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：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：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：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：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：US20060192626A1

公开(公告)日：2006-08-31

申请号：US11362649

申请日：2006-02-25

申请人： Bryan Milliren ,  Roger Clark

发明人： Bryan Milliren ,  Roger Clark

IPC分类号： H03B5/32

CPC分类号： H03B5/04 ,  H03B5/366 ,  H03L1/04

摘要： A double oven crystal oscillator (DOCXO) is disclosed which is highly stable by incorporating means to reduce the effects of ambient pressure changes on the frequency of the oscillator. The oscillator crystal is mounted in a temperature controlled inner oven to reduce the effects on the frequency stability of the oscillator. The oscillator circuitry and all circuitry associated with the inner oven is mounted in good thermal contact with the inner oven. A Faraday shield at ground potential is placed over the oscillator circuitry to minimize the effects of stray capacitance between the oscillator components and the case wall of the inner oven. The effects of minor deformations in the case walls within the oscillator caused by ambient pressure changes and other factors causing pressure changes are thereby greatly minimized. To further reduce effects on oscillator frequency stability the ovens of the DOCXO are temperature controlled, cases are hermetically sealed, the case walls are rigid, and ovens and cases may be evacuated.

摘要翻译： 公开了一种双炉晶体振荡器（DOCXO），其通过并入降低环境压力变化对振荡器频率的影响的方法而具有高度的稳定性。 振荡器晶体安装在温度控制的内部烘箱中，以减少对振荡器的频率稳定性的影响。 振荡器电路和与内部烘箱相关的所有电路与内部烘箱良好的热接触。 接地电位的法拉第屏蔽放置在振荡器电路上，以最小化振荡器部件与内部烘箱的壳体壁之间的杂散电容的影响。 由环境压力变化引起的振荡器外壳壁内的微小变形和导致压力变化的其他因素的影响因此大大降低。 为了进一步减少对振荡器频率稳定性的影响，DOCXO的炉子是温度控制的，壳体被气密密封，壳体壁是刚性的，并且炉子和壳体可能被排空。

公开(公告)号：US4951337A

公开(公告)日：1990-08-28

申请号：US182126

申请日：1988-04-15

申请人： Harold L. Hull ,  Roger Clark

发明人： Harold L. Hull ,  Roger Clark

IPC分类号： A42B1/24 ,  A47C16/00

CPC分类号： A42B1/24 ,  A47C7/383

摘要： A pillow designed and adapted to cover the back portion of a user's head such as a mechanic or workman, said pillow being secured to user's head by means of an elastic or adjustable strap thereby freeing up the use of both of the user's hands when the user is moving about on his back beneath a vehicle or the like, with the filling of the pillow being removable to facilitate the cleaning or washing of the pillow cover and strap, and with the section of the pillow which lays adjacent to the user's head containing means to attach a cap to cover the user's head which cap may also be provided with a visor or the like to protect the eyes of the user.

摘要翻译： 设计并适于覆盖使用者头部的后部的枕头，例如机械师或工人，所述枕头通过弹性或可调节的带固定到使用者的头部，从而当用户释放使用者的双手时使用 正在其后面的车辆或类似物上移动，枕头的填充是可移除的，以便于清洁或洗涤枕头盖和带子，并且枕头部分邻近使用者的头部容纳装置 为了安装盖子以覆盖用户的头部，该帽子还可以设置有遮阳板等，以保护用户的眼睛。