,  Salvatore Carta ,  Kelly T. Jones ,  Brian J. Kramer ,  Chester P. Nelson ,  Pieter S. Penhall ,  Joseph R. Pineda ,  Andrew Sheppard

IPC分类号： B64C1/00 ,  B64C1/26 ,  B64C3/38 ,  B64C5/04 ,  B64C5/12 ,  B64C5/16 ,  B64C9/02 ,  B64C13/00 ,  B64C13/30 ,  B64C13/32 ,  B64C39/12 ,  F16C19/50

CPC分类号： F16C19/50 ,  B64C1/26 ,  B64C3/38 ,  B64C3/385 ,  B64C5/04 ,  B64C5/16 ,  B64C9/02 ,  B64C13/30 ,  B64C13/32 ,  B64C39/12 ,  F16C2326/43 ,  Y02T50/44 ,  Y10T29/49545 ,  Y10T29/49638 ,  Y10T29/49643 ,  Y10T29/4973

摘要： Methods and apparatuses for installing and actuating movable airfoils, such as canards. A canard in one embodiment of the invention includes an airfoil positioned external to an aircraft fuselage. The airfoil can include a first portion and a second portion (such as a flight control surface) movable relative to the first portion. A connecting portion depends from the airfoil portion and has an attachment portion configured to attach to an aircraft internal to the aircraft fuselage. A connecting portion can include first and second load paths to carry corresponding first and second load portions between the airfoil portion and the attachment portion. The connecting portion can be rotatable about a rotation axis positioned between the first and second loads paths. Accordingly, the connecting portion can be relatively compact so as to reduce the impact of the connecting portion and the volume of the fuselage.

摘要翻译： 用于安装和致动可移动翼型件的方法和装置，例如卡车。 在本发明的一个实施例中的鸭子包括位于飞机机身外部的翼型件。 翼型件可以包括可相对于第一部分移动的第一部分和第二部分（例如飞行控制表面）。 连接部分从翼型件部分中取出并且具有被配置为附接到飞行器机身内部的飞行器的附接部分。 连接部分可以包括第一和第二负载路径，以在机翼部分和附接部分之间承载对应的第一和第二负载部分。 连接部分可以围绕位于第一和第二负载路径之间的旋转轴线旋转。 因此，连接部分可以相对紧凑，以减少连接部分的冲击和机身的体积。

公开(公告)号：US20050051671A1

公开(公告)日：2005-03-10

申请号：US10657410

申请日：2003-09-08

申请人： Mihailo Djuric

发明人： Mihailo Djuric

IPC分类号： B64C13/14 ,  B64C13/30

CPC分类号： B64C13/30 ,  B64C13/14 ,  Y02T50/44

摘要： A non-jamming, fail safe flight control system with non-symmetric load alleviation capability includes a dual cable control system one for each side of control surface, like an elevator or an aileron, controlled by a pilot but driven by a driving system which allows control surfaces to even out the load from one side to the other without affecting pilots control while—if one side becomes jammed—enabling the pilot, with no extra action, to continue flying the aircraft utilizing the other side. In another embodiment an automatic lock feature ensures that a pilot is able to continue to complete the flight in case of severance of a control cable due to a discrete damage without interruption attributable to the control system. Yet another embodiment utilizing either the same or a separate locking feature enables the pilot to lock the surfaces upon parking the aircraft.

摘要翻译： 具有非对称负载减轻能力的非干扰的故障安全飞行控制系统包括一个双控制电缆控制系统，一个用于控制表面的每一侧，如电梯或副翼，由飞行员控制，但由驱动系统驱动， 控制表面将负载从一侧平衡到另一侧，而不影响飞行员控制，而如果一方被卡住，使飞行员无需额外的动作就可以利用另一侧继续飞行飞机。 在另一个实施例中，自动锁定功能确保在由于离开的损坏而不会导致控制系统的中断的情况下，飞行员能够继续完成飞行，以防止控制电缆的中断。 利用相同或单独的锁定特征的另一实施例使飞行员能够在停放飞行器时锁定表面。