专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

21. 发明授权

US4619423A Geometries for roughness shapes in laminar flow 失效
标题翻译：层流中粗糙形状的几何
公开(公告)号：US4619423A
公开(公告)日：1986-10-28
申请号：US550681
申请日：1983-11-10
申请人： Bruce J. Holmes , Glenn L. Martin , Christopher S. Domack , Clifford J. Obara , Ahmed A. Hassan
发明人： Bruce J. Holmes , Glenn L. Martin , Christopher S. Domack , Clifford J. Obara , Ahmed A. Hassan
IPC分类号： B64C21/10
CPC分类号： B64C21/10 , B64C2230/20 , Y02T50/166
摘要： This invention is for a passive laminar flow airfoil which has an upper skin 12 and lower skin 14 joined at a trailing edge 16. A leading edge structure 20, such as de-icing equipment, is joined to the upper and lower skins by interface mechanisms 30 and 35. Generally, the interface mechanisms are forward facing steps, with or without adjacent gaps, shaped and dimensioned to accomplish laminar flow using standard airfoil manufacturing techniques.
摘要翻译：本发明涉及一种被动层流翼型件，其具有在后缘16处连接的上皮12和下皮14。诸如除冰设备的前缘结构20通过界面机构连接到上皮和下皮通常，接口机构是面向前的步骤，具有或不具有相邻间隙，其形状和尺寸被设计成使用标准翼型件制造技术来实现层流。

22. 发明授权

US09908617B2 Active flow control for transonic flight 有权
公开(公告)号：US09908617B2
公开(公告)日：2018-03-06
申请号：US13114006
申请日：2011-05-23
申请人： Ahmed A. Hassan , Casey L. Madsen , Garrett M Billman , Mary M. Billman
发明人： Ahmed A. Hassan , Casey L. Madsen , Garrett M Billman
IPC分类号： B64C3/00 , B64C15/14 , B64C21/02
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.

23. 发明申请

US20110309201A1 ACTIVE FLOW CONTROL FOR TRANSONIC FLIGHT 有权
标题翻译：用于航空飞行的主动流量控制
公开(公告)号：US20110309201A1
公开(公告)日：2011-12-22
申请号：US13114006
申请日：2011-05-23
申请人： Ahmed A. Hassan , Casey L. Madsen , Garrett M. Billman , Mary M. Billman
发明人： Ahmed A. Hassan , Casey L. Madsen , Garrett M. Billman , Mary M. Billman
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。

24. 发明授权

US08016245B2 Dynamic bumps for drag reduction at transonic-supersonic speeds 有权
标题翻译：用于跨超声速度减阻的动态碰撞
公开(公告)号：US08016245B2
公开(公告)日：2011-09-13
申请号：US11583140
申请日：2006-10-18
申请人： Ahmed A. Hassan , Bradley A. Osborne , Scott Schwimley , Garry Billman , Mary Billman, legal representative
发明人： Ahmed A. Hassan , Bradley A. Osborne , Scott Schwimley , Garry Billman
IPC分类号： B64C21/08 , B64C23/04 , B64C23/06
CPC分类号： B64C23/04 , B64C2003/148 , Y02T50/12
摘要： A system for reducing overall drag of a mobile platform includes a surface on which an airflow forms a boundary layer and a generally normal shockwave. The airflow is at a first velocity that is one of transonic and supersonic. An oscillating jet injects and extracts a jet flow through the surface. The jet flow is at a second velocity that is substantially less than the first velocity. A recirculation region is upstream of the normal shockwave and is disposed at least partially in the boundary layer. The recirculation region is established at least by the oscillating jet. A generally oblique wave is established by the recirculation region and weakens the normal shockwave to reduce the overall drag experienced by the surface.
摘要翻译：用于减少移动平台的整体拖动的系统包括气流形成边界层的表面和通常正常的冲击波。气流处于跨音速和超音速之一的第一速度。振荡射流注入并提取穿过表面的喷射流。射流处于基本上小于第一速度的第二速度。再循环区域是正常冲击波的上游，并且至少部分地设置在边界层中。至少通过振荡射流建立再循环区域。一般倾斜的波浪由再循环区域建立，削弱了正常的冲击波，减少了表面经受的整体阻力。

