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公开(公告)号：US08376285B1
公开(公告)日：2013-02-19
申请号：US13159424
申请日：2011-06-14
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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公开(公告)号：US08336828B2
公开(公告)日：2012-12-25
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
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：US07823840B2
公开(公告)日：2010-11-02
申请号：US11927257
申请日：2007-10-29
IPC分类号： B64C3/50
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：US07726609B2
公开(公告)日：2010-06-01
申请号：US11687595
申请日：2007-03-16
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
摘要： Aircraft exhaust systems and methods are disclosed. In one embodiment, an integrated propulsion assembly includes a wing assembly having an upper surface and a lower surface, and a propulsion unit at least partially disposed within the wing assembly. An exhaust system is configured to conduct an exhaust flow emanating from the propulsion unit to an exhaust aperture. The exhaust aperture is positioned proximate a trailing edge of the wing assembly, and has an aspect ratio of at least five. In further embodiments, the wing assembly includes a flap member moveably coupled along a trailing edge portion of the wing assembly, and the exhaust aperture is configured to direct the exhaust flow over at least a portion of the flap member.
摘要翻译： 公开了飞机排气系统和方法。 在一个实施例中，集成推进组件包括具有上表面和下表面的翼组件，以及至少部分地布置在翼组件内的推进单元。 排气系统构造成将从推进单元发出的排气流导向排气孔。 排气孔位于翼组件的后缘附近，并且具有至少五的纵横比。 在另外的实施例中，翼组件包括可沿着翼组件的后缘部分可移动地联接的挡板构件，并且排气孔构造成将排气流引导至挡板构件的至少一部分。
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5.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：US07669785B2
公开(公告)日：2010-03-02
申请号：US11379971
申请日：2006-04-24
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 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。
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公开(公告)号：US4732289A
公开(公告)日：1988-03-22
申请号：US891756
申请日：1986-07-31
申请人： Rodney J. Granat , Roger W. Clark
发明人： Rodney J. Granat , Roger W. Clark
IPC分类号： B65D41/34
CPC分类号： B65D41/3433 , Y10S215/901
摘要： A tamper indicating closure member for containers is disclosed having a cap member with a top wall and a peripheral skirt integral therewith. Also included is a separable band portion interconnected to the skirt by a frangible bridge element. The band portion is capable of coacting with an axially inclined ramp surface defined by a circumferential bead on the neck, thereby substantially preventing transverse movement of the closure band portion relative to the container neck.
摘要翻译： 公开了用于容器的防篡改指示关闭构件，其具有顶盖和与其成一体的外围裙部的帽构件。 还包括通过易碎桥接元件与裙部互连的可分离带部分。 带部分能够与由颈部上的圆周胎圈限定的轴向倾斜的斜面共同作用，从而基本上防止封闭带部分相对于容器颈部的横向移动。
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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：US5507402A
公开(公告)日：1996-04-16
申请号：US238244
申请日：1994-05-04
申请人： Roger W. Clark
发明人： Roger W. Clark
CPC分类号： B65D1/0284
摘要： A plastics container includes a neck and an outlet opening, a container body and a base; the base comprising a plurality of circumferentially spaced legs, each leg terminating in a foot portion on which the container is adapted to stand wherein each leg is provided with at least one longitudinally inwardly extending crease. Preferably each leg is provided with a single crease which extends downwardly and inwardly at least to the extent necessary so to substantially divide the foot portion of each leg into two separate support portions on which the container is adapted to stand.
摘要翻译： 塑料容器包括颈部和出口，容器主体和底座; 所述基部包括多个周向间隔开的腿，每个腿终止于足部，所述容器适用于所述脚部，其中每个腿设置有至少一个纵向向内延伸的折痕。 优选地，每个腿部设置有单个折痕，其至少在必要的程度上向下和向内延伸，以便将每个腿部的脚部基本上分成两个单独的支撑部分，容器适用于其上。
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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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