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公开(公告)号：US20090173835A1
公开(公告)日：2009-07-09
申请号：US11370099
申请日：2006-03-07
CPC分类号： B64C23/076 , B64C23/065 , Y02T50/164
摘要： Apparatuses and methods for the controlled trailing wake flows are disclosed. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device carried by the airfoil, with the vortex dissipation device including a fluid flow nozzle, a valve device, and a controller. The fluid flow nozzle can be coupleable to a source of pressurized fluid and can include an orifice positioned to direct a flow of fluid outwardly from the tip. The valve device can be coupled in fluid communication with the fluid flow nozzle to selectively control the flow passing through the orifice. The controller can be coupled to the valve device to direct the operation of the valve device. Accordingly, the vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated.
摘要翻译： 公开了用于受控拖尾尾流的装置和方法。 根据一个实施例的装置涉及一种飞行器系统，其包括具有第一和第二相对面向的流动表面和尖端的翼型件。 该系统还可以包括由翼型件携带的涡流消散装置，涡流消散装置包括流体流动喷嘴，阀装置和控制器。 流体流动喷嘴可以耦合到加压流体源，并且可以包括定位成将流体流从尖端向外引导的孔。 阀装置可以与流体流动喷嘴流体连通地联接，以选择性地控制通过孔口的流动。 控制器可以联接到阀装置以引导阀装置的操作。 因此，可以启动涡流消散装置以加速涡流（例如，翼尖涡流）在其产生之后消散的速率。
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公开(公告)号：US07661629B2
公开(公告)日：2010-02-16
申请号：US11370099
申请日：2006-03-07
CPC分类号： B64C23/076 , B64C23/065 , Y02T50/164
摘要： Apparatuses and methods for the controlled trailing wake flows. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device carried by the airfoil, with the vortex dissipation device including a fluid flow nozzle, a valve device, and a controller. The fluid flow nozzle can be coupleable to a source of pressurized fluid and can include an orifice positioned to direct a flow of fluid outwardly from the tip. The valve device can be coupled in fluid communication with the fluid flow nozzle to selectively control the flow passing through the orifice. The controller can be coupled to the valve device to direct the operation of the valve device. Accordingly, the vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated.
摘要翻译： 用于受控拖尾尾流的装置和方法。 根据一个实施例的装置涉及一种飞行器系统，其包括具有第一和第二相对面向的流动表面和尖端的翼型件。 该系统还可以包括由翼型件携带的涡流消散装置，涡流消散装置包括流体流动喷嘴，阀装置和控制器。 流体流动喷嘴可以耦合到加压流体源，并且可以包括定位成将流体流从尖端向外引导的孔。 阀装置可以与流体流动喷嘴流体连通地联接，以选择性地控制通过孔口的流动。 控制器可以联接到阀装置以引导阀装置的操作。 因此，可以启动涡流消散装置以加速涡流（例如，翼尖涡流）在其产生之后消散的速率。
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公开(公告)号：US20110108672A1
公开(公告)日：2011-05-12
申请号：US12617214
申请日：2009-11-12
申请人： Arvin Shmilovich , Yoram Yadlin , Roger W. Clark
发明人： Arvin Shmilovich , Yoram Yadlin , Roger W. Clark
IPC分类号： B64C21/04
CPC分类号： B64C21/04 , B64C9/18 , B64C9/38 , Y02T50/166 , Y02T50/32
摘要： An apparatus comprises a platform configured to move in a streamwise direction, an actuation unit associated with a control surface of the platform, a fluid source configured to supply an airflow to the actuation unit, and a control unit for moving an air jet across the control surface. The actuation unit is configured to form a traversing air jet pointing in the streamwise direction.
摘要翻译： 一种设备包括：被配置为沿流动方向移动的平台，与平台的控制表面相关联的致动单元，被配置为向致动单元供应气流的流体源，以及用于使空气流跨过控制器移动的控制单元 表面。 致动单元构造成形成指向流动方向的横穿空气喷射。
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公开(公告)号：US20090108125A1
公开(公告)日：2009-04-30
申请号：US11927257
申请日：2007-10-29
CPC分类号： B64C21/04 , B64C9/38 , Y02T50/166
摘要： Coanda Effect and lift produced along a surface of an airfoil are increased by ducting compressed fluid from the engine to the surface of the airfoil. An engine produces exhaust gases that are predominantly directed toward an aft end of the aircraft by a cowling or other structure as an exhaust plume. One or more internal ducts extend from the engine to the surface of the airfoil to thereby transmit a compressed fluid from the engine to the surface in order to suppress flow separation along the surface, thereby causing the engine exhaust flow to remain attached to the surface over a wider span. Such structures and techniques may find particular use in aircraft designed to exploit upper surface blowing (USB) techniques and structures for short takeoff and landing (STOL) performance.
