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公开(公告)号：US07387277B2
公开(公告)日：2008-06-17
申请号：US11027570
申请日：2004-12-29
申请人： Jan A. Kordel , Richard B. Tanner , Ian C. Burford , Victor A. Munsen , Daniel E. McGinty , Scott N. Rampton , Bruce R. Fox , James M. Kelly , Miles O. Johnson
发明人： Jan A. Kordel , Richard B. Tanner , Ian C. Burford , Victor A. Munsen , Daniel E. McGinty , Scott N. Rampton , Bruce R. Fox , James M. Kelly , Miles O. Johnson
IPC分类号： B64C3/20
CPC分类号： B64C3/00
摘要： Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.
摘要翻译： 公开了具有复合材料和金属板的飞机机翼组件。 在一个实施例中，翼组件包括支撑结构，由金属材料形成并联接到支撑结构的上面板组件，以及由复合材料形成并联接到支撑结构的下部面板组件。 金属材料可以是铝，钛或任何其它合适的金属，并且复合材料可以是碳纤维增强塑料（CFRP）材料或其它合适的复合材料。 在另一个实施例中，上面板组件包括向下悬垂的第一腹板部分，并且下面板组件包括向上悬垂的第二腹板部分，第二腹板部分靠近第一腹板部分，并且设置隔离材料的接口构件 在第一和第二纤维网部分之间。
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公开(公告)号：US20080023585A1
公开(公告)日：2008-01-31
申请号：US11027570
申请日：2004-12-29
申请人： Jan A. Kordel , Richard B. Tanner , Ian C. Burford , Victor A. Munsen , Daniel E. McGinty , Scott N. Rampton , Bruce R. Fox , James M. Kelly , Miles O. Johnson
发明人： Jan A. Kordel , Richard B. Tanner , Ian C. Burford , Victor A. Munsen , Daniel E. McGinty , Scott N. Rampton , Bruce R. Fox , James M. Kelly , Miles O. Johnson
IPC分类号： B64C3/00
CPC分类号： B64C3/00
摘要： Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.
摘要翻译： 公开了具有复合材料和金属板的飞机机翼组件。 在一个实施例中，翼组件包括支撑结构，由金属材料形成并联接到支撑结构的上面板组件，以及由复合材料形成并联接到支撑结构的下部面板组件。 金属材料可以是铝，钛或任何其它合适的金属，并且复合材料可以是碳纤维增强塑料（CFRP）材料或其它合适的复合材料。 在另一个实施例中，上面板组件包括向下悬垂的第一腹板部分，并且下面板组件包括向上悬垂的第二腹板部分，第二腹板部分靠近第一腹板部分，并且设置隔离材料的接口构件 在第一和第二纤维网部分之间。
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公开(公告)号：US06830218B2
公开(公告)日：2004-12-14
申请号：US10334452
申请日：2002-12-31
申请人： Jan A. Kordel , Richard B. Tanner
发明人： Jan A. Kordel , Richard B. Tanner
IPC分类号： B64C326
CPC分类号： B64C3/26 , B64F5/10 , F16B2200/30
摘要： A method, system, and apparatus for attaching a fairing to a body or aircraft wing are disclosed. A plurality of attach anchors is disposed on the body or aircraft wing to which the fairing is to be attached. Disposed in the fairing is a plurality of core pockets that are alignable with the plurality of attach anchors, and each of the core pockets defines a channel. The fairing is placed over the body or the aircraft wing such that the heads of the attach anchors are received in the core pockets. The fairing is then slid across the body or the aircraft wing with the channels sliding along the heads of the attach anchors such that the fairing is prevented from being lifted away from the body or aircraft wing.
摘要翻译： 公开了一种用于将整流罩附接到身体或飞机机翼上的方法，系统和装置。 多个附接锚固件设置在整流罩将要连接到的主体或飞机机翼上。 布置在整流罩中的是多个可与多个连接锚固件对准的芯袋，并且每个芯袋限定通道。 整流罩放置在身体或飞机机翼上，使得附接锚的头部被容纳在芯袋中。 然后，整流罩滑过身体或飞机机翼，通道沿连接锚的头部滑动，从而防止整流罩从身体或飞机机翼上抬起。
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公开(公告)号：US09108715B2
公开(公告)日：2015-08-18
申请号：US13482537
申请日：2012-05-29
申请人： Jan A. Kordel , Seiya Sakurai
发明人： Jan A. Kordel , Seiya Sakurai
CPC分类号： B64C1/10 , B64C9/16 , B64C9/18 , B64C2009/143
摘要： A rotary actuated high lift gapped aileron system and method are presented. A high lift gapped aileron couples to an airfoil at a hinge line and changes a camber of the airfoil. A rotary actuator coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door positioned under the hinge line provides an airflow over the high lift gapped aileron. A deployment linkage mechanism coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.
