公开(公告)号：US20070114328A1

公开(公告)日：2007-05-24

申请号：US11284113

申请日：2005-11-21

申请人： Douglas Lacy ,  Jan Kordel ,  John Dovey ,  Michael Balzer ,  Seiya Sakurai ,  Neal Huynh

发明人： Douglas Lacy ,  Jan Kordel ,  John Dovey ,  Michael Balzer ,  Seiya Sakurai ,  Neal Huynh

IPC分类号： B64C39/06

CPC分类号： B64C9/16 ,  B64C9/18 ,  Y02T50/32

摘要： Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.

摘要翻译： 公开了包括具有向前定位的铰链线的装置的飞机后缘装置和相关方法。 根据本发明的一个实施例的飞行器系统包括联接到机翼的翼和后缘装置。 后缘装置可以在收起位置和展开位置之间相对于翼移动，后缘装置具有前缘，后缘，上表面和下表面。 当后缘装置处于收起位置时，上表面可以与翼的交点。 后缘装置相对于机翼的运动可以包括围绕位于交叉点前方的铰链线的旋转运动，并且当机翼的后缘和后缘装置的前缘之间可以定位间隙 后缘装置处于展开位置。

公开(公告)号：US20060175468A1

公开(公告)日：2006-08-10

申请号：US11051738

申请日：2005-02-04

申请人： Neal Huynh ,  Robert Bleeg ,  Ralph Pepper ,  John Standley ,  Brian Bocksch

发明人： Neal Huynh ,  Robert Bleeg ,  Ralph Pepper ,  John Standley ,  Brian Bocksch

IPC分类号： B64C9/22

CPC分类号： B64C9/16 ,  B64C9/323 ,  B64D2045/001 ,  Y02T50/32 ,  Y02T50/44

摘要： Systems and methods for controlling aircraft flaps and spoilers are disclosed. Systems in accordance with some embodiments include a wing having a trailing edge, and a flap positioned proximate to the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position by operation of a first actuator. A spoiler can be positioned at least proximate to the trailing edge and can be movable among at least three positions, including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position deflected downwardly from the first, and a third spoiler position deflected upwardly from the first. A second actuator can be operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions in a manner that is mechanically independent of the motion of the flap.

摘要翻译： 公开了用于控制飞机襟翼和扰流板的系统和方法。 根据一些实施例的系统包括具有后缘的机翼和靠近机翼后缘设置的翼片，并且通过第一致动器的操作可相对于翼片在第一翼片位置和第二翼片位置之间展开。 扰流器可以至少靠近后缘定位，并且可以在至少三个位置之间移动，包括第一扰流器位置，其中扰流器与翼的上表面形成大致连续的轮廓，向下偏转的第二扰流器位置 从第一和第三扰流器位置向上偏离第一扰流器位置。 第二致动器可以可操作地联接到扰流板，以在机械上独立于挡板的运动的方式在第一，第二和第三扰流板位置之间移动扰流板。

公开(公告)号：US20050116095A1

公开(公告)日：2005-06-02

申请号：US10714744

申请日：2003-11-17

申请人： Paul Cline ,  Neal Huynh ,  Leonard Inderhees ,  Munior Orgun ,  Mark Smith ,  Alexander Oleson

发明人： Paul Cline ,  Neal Huynh ,  Leonard Inderhees ,  Munior Orgun ,  Mark Smith ,  Alexander Oleson

IPC分类号： B64C13/42

CPC分类号： B64C13/42 ,  B64C13/044 ,  Y02T50/44

摘要： A reliably redundant PCU for an aircraft. The PCU includes an override mechanism coupled to the aircraft's control path and a first control member coupled to the override mechanism whereby the override mechanism attempts to transmit a command from the command path to the first control member. The unit also includes a second control member coupled to the control path whereby the command path transmits the command to the second control member. Additionally, the PCU includes two actuator members coupled to the control members whereby the actuator members attempt to move in response to the command. If the first control member resists moving the override mechanism allows the second control member to actuate the rudder. The PCU also includes a common actuator coupled to the actuator members and the control surface, whereby the actuator moves the control surface. Moreover, a unitary housing contains the first and the second actuator members.

