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公开(公告)号：US08267665B2
公开(公告)日：2012-09-18
申请号：US12237911
申请日：2008-09-25
CPC分类号： F01D5/147 , B64C11/00 , B64C27/18 , F01D5/145 , F01D5/18 , F03D1/0675 , F04D29/324 , F04D29/38 , F04D29/663 , Y02E10/721 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A rotor blade including a root attachable to a rotor hub. The blade includes a tip and one or more channels aligned within the blade generally between the root and the tip. Each channel has a sealed first end and a second end vented to outside the blade. The channel(s) are vented to one or more exterior surfaces of the blade through one or more apertures in the exterior surface(s).
摘要翻译： 一种转子叶片，其包括可附接到转子毂的根部。 叶片包括尖端以及通常在根部和尖端之间在叶片内对齐的一个或多个通道。 每个通道具有密封的第一端和通向叶片外部的第二端。 通道通过外表面中的一个或多个孔被排放到叶片的一个或多个外表面。
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公开(公告)号：US20100074758A1
公开(公告)日：2010-03-25
申请号：US12237911
申请日：2008-09-25
CPC分类号： F01D5/147 , B64C11/00 , B64C27/18 , F01D5/145 , F01D5/18 , F03D1/0675 , F04D29/324 , F04D29/38 , F04D29/663 , Y02E10/721 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A rotor blade including a root attachable to a rotor hub. The blade includes a tip and one or more channels aligned within the blade generally between the root and the tip. Each channel has a sealed first end and a second end vented to outside the blade. The channel(s) are vented to one or more exterior surfaces of the blade through one or more apertures in the exterior surface(s).
摘要翻译： 一种转子叶片，其包括可附接到转子毂的根部。 叶片包括尖端以及通常在根部和尖端之间在叶片内对齐的一个或多个通道。 每个通道具有密封的第一端和通向叶片外部的第二端。 通道通过外表面中的一个或多个孔被排放到叶片的一个或多个外表面。
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公开(公告)号：US08439313B2
公开(公告)日：2013-05-14
申请号：US12905382
申请日：2010-10-15
申请人： Blaine K. Rawdon , John C. Vassberg
发明人： Blaine K. Rawdon , John C. Vassberg
CPC分类号： B64C23/069 , Y02T50/164
摘要： An aircraft may include a pair of wings. A forward swept winglet may be attached proximate to a wing tip of each wing. The forward swept winglet may include a leading edge and a trailing edge. The leading edge of each winglet may extend from the wing at a predetermined forward sweep angle relative to a line perpendicular to a chord of the wing tip in a direction corresponding to a forward portion of the aircraft.
摘要翻译： 飞机可能包括一对机翼。 向前扫掠的小翼可以附接到每个翼的翼尖附近。 向前扫掠的小翼可以包括前缘和后缘。 每个小翼的前缘可以相对于垂直于翼尖的翼弦在与飞行器的前部相对应的方向上以预定的前掠角延伸。
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公开(公告)号：US07048228B2
公开(公告)日：2006-05-23
申请号：US10678474
申请日：2003-10-03
申请人： John C. Vassberg , Lie-Mine Gea , James D. McLean , David P. Witkowski , Steven E. Krist , Richard L. Campbell
发明人： John C. Vassberg , Lie-Mine Gea , James D. McLean , David P. Witkowski , Steven E. Krist , Richard L. Campbell
IPC分类号： B64C3/48
CPC分类号： B64C3/28 , B64C21/02 , B64C2003/149 , B64C2230/20 , Y02T50/12 , Y02T50/166
摘要： An aircraft wing includes a leading airfoil element and a trailing airfoil element. At least one slot is defined by the wing during at least one transonic condition of the wing. The slot may either extend spanwise along only a portion of the wingspan, or it may extend spanwise along the entire wingspan. In either case, the slot allows a portion of the air flowing along the lower surface of the leading airfoil element to split and flow over the upper surface of the trailing airfoil element so as to achieve a performance improvement in the transonic condition.