摘要翻译： 通过将压缩流体从发动机引导到翼型件的表面，沿着翼型件的表面产生的附壁效应和升力增加。 发动机产生主要通过整流罩或其他结构作为排气羽流朝向飞行器的后端的废气。 一个或多个内部管道从发动机延伸到翼面的表面，从而将压缩的流体从发动机传递到表面，以便抑制沿着表面的流动分离，从而使发动机排气流保持附着在表面上 更宽的跨度 这种结构和技术可以在设计用于利用上表面吹风（USB）技术和用于短起飞和着陆（STOL））性能的结构的飞机中发现。
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公开(公告)号：US08033510B2
公开(公告)日：2011-10-11
申请号：US11200506
申请日：2005-08-09
申请人： Arvin Shmilovich , Yoram Yadlin , Roger W. Clark
发明人： Arvin Shmilovich , Yoram Yadlin , Roger W. Clark
CPC分类号： B64C9/16 , B64C9/22 , B64C21/025 , B64C2230/04 , B64C2230/06 , B64C2230/18 , Y02T50/166 , Y02T50/32 , Y02T50/44
摘要： A system and method for generating lift provided by a multi-element aircraft wing are provided. The system includes a main wing element, a slat interconnected to the main wing element, and a flap interconnected to the main wing element. The system also includes at least one port defined in at least one of the slat, main wing element, and flap. In addition, the system includes at least one fluidic device operable to regulate fluid flow into and out of the at least one port to control boundary layer flow over at least one of the slat, main wing element, and flap.
摘要翻译： 提供了一种用于产生由多元件飞机机翼提供的升降机的系统和方法。 该系统包括主翼元件，与主翼元件相互连接的板条以及与主翼元件互连的翼片。 该系统还包括限定在板条，主翼元件和翼片中的至少一个中的至少一个端口。 此外，该系统包括至少一个流体装置，其可操作以调节进入和离开至少一个端口的流体流动，以控制边界层在板条，主翼元件和翼片中的至少一个上的流动。
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公开(公告)号：US08087618B1
公开(公告)日：2012-01-03
申请号：US12500419
申请日：2009-07-09
IPC分类号： B64C3/50
CPC分类号： B64C9/38 , B64C21/04 , Y02T50/166
摘要： A propulsion system for an aircraft includes an airfoil, an engine having an engine cowling carried by the airfoil and configured to produce exhaust gases that are predominantly directed toward an aft end of the airfoil by the engine cowling as engine exhaust, a propulsion flap carried by the airfoil and disposed aft of the engine cowling and a plurality of exhaust ejection orifices provided in the propulsion flap and adapted to receive at least a portion of the exhaust gases from the engine cowling.
摘要翻译： 用于飞机的推进系统包括翼型件，发动机，其具有由翼型件承载的发动机整流罩，并且构造成产生主要通过作为发动机排气的发动机整流罩指向翼型的后端的排气，由...引导的推进翼 所述翼型件和所述发动机整流罩的后部以及设置在所述推进翼片中的多个排气喷射孔，并且适于接收来自所述发动机整流罩的废气的至少一部分。
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公开(公告)号：US20090108141A1
公开(公告)日：2009-04-30
申请号：US11927290
申请日：2007-10-29
CPC分类号： B64C9/38 , B64C3/58 , B64C7/00 , B64C21/04 , B64C2230/04 , Y02T50/166
摘要： Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling extends outwardly from the surface of the airfoil that has an exit plane configured for directing exhaust gases toward a rear of the aircraft. Fences extending outwardly from the surface and proximate to the exit plane of the engine cowling are configured to guide the exhaust gases along at least a portion of the airfoil surface, thereby restricting spanwise movement of the gases and increasing the Coanda Effect exhibited by the gases, thereby increasing the amount of lift produced along the surface of the airfoil. Such techniques may be used in short take-off and landing (STOL) aircraft.
摘要翻译： 由飞机的翼型产生的升力通过抑制从翼型的表面的流体分离而增加。 发动机整流罩从翼型件的表面向外延伸，其具有用于将废气引导到飞行器后部的出口平面。 从表面向外延伸并且靠近发动机整流罩的出口平面的围栏被构造成沿着翼面表面的至少一部分引导废气，从而限制气体的翼展运动并增加气体所展示的附壁效应， 从而增加沿着翼面的表面产生的升力量。 这种技术可以用于短时起飞（STOL）飞机。
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公开(公告)号：US08016244B2
公开(公告)日：2011-09-13
申请号：US11747112
申请日：2007-05-10
申请人： Arvin Shmilovich , Yoram Yadlin , Roger W. Clark
发明人： Arvin Shmilovich , Yoram Yadlin , Roger W. Clark
IPC分类号： B64C23/06
CPC分类号： B64C23/076 , B64C23/065 , Y02T50/164
摘要： Active systems and methods for controlling aircraft vortices are disclosed. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device carried by the airfoil, with the vortex dissipation device including an orifice positioned to direct a flow of fluid outwardly from the tip, an actuator operatively coupled to the fluid flow orifice and positioned to change a manner in which flow is directed outwardly from the tip, and a controller operatively coupled to the actuator to direct the operation of the actuator. The vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated, for example, by alternately pulsing flow inwardly and outwardly through the fluid flow orifice.
