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：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：US20070252040A1

公开(公告)日：2007-11-01

申请号：US11220446

申请日：2005-09-07

申请人： Jan Kordel ,  Seiya Sakurai ,  Bret Bowers ,  Christopher Glassmoyer ,  Darren Williams

发明人： Jan Kordel ,  Seiya Sakurai ,  Bret Bowers ,  Christopher Glassmoyer ,  Darren Williams

IPC分类号： B64C3/00

CPC分类号： B64C7/00 ,  B64C9/18 ,  B64C2009/143 ,  Y02T50/32 ,  Y10S277/916

摘要： Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.

摘要翻译： 这里描述了用于与飞机上的控制表面一起使用的气动密封件。 在一个实施例中，与飞行器一起使用的密封组件包括第一密封构件和第二密封构件。 第一密封构件具有构造成附接到飞机的固定翼型部分的第一近端部分，以及构造成从固定翼型部分朝向可移动控制表面向外延伸的第一远端部分。 第二密封构件具有构造成附接到可移动控制表面的第二近端部分，以及被配置为从控制表面朝向固定翼型部分向外延伸的第二远端部分。 在该实施例中，第二远端部分进一步构造成当控制表面相对于固定翼型部分移动时，可移动地接触第一远端部分以至少部分地密封固定翼型部分和可移动控制表面之间的间隙。

公开(公告)号：US4878376A

公开(公告)日：1989-11-07

申请号：US290163

申请日：1988-12-27

申请人： Mark Leonov ,  Jan Kordel

发明人： Mark Leonov ,  Jan Kordel

IPC分类号： G01M3/34

CPC分类号： G01M3/34

摘要： A test fixture for sputter targets used in the manufacture of semiconductor devices and a method of testing sputter targets. The test fixture comprises a specially shaped piece of material which is adapted to receive a sputter target. The test fixture generally conforms to the shape of the sputter target. The interface between the test fixture and the sputter target is carefully manufactured so as to maintain an airtight seal. A passageway is disposed within one sidewall of the test fixture. A vacuum tubing is disposed within the passageway and valve is connected to the tubing so that the cavity within the test fixture can be evacuated. The size of the cavity is kept small so that it may be quickly evacuated. The present invention provides an efficient and cost effective method of testing sputter targets prior to their being placed in the sputter machine.

摘要翻译： 用于制造半导体器件的溅射靶的测试夹具和测试溅射靶的方法。 测试夹具包括适于接收溅射靶的特殊形状的材料片。 测试夹具通常符合溅射靶的形状。 仔细地制造测试夹具和溅射靶之间的界面，以保持气密密封。 通道设置在测试夹具的一个侧壁内。 真空管道设置在通道内，阀门连接到管道，使得测试夹具内的空腔可以被排空。 空腔的尺寸保持较小，从而可以快速抽真空。 本发明提供了一种在溅射靶被放置在溅射机中之前测试溅射靶的有效且成本有效的方法。