摘要翻译： 提出了一种旋转驱动的高电梯间隙副翼系统和方法。 一个高升降机的副翼在铰链上与翼型相连，并改变了翼型的弯度。 耦合到高电梯间隙副翼的旋转致动器响应于致动指令产生高升力带隙副翼的旋转运动。 定位在铰链线上方的垂直面板增强了升降机间隙副翼的升力。 位于铰链线下方的海湾唇门在高升高间隙副翼上提供气流。 联接到高提升间隙副翼的展开联动机构响应于旋转运动而定位下垂面板和小湾唇门。
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公开(公告)号：US08733692B2
公开(公告)日：2014-05-27
申请号：US13493688
申请日：2012-06-11
申请人： Jan A. Kordel , Mark S. Good
发明人： Jan A. Kordel , Mark S. Good
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , B64C23/072 , Y02T50/164 , Y10T29/49826 , Y10T74/20238 , Y10T292/0962 , Y10T292/558
摘要： Latching apparatus and methods are disclosed herein. An example apparatus includes a first latch portion including a first tooth and a first pin disposed in a first aperture defined by the first tooth and a second latch portion including a second tooth and a second pin disposed in an second aperture defined by the second tooth. The second tooth of the second latch portion is to mesh with the first tooth of the first latch portion to substantially orient the first pin and the second pin along an axis. The example apparatus further includes an actuator adjacent a first end of one of the first latch portion or the second latch portion to move the first pin and the second pin along the axis to lock the first latch portion to the second latch portion.
摘要翻译： 本文公开了锁存装置和方法。 示例性装置包括第一闩锁部分，其包括第一齿和设置在由第一齿限定的第一孔中的第一销和包括第二齿的第二闩锁部分和设置在由第二齿限定的第二孔中的第二销。 第二闩锁部分的第二齿与第一闩锁部分的第一齿啮合，以使第一销和第二销基本上沿轴线定位。 该示例设备还包括邻近第一闩锁部分或第二闩锁部分之一的第一端的致动器，以使第一销和第二销沿着轴线移动以将第一闩锁部分锁定到第二闩锁部分。
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6.发明授权Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods 有权飞机后缘装置，包括具有向前定位的铰链线的装置以及相关联的方法公开(公告)号：US08567726B2
公开(公告)日：2013-10-29
申请号：US13252011
申请日：2011-10-03
申请人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
发明人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
IPC分类号： B64C9/18
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时 后缘装置处于展开位置。
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7.发明申请Aircraft Trailing Edge Devices, Including Devices Having Forwardly Positioned Hinge Lines, and Associated Methods 有权飞机后端设备，包括具有向前定位的铰链线的设备以及相关方法公开(公告)号：US20120018588A1
公开(公告)日：2012-01-26
申请号：US13252011
申请日：2011-10-03
申请人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
发明人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
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时 后缘装置处于展开位置。
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公开(公告)号：US09016623B2
公开(公告)日：2015-04-28
申请号：US13308019
申请日：2011-11-30
CPC分类号： B64C13/32 , B64C9/02 , B64C9/16 , Y10T29/49826
摘要： A flaperon mechanism that provides jam protection while preventing the component departing from the airplane or causing unacceptable collateral damage. The jam protection feature comprises a controlled failure (fused) mechanism that is associated with the flaperon and flaperon hinge panel and maintains functional movement of the devices. Additional features can be added to the mechanism to block, shield, allow runout and shed other obstruction avenues.
摘要翻译： 襟副翼机构，在防止组件离开飞机或造成不可接受的附带损坏的同时提供堵塞保护。 阻塞保护功能包括与襟人和襟副翼铰链板相关联的受控故障（熔断）机构，并保持设备的功能运动。 可以添加其他功能来阻止，屏蔽，允许跳动和流失其他障碍途径的机制。
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公开(公告)号：US20130327883A1
公开(公告)日：2013-12-12
申请号：US13493688
申请日：2012-06-11
申请人： Jan A. Kordel , Mark S. Good
发明人： Jan A. Kordel , Mark S. Good
CPC分类号： B64C3/56 , B64C23/072 , Y02T50/164 , Y10T29/49826 , Y10T74/20238 , Y10T292/0962 , Y10T292/558
摘要： Latching apparatus and methods are disclosed herein. An example apparatus includes a first latch portion including a first tooth and a first pin disposed in a first aperture defined by the first tooth and a second latch portion including a second tooth and a second pin disposed in an second aperture defined by the second tooth. The second tooth of the second latch portion is to mesh with the first tooth of the first latch portion to substantially orient the first pin and the second pin along an axis. The example apparatus further includes an actuator adjacent a first end of one of the first latch portion or the second latch portion to move the first pin and the second pin along the axis to lock the first latch portion to the second latch portion.
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10.发明授权Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods 有权飞机后缘装置，包括具有向前定位的铰链线的装置以及相关联的方法公开(公告)号：US08038103B2
公开(公告)日：2011-10-18
申请号：US12497493
申请日：2009-07-02
申请人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
发明人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
IPC分类号： B64C9/18
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。
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