摘要翻译： 飞机机翼包括一个先导的翼型元件和一个后翼型元件。 在机翼的至少一个跨音速条件期间，机翼限定了至少一个槽。 狭槽可以沿翼展的翼展方向延伸，或者可以沿着整个翼展展开翼展。 在任一种情况下，狭槽允许空气沿着先导翼型元件的下表面流动的一部分分流并流过后翼型元件的上表面，从而在跨音速条件下实现性能改进。
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公开(公告)号：US08403256B1
公开(公告)日：2013-03-26
申请号：US12410894
申请日：2009-03-25
申请人： Robert D Gregg, III , Aaron J. Kutzmann , David J. Manley , John C. Vassberg , Neal Harrison , Max Kismarton
发明人： Robert D Gregg, III , Aaron J. Kutzmann , David J. Manley , John C. Vassberg , Neal Harrison , Max Kismarton
IPC分类号： B64C39/12
CPC分类号： B64C1/061 , B64C3/10 , B64C9/38 , B64C2001/0045 , B64C2039/105 , Y02T50/12 , Y02T50/32 , Y02T50/44
摘要： Apparatus and methods provide for a swept-wing powered-lift aircraft. Aspects of the disclosure provide a powered-lift aircraft that utilizes the engine exhaust flow over upper surface blown flaps to increase lift during various flight operations. The powered-lift aircraft has wings with inboard portions and outboard portions. The adjacent inboard and outboard portions share a swept leading edge. The leading edge is swept to a degree that shifts the outboard portion rearward to a position in which the aircraft center of lift has little to no variance upon the activation or deactivation of a powered-lift system.
摘要翻译： 装置和方法提供了扫掠式动力升降飞机。 本公开的方面提供了一种动力升降飞行器，其利用在上表面吹风襟翼上的发动机排气流，以在各种飞行操作期间增加升力。 动力升降飞机具有内侧部分和外侧部分的翼。 相邻的内侧和外侧部分共享一个扫掠的前缘。 前缘被扫掠到将外侧部分向后移动到在升降系统的启动或停用时电梯的中心几乎没有变化的位置的程度。
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6.发明授权Aircraft configuration utilizing fuselage, wing, empennage, and exhaust flow control devices 有权飞机配置采用机身，机翼，尾翼和排气流量控制装置公开(公告)号：US08061655B1
公开(公告)日：2011-11-22
申请号：US12410813
申请日：2009-03-25
申请人： David J. Manley , Aaron J. Kutzmann , Robb Gregg, III , John C. Vassberg , Antonio B. Gonzales , Steve Hollowell , Neal Harrison , Edward Lawson , Max Kismarton , Kevin Lutke
发明人： David J. Manley , Aaron J. Kutzmann , Robb Gregg, III , John C. Vassberg , Antonio B. Gonzales , Steve Hollowell , Neal Harrison , Edward Lawson , Max Kismarton , Kevin Lutke
IPC分类号： B64C1/00
摘要： Apparatus and methods provide for an aircraft configuration that utilize structural and engine exhaust flow control devices to enhance performance. Aspects of the disclosure provide a fuselage with a pressure vessel nested within a non-cylindrical outer mold line fairing. A twin-boom empennage may be connected to the fuselage. A wing may attach in a blended wing configuration with a sweep angle that positions the aircraft center of lift to minimize any pitching moment induced by the activation or deactivation of an upper surface blown (USB) system. The USB system may include a conformal USB flap positioned downstream of an engine exhaust plume, as well as a controllable USB nozzle aperture to promote exhaust flow attachment to the conformal USB flap. A universal convergent nozzle may be utilized to connect each controllable USB nozzle aperture to a corresponding internally mounted aircraft engine.