摘要翻译： 飞机可靠冗余的PCU。 PCU包括耦合到飞行器的控制路径的超控机构和耦合到超控机构的第一控制构件，由此超控机构试图将命令从命令路径发送到第一控制构件。 该单元还包括耦合到控制路径的第二控制构件，由此命令路径将命令发送到第二控制构件。 此外，PCU包括联接到控制构件的两个致动器构件，由此致动器构件试图响应于该命令而移动。 如果第一控制构件抵抗移动超控机构，则允许第二控制构件致动舵。 PCU还包括耦合到致动器构件和控制表面的公共致动器，由此致动器移动控制表面。 此外，整体式壳体包含第一和第二致动器构件。

公开(公告)号：US20050103932A1

公开(公告)日：2005-05-19

申请号：US10697383

申请日：2003-10-30

申请人： Neal Huynh

发明人： Neal Huynh

IPC分类号： B64C13/30

CPC分类号： B64C13/30

摘要： Redundant control systems and/or failure detection systems and associated methods are disclosed herein. In one embodiment of the invention, the control system can include a first control link that transmits control inputs between at least one control input device and at least one control output device and a second control link, at least one portion of which is changeable from a disengaged state to an engaged state, the at least one portion being inactive when in the disengaged state. In another embodiment, the control system can include at least one detection system that detects failures of a control link. In yet another embodiment, the second control link can be automatically engaged when a failure in the first control link is detected.

摘要翻译： 本文公开了冗余控制系统和/或故障检测系统及相关方法。 在本发明的一个实施例中，控制系统可以包括第一控制链路，其在至少一个控制输入设备和至少一个控制输出设备与第二控制链路之间传输控制输入，其至少一部分可以从 脱离状态到接合状态，当处于分离状态时，至少一个部分是不活动的。 在另一个实施例中，控制系统可以包括检测控制链路故障的至少一个检测系统。 在另一个实施例中，当检测到第一控制链路中的故障时，第二控制链路可以自动接合。

公开(公告)号：US20070176051A1

公开(公告)日：2007-08-02

申请号：US11116905

申请日：2005-04-27

申请人： Mark Good ,  Neal Huynh ,  Kelly Jones ,  Selya Sakurai

发明人： Mark Good ,  Neal Huynh ,  Kelly Jones ,  Selya Sakurai

IPC分类号： B64C3/50

CPC分类号： B64C9/16 ,  B64C9/32 ,  B64C9/323 ,  B64C2009/143 ,  Y02T50/32

摘要： Actuation device positioning systems and associated methods, including aircraft spoiler droop systems are generally disclosed herein. One aspect of the invention is directed toward a positioning system that includes an eccentric cam and a drive mechanism coupled to the eccentric cam to rotate the eccentric cam between a first cam position and a second cam position. The system can further include an actuation device having an anchor portion and a movable portion that is movable relative to the anchor portion, the anchor portion operatively coupled to the eccentric cam. The eccentric cam can be positioned to move the anchor portion to a first anchor position when the eccentric cam is rotated to the first cam position and to move the anchor portion to a second anchor position when the eccentric cam is rotated to the second cam position.

摘要翻译： 本文通常公开了致动装置定位系统和相关方法，包括飞机扰流器下垂系统。 本发明的一个方面涉及一种定位系统，其包括偏心凸轮和联接到偏心凸轮的驱动机构，以在第一凸轮位置和第二凸轮位置之间旋转偏心凸轮。 该系统还可以包括具有锚定部分和可相对于锚固部分可移动的可移动部分的致动装置，该锚固部分可操作地联接到偏心凸轮。 当偏心凸轮旋转到第一凸轮位置时，偏心凸轮可以定位成将锚固部分移动到第一锚固位置，并且当偏心凸轮旋转到第二凸轮位置时，偏心凸轮可以定位成将锚定部分移动到第一锚定位置。

公开(公告)号：US20050022590A1

公开(公告)日：2005-02-03

申请号：US10813854

申请日：2004-03-31

申请人： Neal Huynh

发明人： Neal Huynh

IPC分类号： G01L5/22 ,  G01W1/00

CPC分类号： G01L5/22

摘要： A control surface controller force measurement system for an aircraft is provided and includes a control surface interface for positioning the aerodynamic control surfaces on an aircraft. The control surface interface transfers mechanical force to an articulated crank, which supplies the flight control system with the desired position of the control surface. The articulated crank has a first mechanical link that is pivotable about a first pivot and a second mechanical link interconnecting the control surface interface to the first mechanical link. The second mechanical link is pivotable with respect to the control surface interface at a second pivot. A force transducer interconnects the first and second mechanical links independent of the second pivot such that the mechanical force applied to the control surface interface is represented by an electrical signal output of the force transducer.