25. 发明授权

US07255309B2 Vernier active flow control effector 有权
标题翻译：游标主动流量控制效应器
公开(公告)号：US07255309B2
公开(公告)日：2007-08-14
申请号：US10890639
申请日：2004-07-14
申请人： Clete M. Boldrin , Ahmed A. Hassan
发明人： Clete M. Boldrin , Ahmed A. Hassan
IPC分类号： B64C21/04
CPC分类号： B64C21/08 , B64C2230/04 , B64C2230/18 , Y02T50/166
摘要： Methods and apparatus for controlling the attitude of a mobile platform with a resolution suitable for vernier attitude control. In a preferred embodiment, a method includes flowing fluid through an orifice of an aerodynamic surface. The method also includes modifying a boundary layer of the aerodynamic surface with the flowing fluid. Another preferred embodiment provides an aerodynamic member of a mobile platform. The aerodynamic member includes an aerodynamic surface, an orifice, an actuator, and a fluid moving member. The orifice is in the aerodynamic surface and the actuator is subject to friction and backlash. The fluid moving member communicates with the orifice and causes the fluid to flow through the orifice to modify the boundary layer of aerodynamic surface.
摘要翻译：用于以适合游标态度控制的分辨率来控制移动平台姿态的方法和装置。在优选实施例中，一种方法包括使流体流过空气动力学表面的孔口。该方法还包括用流动的流体改变空气动力学表面的边界层。另一个优选实施例提供了一种移动平台的空气动力学构件。空气动力学构件包括空气动力学表面，孔，致动器和流体移动构件。孔口处于空气动力学表面，致动器经受摩擦和间隙。流体移动构件与孔口连通并使流体流过孔口以改变空气动力学表面的边界层。

26. 发明授权

US07195210B2 Fiber matrix for a geometric morphing wing 有权
标题翻译：用于几何变形翼的纤维矩阵
公开(公告)号：US07195210B2
公开(公告)日：2007-03-27
申请号：US10357022
申请日：2003-02-03
申请人： Brian K. Hamilton , Stephen Lewis Guymon , Gregory E. Dockter , Ahmed A. Hassan
发明人： Brian K. Hamilton , Stephen Lewis Guymon , Gregory E. Dockter , Ahmed A. Hassan
IPC分类号： B64C3/46
CPC分类号： B64C3/54 , B64C3/30 , B64C3/38 , B64C3/46 , B64C5/10 , B64C27/473 , B64C2003/445 , Y02T50/14
摘要： An airfoil member (14) includes a geometric morphing device (18). The geometric morphing device (18) has an inflatable member (30). The inflatable member (30) has an exterior wall (32) and multiple inflated states. The exterior wall (32) includes a layer with one or more fibers embedded therein. The exterior wall (32) controls size, shape, and expansion ability of the geometric morphing device (18).
摘要翻译：机翼构件（14）包括几何变形装置（18）。几何变形装置（18）具有可充气构件（30）。可膨胀构件（30）具有外壁（32）和多个充气状态。外壁（32）包括具有嵌入其中的一个或多个纤维的层。外壁（32）控制几何变形装置（18）的尺寸，形状和膨胀能力。

27. 发明授权

US5711651A Blade vortex interaction noise reduction techniques for a rotorcraft 失效
公开(公告)号：US5711651A
公开(公告)日：1998-01-27
申请号：US662601
申请日：1996-06-13
申请人： Bruce D. Charles , Ahmed A. Hassan , Hormoz Tadghighi , Ram D. JanakiRam , Lakshmi N. Sankar
发明人： Bruce D. Charles , Ahmed A. Hassan , Hormoz Tadghighi , Ram D. JanakiRam , Lakshmi N. Sankar
IPC分类号： B64C27/00 , B64C27/46 , F01D5/00
CPC分类号： B64C27/001 , B64C27/463 , B64C2027/7266 , Y02T50/34
摘要： An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The flap may be actuated in any conventional way, and is scheduled to be actuated to a deflected position during rotation of the rotor blade through predetermined regions of the rotor azimuth, and is further scheduled to be actuated to a retracted position through the remaining regions of the rotor azimuth. Through the careful azimuth-dependent deployment and retraction of the flap over the rotor disk, blade tip vortices which are the primary source for BVI noise are (a) made weaker and (b) pushed farther away from the rotor disk (that is, larger blade-vortex separation distances are achieved).

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式