摘要翻译： 公开了用于控制飞行器旋涡的主动系统和方法。 根据一个实施例的装置涉及一种飞行器系统，其包括具有第一和第二相对面向的流动表面和尖端的翼型件。 该系统还可以包括由翼型件承载的涡流耗散装置，其中涡流消散装置包括定位成将流体流从尖端向外引导的孔口，致动器可操作地联接到流体流动孔口并且定位成改变 该流动从尖端向外指向，并且控制器可操作地联接到致动器以引导致动器的操作。 涡流消散装置可以被激活以加速涡流（例如，翼尖涡流）在其产生之后消散的速率，例如通过交替地脉冲流动通过流体流动孔口向内和向外流动。
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9.发明授权公开(公告)号：US07878458B2
公开(公告)日：2011-02-01
申请号：US11927290
申请日：2007-10-29
IPC分类号： B64C21/04
CPC分类号： B64C9/38 , B64C3/58 , B64C7/00 , B64C21/04 , B64C2230/04 , Y02T50/166
摘要： Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling extends outwardly from the surface of the airfoil that has an exit plane configured for directing exhaust gases toward a rear of the aircraft. Fences extending outwardly from the surface and proximate to the exit plane of the engine cowling are configured to guide the exhaust gases along at least a portion of the airfoil surface, thereby restricting spanwise movement of the gases and increasing the Coanda Effect exhibited by the gases, thereby increasing the amount of lift produced along the surface of the airfoil. Such techniques may be used in short take-off and landing (STOL) aircraft.
摘要翻译： 由飞机的翼型产生的升力通过抑制从翼型的表面的流体分离而增加。 发动机整流罩从翼型件的表面向外延伸，其具有用于将废气引导到飞行器后部的出口平面。 从表面向外延伸并且靠近发动机整流罩的出口平面的围栏被构造成沿着翼面表面的至少一部分引导废气，从而限制气体的翼展运动并增加气体所展示的附壁效应， 从而增加沿着翼面的表面产生的升力量。 这种技术可以用于短时起飞（STOL）飞机。
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10.发明授权Integrated engine exhaust systems and methods for drag and thermal stress reduction 有权一体化发动机排气系统和减少和减少热应力的方法公开(公告)号：US07798423B1
公开(公告)日：2010-09-21
申请号：US12686639
申请日：2010-01-13
申请人： Arvin Shmilovich , Yoram Yadlin , David M. Smith , Roger W. Clark
发明人： Arvin Shmilovich , Yoram Yadlin , David M. Smith , Roger W. Clark
IPC分类号： B63H11/10
CPC分类号： B64D33/06 , F02K1/06 , F02K3/06 , F05D2250/14 , Y02T50/671
摘要： Integrated engine exhaust systems and techniques for operating integrated engine exhaust systems are disclosed. In one embodiment, a propulsion system includes an engine installation configured to be mounted on a wing assembly of an aircraft. The engine installation includes an engine, and an exhaust system operatively coupled to the engine. The exhaust system includes at least one nozzle to exhaust an exhaust flow from the engine. The nozzle includes a variable portion configured to vary an exit aperture of the nozzle from a first shape to a second shape to change a flowfield shape of at least a portion of the nozzle flowfield proximate the wing assembly, thereby reducing at least one of drag and thermal loading on the wing assembly. In a further embodiment, the exhaust system includes an inner nozzle that exhausts a core exhaust flow, and an outer nozzle that exhausts a secondary exhaust flow, the outer nozzle having the variable portion configured to vary the exit aperture of the outer nozzle.
摘要翻译： 公开了用于操作集成发动机排气系统的集成发动机排气系统和技术。 在一个实施例中，推进系统包括构造成安装在飞行器的翼组件上的发动机装置。 发动机安装包括发动机和可操作地联接到发动机的排气系统。 排气系统包括至少一个喷嘴以排出来自发动机的排气流。 喷嘴包括可变部分，其被配置为将喷嘴的出口孔从第一形状改变到第二形状，以改变靠近翼组件的喷嘴流场的至少一部分的流场形状，从而减少阻力和 机翼组件上的热负荷。 在另一实施例中，排气系统包括排出核心排气流的内部喷嘴和排出二次排气流的外部喷嘴，外部喷嘴具有可变部分，以改变外部喷嘴的出口孔径。
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