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公开(公告)号：US09908617B2
公开(公告)日：2018-03-06
申请号：US13114006
申请日：2011-05-23
CPC分类号： B64C15/14 , B64C21/02 , B64C2230/02 , Y02T50/166
摘要： An air vehicle includes an airfoil designed for transonic flight. The airfoil has a region of supersonic flow during transonic flight. A surface of the airfoil has upstream and downstream orifices at or within the region. The air vehicle further includes an active flow control system for controlling air vehicle motion during transonic flight by controlling flow through the orifices to alter strength and location of a shock wave in the region. The system creates an aerodynamic imbalance to move the shock wave.
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公开(公告)号：US09896191B2
公开(公告)日：2018-02-20
申请号：US14966444
申请日：2015-12-11
发明人： Von D. Baker
摘要： A jet aircraft includes an aircraft integrated, fluid vectoring, exhaust nozzle system. Implementation of this disclosure may eliminate or reduce the size of the aircraft vertical stabilizer and rudder assembly, thereby potentially improving aircraft survivability and increasing aircraft thrust-to-weight ratio.
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公开(公告)号：US20160185449A1
公开(公告)日：2016-06-30
申请号：US14966444
申请日：2015-12-11
发明人： Von D. Baker
IPC分类号： B64C21/08
摘要： A jet aircraft includes an aircraft integrated, fluid vectoring, exhaust nozzle system. Implementation of this disclosure may eliminate or reduce the size of the aircraft vertical stabilizer and rudder assembly, thereby potentially improving aircraft survivability and increasing aircraft thrust-to-weight ratio.
摘要翻译： 喷气式飞机包括飞机一体化，流体矢量化，排气喷嘴系统。 本公开的实施可以消除或减小飞机垂直稳定器和方向舵组件的尺寸，从而潜在地改善飞机的生存能力和增加飞机的推力重量比。
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公开(公告)号：US20110309201A1
公开(公告)日：2011-12-22
申请号：US13114006
申请日：2011-05-23
IPC分类号： B64C21/04
CPC分类号： B64C15/14 , B64C21/02 , B64C2230/02 , Y02T50/166
摘要： An air vehicle includes an airfoil designed for transonic flight. The airfoil has a region of supersonic flow during transonic flight. A surface of the airfoil has upstream and downstream orifices at or within the region. The air vehicle further includes an active flow control system for controlling air vehicle motion during transonic flight by controlling flow through the orifices to alter strength and location of a shock wave in the region. The system creates an aerodynamic imbalance to move the shock wave.
摘要翻译： 一种空中飞行器包括设计用于跨音速飞行的翼型。 翼型在跨音速飞行期间具有超音速流动区域。 翼面的表面在该区域内或内部具有上游和下游孔。 空中飞行器还包括一个主动流量控制系统，用于通过控制通过孔口的流量来控制跨音速飞行中的空中飞行器运动，以改变该区域中冲击波的强度和位置。 该系统产生气动不平衡以移动冲击波。
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公开(公告)号：US07984879B2
公开(公告)日：2011-07-26
申请号：US11995233
申请日：2007-08-31
申请人： Michael Victor Cook , Clyde Warsop
发明人： Michael Victor Cook , Clyde Warsop
IPC分类号： B64C21/04
摘要： A flow control actuator 10 for a body exposed to fluid flow comprises first and second flow surfaces 14, 16 spaced to define an elongate gap 20 therebetween. An elongate control element is disposed in or adjacent the gap and has an externally facing arcuate surface and defines a first slot 24 between the control element and said first flow surface and a second slot between said control element and said second flow surface 26. The control element 22 is moveable to allow the width of said slots to be adjusted generally proportionally. The flow of pressurized flow control fluid passes from a plenum chamber 30 out through one or both slots 24, 26 to be deflected around the arcuate surface under the influence of the Coanda effect. The flow control actuator 10 may be provided in the trailing or leading edge of an aerofoil; alternatively it may be provided between two surfaces spaced to provide said gap but otherwise providing a generally continuous surface.