摘要翻译： 提供了用于飞行器的控制表面控制器力测量系统，并且包括用于将空气动力学控制表面定位在飞行器上的控制表面接口。 控制表面接口将机械力传递到铰接式曲柄，其向飞行控制系统提供控制表面的期望位置。 所述铰接曲柄具有第一机械连杆，所述第一机械连杆可围绕第一枢轴枢转并且所述第二机械连杆将所述控制表面接口互连到所述第一机械连杆。 第二机械连杆可在第二枢轴处相对于控制表面界面枢转。 力传感器与第二枢轴独立地互连第一和第二机械连杆，使得施加到控制表面界面的机械力由力传感器的电信号输出表示。

公开(公告)号：US20070114329A1

公开(公告)日：2007-05-24

申请号：US11284247

申请日：2005-11-21

申请人： Douglas Lacy ,  Kevin Beyer ,  Stephen Brown ,  Paul Dees ,  Neal Huynh ,  Jan Kordel ,  Clayton Prow ,  Seiya Sakurai

发明人： Douglas Lacy ,  Kevin Beyer ,  Stephen Brown ,  Paul Dees ,  Neal Huynh ,  Jan Kordel ,  Clayton Prow ,  Seiya Sakurai

IPC分类号： B64C39/06

CPC分类号： B64C9/16 ,  B64C2009/143

摘要： Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path. An outboard trailing edge device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path that is non-parallel to the first motion path. An intermediate trailing edge device can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.

摘要翻译： 公开了包括具有非平行运动路径的装置和相关方法的飞行器后缘装置。 根据一个实施例的装置包括机翼和内侧后缘装置，其联接到机翼并且可沿着第一运动路径在第一收起位置和第一展开位置之间相对于机翼移动。 外侧后缘装置可以联接到内侧后缘装置的翼外侧，并且可以沿着不平行于第一运动路径的第二运动路径相对于机翼移动。 中间后缘装置可以联接在内侧和后侧后缘装置之间，并且可以沿着不平行于第一和第二运动路径的第三运动路径移动。 每个后缘装置可以在移动到它们各自的展开位置时相对于机翼打开间隙。

公开(公告)号：US20050011994A1

公开(公告)日：2005-01-20

申请号：US10860438

申请日：2004-06-03

申请人： Seiya Sakurai ,  Stephen Fox ,  Kevin Beyer ,  Douglas Lacy ,  Paul Johnson ,  Stephen Wells ,  Jack Noble ,  Paul Meredith ,  Neal Huynh ,  Russell Christianson ,  Paul Vijgen ,  Michael Fitzpatrick ,  Clayton Prow ,  Edward Gronenthal

发明人： Seiya Sakurai ,  Stephen Fox ,  Kevin Beyer ,  Douglas Lacy ,  Paul Johnson ,  Stephen Wells ,  Jack Noble ,  Paul Meredith ,  Neal Huynh ,  Russell Christianson ,  Paul Vijgen ,  Michael Fitzpatrick ,  Clayton Prow ,  Edward Gronenthal

IPC分类号： B64C9/16 ,  B64C9/20 ,  B65D51/18

CPC分类号： B64C9/20 ,  B64C9/16 ,  Y02T50/32 ,  Y02T50/44

摘要： Trailing edge devices configured to carry out multiple functions, and associated methods of use and manufacture are disclosed. An external fluid flow body (e.g., an airfoil) configured in accordance with an embodiment of the invention includes a first portion and a second portion, at least a part of the second portion being positioned aft of the first portion, with the second portion being movable relative to the first portion between a neutral position, a plurality of upward positions, and a plurality of downward positions. A guide structure can be coupled between the first and second portions, and an actuator can be operatively coupled between the first and second portions to move the second portion relative to the first portion. In one embodiment, a flexible surface can track the motion of the second portion and can expose a gap at some positions. In another embodiment, a controller can be coupled to the actuator and can be configured to direct the actuator to move the second portion to a high lift setting, a high drag setting, a roll setting, and a trim setting. In yet another embodiment, trailing edge devices on an airfoil can have scaled, mechanically similar guide structures.

摘要翻译： 被配置为执行多个功能的后端设备以及相关联的使用和制造方法被公开。 根据本发明的实施例配置的外部流体流动体（例如，翼型）包括第一部分和第二部分，第二部分的至少一部分位于第一部分的后部，第二部分是 相对于第一部分在中立位置，多个向上位置和多个向下位置之间移动。 引导结构可以联接在第一和第二部分之间，并且致动器可以可操作地联接在第一和第二部分之间，以相对于第一部分移动第二部分。 在一个实施例中，柔性表面可以跟踪第二部分的运动并且可以在某些位置暴露间隙。 在另一个实施例中，控制器可以联接到致动器，并且可以被配置为引导致动器将第二部分移动到高提升设置，高阻力设置，滚转设置和修剪设置。 在另一个实施例中，翼型件上的后缘装置可以具有缩放的机械上相似的导向结构。