摘要翻译： 装置和方法提供了利用结构和发动机排气流量控制装置来增强性能的飞行器配置。 本公开的方面提供了一种具有嵌套在非圆柱形外模线整流罩内的压力容器的机身。 机身可能连接双桅杆尾翼。 翼可以以具有扫掠角的混合翼构型附接，该倾斜角定位飞行器的升降机中心，以最小化由上表面吹（USB）系统的激活或停用引起的任何俯仰时刻。 USB系统可以包括位于发动机排气羽流下游的共形USB挡板以及可控制的USB喷嘴孔，以促进附着到保形USB挡板的排气流。 可以使用通用会聚喷嘴将每个可控USB喷嘴孔连接到相应的内部安装的飞机发动机。
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公开(公告)号：US20090052478A1
公开(公告)日：2009-02-26
申请号：US11841481
申请日：2007-08-20
申请人： John C. Vassberg , David T. Yeh , Mark A. DeHaan , Neal A. Harrison , Alan Z. Ullman , Michael W. Traffenstedt
发明人： John C. Vassberg , David T. Yeh , Mark A. DeHaan , Neal A. Harrison , Alan Z. Ullman , Michael W. Traffenstedt
IPC分类号： H01S3/10
CPC分类号： B64C23/00
摘要： Systems and methods are described for controlling flow disturbances emanating from a protrusion, such as a beam propagating device. In one embodiment, a method includes positioning a flow control element at least partially around a base portion of a protrusion, wherein the flow control element includes at least one flow expanding feature. A reduced pressure zone is generated proximate an aft portion of the protrusion by expanding at least a portion of a flowfield. One or more flow disturbances emanating downstream from the protrusion are deflected using the at least one reduced pressure zone.
摘要翻译： 描述了用于控制从诸如光束传播装置的突起发出的流动干扰的系统和方法。 在一个实施例中，一种方法包括至少部分地围绕突起的基部定位流量控制元件，其中流量控制元件包括至少一个流动扩张特征。 通过膨胀流场的至少一部分，在突起的后部附近产生减压区。 使用至少一个减压区域使从突出部下游发出的一个或多个流动干扰被偏转。
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公开(公告)号：US08167249B1
公开(公告)日：2012-05-01
申请号：US12410820
申请日：2009-03-25
申请人： Neal Harrison , John C. Vassberg
发明人： Neal Harrison , John C. Vassberg
IPC分类号： B64C21/00
摘要： Apparatus and methods provide for a controllable upper surface blown (USB) nozzle aperture. Aspects of the disclosure provide a powered-lift aircraft that utilizes a controllable nozzle aperture to maximize the spreading of the engine exhaust flow over the wing and USB flap surfaces to increase lift when desirable and to minimize exhaust plume contact with the wing and USB flap surfaces when minimizing drag is desirable. The controllable USB nozzle aperture includes movable upper, lower, and side duct surfaces to dynamically vary the geometry of the nozzle exit aperture to minimize the height and maximize the width of the exit aperture for maximum spreading of the exhaust plume or to maximize the height and minimize the width of the exit aperture for minimizing the spreading of the exhaust plume and minimizing the associated drag.
摘要翻译： 装置和方法提供了可控的上表面吹（USB）喷嘴孔。 本公开的方面提供一种动力升降飞机，其利用可控喷嘴孔径来最大化发动机排气流在机翼和USB挡板表面上的扩展，以在期望时增加升力并且使与尾翼和USB挡板表面的排气羽流接触最小化 当需要最小化阻力时。 可控制的USB喷嘴孔包括可移动的上部，下部和侧部管道表面，以动态地改变喷嘴出口孔的几何形状，以最小化高度并使出口孔的宽度最大化，以最大限度地扩展排气羽流，或者最大化高度， 使出口孔的宽度最小化，以使排气羽流的扩展最小化并使相关的阻力最小化。
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公开(公告)号：US08936219B2
公开(公告)日：2015-01-20
申请号：US13436355
申请日：2012-03-30
申请人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to a ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move from the static position to an in-flight position and resulting in a relative span increase of the wing.
摘要翻译： 用于飞机机翼的小翼系统可以包括安装到翼尖的上小翼和下小翼。 当机翼受到地面静载时，下小翼可能具有静态位置。 下小翼可以被配置成使得在大约1-g飞行载荷下翼的向上偏转导致下小翼从静止位置移动到飞行位置，并且导致翼的相对跨度增加。
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公开(公告)号：US20130256460A1
公开(公告)日：2013-10-03
申请号：US13436355
申请日：2012-03-30
申请人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to a ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move from the static position to an in-flight position and resulting in a relative span increase of the wing.
摘要翻译： 用于飞机机翼的小翼系统可以包括安装到翼尖的上小翼和下小翼。 当机翼受到地面静载时，下小翼可能具有静态位置。 下小翼可以被配置成使得在大约1-g飞行载荷下翼的向上偏转导致下小翼从静止位置移动到飞行位置，并且导致翼的相对跨度增加。
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