摘要翻译： 用于暴露于流体流动的主体的流量控制致动器10包括间隔开的第一和第二流动表面14,16，以在其间限定细长间隙20。 细长的控制元件设置在间隙中或邻近间隙并且具有外部面对的弓形表面并且在控制元件和所述第一流动表面之间限定第一槽24和在所述控制元件和所述第二流动表面26之间的第二槽。控制 元件22可移动以允许所述槽的宽度大致成正比地调节。 加压流量控制流体的流动从通风室30通过一个或两个狭槽24,26，在柯恩达效应的影响下绕弧形表面偏转。 流量控制致动器10可以设置在机翼的后缘或前缘中; 或者可以在间隔开的两个表面之间提供以提供所述间隙，但是另外提供大致连续的表面。
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6.发明申请Method And System For Controlling Fluid Flow In Relation To A Foil And Harnessing Energy Therefrom 有权控制液体流动的方法和系统与箔片的关系和利用能量公开(公告)号：US20100044501A1
公开(公告)日：2010-02-25
申请号：US11947063
申请日：2007-11-29
申请人： Bert A. Silich
发明人： Bert A. Silich
IPC分类号： B64C15/14
CPC分类号： B64C23/065 , B64C15/14 , Y02T50/164
摘要： A method and system 10 for controlling fluid flow 12 in relation to a body or foil 14. The system 10 has one or more channels 16, at least some of which having an inlet port 18 and an outlet port 20 defined in the foil 14 through which at least some of the fluid 12 may flow. The inlet port 18 is defined adjacent to a leading edge region 22 of the foil 14 and the outlet port 20 is located in a another region 24 of the foil. Optionally, a differential vectoring means 24 provides a differential mass flow rate across the foil 14 to provide a resultant force that in one illustrative environment creates, enhances, or stops a rolling action of the foil 14.
摘要翻译： 用于相对于主体或箔片14控制流体流动的方法和系统10.系统10具有一个或多个通道16，其中至少一些通道具有限定在箔14中的入口端口18和出口端口20 其中至少一些流体12可以流动。 入口端口18邻近箔片14的前缘区域22限定，并且出口端口20位于箔片的另一区域24中。 可选地，差分向量装置24提供穿过箔片14的差分质量流率，以提供在一个说明性环境中产生，增强或停止箔片14的滚动动作的合力。
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公开(公告)号：US07510140B2
公开(公告)日：2009-03-31
申请号：US11224404
申请日：2005-09-12
申请人： Edward L. Lawson , David A. Boyer
发明人： Edward L. Lawson , David A. Boyer
IPC分类号： B64C29/00
CPC分类号： B64C29/0016 , B64C15/02 , B64C15/14 , B64C29/0066 , B64D27/20 , B64D33/02 , B64D33/04 , F02C6/00 , F02K3/077
摘要： A method of generating lift for a vehicle including a gas turbine engine having a combustor, a core flow heated by the combustor, and a bypass flow which bypasses the combustor. The method includes segregating at least a portion of the core flow from the bypass flow, directing the segregated portion of the core flow in a first direction to generate lift for the vehicle, segregating at least a portion of the bypass flow from the core flow, and directing the segregated a portion of the bypass flow in a second direction to generate lift for the vehicle.
摘要翻译： 一种产生用于车辆的升降机的方法，包括具有燃烧器的燃气涡轮发动机，由燃烧器加热的芯流，以及绕过燃烧器的旁路。 该方法包括将来自旁路流的核心流的至少一部分分离，将核心流的分离部分沿第一方向引导以产生用于车辆的升力，将旁路流的至少一部分与核心流隔离， 并且将旁路流的一部分分离在第二方向上以产生用于车辆的升力。
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公开(公告)号：US07395988B2
公开(公告)日：2008-07-08
申请号：US11265655
申请日：2005-11-02
IPC分类号： B64C27/82
摘要： Aircraft including an airframe having a fuselage extending between a forward end and an aft end and a fixed wing extending laterally from the fuselage. The aircraft includes a power plant mounted on the airframe producing exhaust during operation. The aircraft includes a rotor/wing rotatably mounted on the airframe including a plurality of blades and an adjustable nozzle mounted on the airframe downstream from the power plant exhaust for selectively directing the power plant exhaust to exit the aircraft at a pre-selected angle with respect to the airframe within a range of angles extending from about horizontally rearward to about vertically downward.
