公开(公告)号：US20070045476A1

公开(公告)日：2007-03-01

申请号：US11332835

申请日：2006-01-13

申请人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark ,  Donald Leopold

发明人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark ,  Donald Leopold

IPC分类号： B64C23/06

CPC分类号： B64C23/076 ,  B64C23/065 ,  Y02T50/164

摘要： A system and method for dissipating vortices that form at the wingtips on aircraft and from other airfoils. A jet air stream is discharged in a location at or proximate to the outer end portion of the airfoil into the vortex flow, and the jet air stream is moved cyclically back and forth. The cyclic movement can be at lower or higher frequencies to alleviate at least in part intensity of the vortex or accelerate instability of the vortex which leads to vortex dissipation.

摘要翻译： 一种用于消散在飞机和其他翼型上的翼尖处形成的涡流的系统和方法。 喷气空气流在翼型的外端部分处或附近的位置被排放到涡流中，并且喷气流被循环地前后移动。 循环运动可以在较低或更高的频率以减轻涡流的至少部分强度或加速导致涡流耗散的涡流的不稳定性。

公开(公告)号：US07100875B2

公开(公告)日：2006-09-05

申请号：US10784067

申请日：2004-02-20

申请人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark ,  Donald Leopold

发明人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark ,  Donald Leopold

IPC分类号： B64C23/00

CPC分类号： B64C23/076 ,  B64C23/065 ,  Y02T50/164

摘要： A system and method for dissipating vortices that form at the wingtips on aircraft and from other airfoils. A jet air stream is discharged in a location at or proximate to the outer end portion of the airfoil into the vortex flow, and the jet air stream is moved cyclically back and forth. The cyclic movement can be at lower or higher frequencies to alleviate at least in part intensity of the vortex or accelerate instability of the vortex which leads to vortex dissipation.

公开(公告)号：US20050184196A1

公开(公告)日：2005-08-25

申请号：US10784067

申请日：2004-02-20

申请人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark ,  Donald Leopold

发明人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark ,  Donald Leopold

IPC分类号： B64C23/06

CPC分类号： B64C23/076 ,  B64C23/065 ,  Y02T50/164

摘要： A system and method for dissipating vortices that form at the wingtips on aircraft and from other airfoils. A jet air stream is discharged in a location at or proximate to the outer end portion of the airfoil into the vortex flow, and the jet air stream is moved cyclically back and forth. The cyclic movement can be at lower or higher frequencies to alleviate at least in part intensity of the vortex or accelerate instability of the vortex which leads to vortex dissipation.

摘要翻译： 一种用于消散在飞机和其他翼型上的翼尖处形成的涡流的系统和方法。 喷气空气流在翼型的外端部分处或附近的位置被排放到涡流中，并且喷气流被循环地前后移动。 循环运动可以在较低或更高的频率以减轻涡流的至少部分强度或加速导致涡流耗散的涡流的不稳定性。

公开(公告)号：US07597289B2

公开(公告)日：2009-10-06

申请号：US11332835

申请日：2006-01-13

申请人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark ,  Donald Leopold

发明人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark ,  Donald Leopold

IPC分类号： B64C23/00

CPC分类号： B64C23/076 ,  B64C23/065 ,  Y02T50/164

摘要： A system and method for dissipating vortices that form at the wingtips on aircraft and from other airfoils. A jet air stream is discharged in a location at or proximate to the outer end portion of the airfoil into the vortex flow, and the jet air stream is moved cyclically back and forth. The cyclic movement can be at lower or higher frequencies to alleviate at least in part intensity of the vortex or accelerate instability of the vortex which leads to vortex dissipation.

摘要翻译： 一种用于消散在飞机和其他翼型上的翼尖处形成的涡流的系统和方法。 喷气空气流在翼型的外端部分处或附近的位置被排放到涡流中，并且喷气流被循环地前后移动。 循环运动可以在较低或更高的频率以减轻涡流的至少部分强度或加速导致涡流耗散的涡流的不稳定性。

公开(公告)号：US20070246604A1

公开(公告)日：2007-10-25

申请号：US11379971

申请日：2006-04-24

申请人： Arvin Shmilovich ,  Yoram Yadlin ,  David Smith ,  Roger Clark

发明人： Arvin Shmilovich ,  Yoram Yadlin ,  David Smith ,  Roger Clark

IPC分类号： B64B1/36

CPC分类号： B64D33/06 ,  F02K1/06 ,  F02K3/06 ,  F05D2250/14 ,  Y02T50/671

摘要： Integrated engine exhaust systems and methods for reducing drag and thermal loads 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 configured 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： 公开了用于减少阻力和热负荷的集成发动机排气系统和方法。 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，其构造成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。

公开(公告)号：US20070051855A1

公开(公告)日：2007-03-08

申请号：US11200506

申请日：2005-08-09

申请人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark

发明人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark

IPC分类号： B64C21/04

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。

公开(公告)号：US20070034746A1

公开(公告)日：2007-02-15

申请号：US11200515

申请日：2005-08-09

申请人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark ,  David Manley

发明人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark ,  David Manley

IPC分类号： B64C21/00 ,  B64C21/04 ,  B64C9/16

CPC分类号： B64C9/16 ,  B64C9/22 ,  B64C21/02 ,  B64C21/04 ,  B64C2230/04 ,  B64C2230/06 ,  Y02T50/166 ,  Y02T50/32

摘要： A system and method for controlling boundary layer flow over an aircraft wing are provided. The system includes at least one wing element, and a plurality of ports defined in the wing element and in fluid communication with one another. The system also includes at least one fluidic device operable to continuously ingest the fluid through at least one of the ports and eject the fluid out of at least one other port to control boundary layer flow of the fluid over the wing element.

摘要翻译： 提供一种用于控制飞机机翼上的边界层流动的系统和方法。 该系统包括至少一个翼元件和限定在翼元件中并且彼此流体连通的多个端口。 该系统还包括至少一个流体装置，其可操作以通过至少一个端口连续摄取流体并将流体从至少一个其它端口排出，以控制流体在翼元件上的边界层流动。

公开(公告)号：US20080042013A1

公开(公告)日：2008-02-21

申请号：US11747112

申请日：2007-05-10

申请人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger Clark

发明人： Arvin Shmilovich ,  Yoram Yadlin ,  Roger 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。

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。

公开(公告)号：US07878458B2

公开(公告)日：2011-02-01

申请号：US11927290

申请日：2007-10-29

申请人： Arvin Shmilovich ,  Yoram Yadlin ,  Robert D. Gregg, III ,  Roger W. Clark

发明人： Arvin Shmilovich ,  Yoram Yadlin ,  Robert D. Gregg, III ,  Roger W. Clark

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。