摘要翻译： 飞机包括具有在前端和后端之间延伸的机身的机身和从机身横向延伸的固定翼。 飞机包括安装在机身上的发电厂，在运行期间产生排气。 飞行器包括可旋转地安装在机身上的转子/机翼，其包括多个叶片和安装在发电厂排气下游的机身上的可调节喷嘴，用于选择性地引导发电厂排气以相对于预定角度离开飞行器 在从大约水平向后延伸到大约垂直向下的角度范围内的机身上。
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公开(公告)号：US07267300B2
公开(公告)日：2007-09-11
申请号：US11065855
申请日：2005-02-25
IPC分类号： B64C15/02
CPC分类号： B64D35/04 , B64C15/14 , B64C29/0025 , F16H1/222
摘要： Aircraft comprising an airframe having a forward end, an aft end opposite the forward end, a top extending between the forward end and the aft end, and a bottom opposite the top side. The aircraft further includes a power plant mounted on the airframe. In addition, the aircraft includes at least two propellers rotatably mounted on the airframe and powered by the power plant for moving the aircraft in a generally forward direction during operation of the propellers. Also, the aircraft includes at least two counter-rotatable fan sets mounted on the airframe and powered by the power plant for providing upward lift to the aircraft during operation of the fan sets.
摘要翻译： 飞机包括具有前端，与前端相对的后端的机身，在前端和后端之间延伸的顶部和与顶侧相对的底部。 飞机还包括安装在机身上的发电厂。 此外，该飞行器包括至少两个可旋转地安装在机身上的推进器，并由动力装置供电，用于在螺旋桨操作期间沿大致向前的方向移动飞行器。 此外，飞行器包括安装在机身上并由发电厂供电的至少两个可逆旋转的风扇组，用于在风扇组的运行期间向飞机提供向上升力。
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10.发明授权Aircraft engine inlet hot gas and foreign object ingestion reduction and pitch control system 失效飞机引擎入口热气和异物摄入减少和俯仰控制系统
公开(公告)号：US5779169A
公开(公告)日：1998-07-14
申请号：US573047
申请日：1995-12-15
申请人： Mark L. Sloan
发明人： Mark L. Sloan
CPC分类号： F02K1/002 , B64C15/14 , B64C29/0066 , B64D33/02 , F02K3/025 , B64D2033/026
摘要： An aircraft for vertical or short take off and landing operations having two main lift nozzles, both positioned at or near the aircraft center of gravity utilizes one or more jet screen nozzles, arranged in a variety of shapes and combinations, discharging bypass air from a position forward of the center of gravity, and a variable pitch nozzle discharging engine exhaust gas mixed with bypass air from a position aft of the center of gravity, to achieve pitch control while airborne in vertical take off or landing mode. The jet screen nozzle also prevents or reduces ingestion of mixed hot exhaust gas and bypass air discharged through the main lift nozzles. The jet screen nozzle further prevents or reduces ingestion of foreign object debris disturbed by the vertical lift discharge flowing from the main lift nozzles. Lift improvement devices are deployed during short or vertical takeoff and landing operations to act as air dams to cause main lift nozzle discharge striking the ground and returning to the aircraft as a fountain flow and flowing against the lower surface of the aircraft, to separate from the aircraft surface and return toward the ground. This enhances lift effect on the aircraft while avoiding further hot exhaust gas flow along the aircraft skin surface and eventually into the aircraft engine inlet. A control system modulates the jet screen nozzle and aft pitch control nozzle, along with the cruise nozzle, main lift nozzles and other control nozzles so that total engine discharge flow area remains substantially constant through a range of pitch control and other maneuvering commands.
摘要翻译： 一种用于垂直或短时起飞和着陆作业的飞机，其具有两个位于飞机重心处或附近的主要提升喷嘴，其使用一个或多个喷射筛喷嘴，其布置成各种形状和组合，从旁边排出旁路空气 重心的前方，以及从重心位置排出与旁路空气混合的发动机废气的可变节距喷嘴，在垂直起飞或着陆模式下实现俯仰控制。 喷射式喷嘴还防止或减少了通过主提升喷嘴排出的混合热废气和旁路空气的摄取。 喷丝机喷嘴进一步防止或减少由从主升力喷嘴流出的垂直提升排放物而扰乱的异物碎屑摄取。 升降机设备在短时或垂直起飞和着陆作业期间部署，作为空气坝，使主升力喷头排放到地面并作为喷泉流返回飞机，并流向飞机的下表面，与飞机的下表面分离 飞机表面并返回地面。 这增强了对飞行器的提升效果，同时避免了沿着飞机皮肤表面的进一步的热废气流并且最终进入飞机发动机入口。 控制系统连同巡航喷嘴，主提升喷嘴和其他控制喷嘴一起调节喷射屏幕喷嘴和后桨距控制喷嘴，使得总发动机排气流动面积通过一系列俯仰控制和其他操纵命令保持基本恒定。
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