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1. 发明授权

US10875658B2 Ejector and airfoil configurations 有权
公开(公告)号：US10875658B2
公开(公告)日：2020-12-29
申请号：US16031586
申请日：2018-07-10
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
IPC分类号： B64C23/00 , B64D33/04 , B64C39/02 , B64C15/14 , B64C9/38 , B64C15/00 , B64C21/00 , B64D27/10 , B64C21/04 , F02K1/36 , F02K1/00 , F02C3/04 , F02C6/04 , B64D27/18 , B64D29/02 , B64D33/02
CPC分类号： B64D33/04 , B64C9/38 , B64C15/00 , B64C15/14 , B64C21/00 , B64C21/04 , B64C23/005 , B64C39/024 , B64D27/10 , B64D27/18 , B64D29/02 , B64D33/02 , F02C3/04 , F02C6/04 , F02K1/002 , F02K1/36 , B64C2201/10 , B64C2201/104 , B64C2230/04 , B64C2230/16 , B64D2033/0273 , F05D2220/90 , Y02T50/10 , Y02T50/30 , Y02T50/40
摘要： A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

2. 发明申请

US20190210714A1 AERODYNAMIC ELEMENT OF AN AIRCRAFT, COMPRISING A SET OF PROTRUDING ELEMENTS 审中-公开
公开(公告)号：US20190210714A1
公开(公告)日：2019-07-11
申请号：US16239730
申请日：2019-01-04
申请人： Airbus Operations S.A.S.
发明人： Mathias Farouz-Fouquet
IPC分类号： B64C21/10
CPC分类号： B64C3/141 , B64C21/00 , B64C23/06 , B64C2003/148 , B64C2230/26 , B64D29/00
摘要： An aerodynamic element is provided with at least one set of protruding elements, each of the protruding elements is produced in the form of an elongate and profiled rib projecting from a surface of the aerodynamic element. The protruding elements are arranged at the surface of the aerodynamic element, one beside the other, being oriented substantially parallel to one another so that each of them generates a vortex, the set of vortices thus generated making it possible to reduce crossflow instability.

3. 发明申请

US20180201362A1 AIRCRAFT WITH A VARIABLE FUSELAGE SURFACE FOR BOUNDARY LAYER OPTIMIZATION 审中-公开
公开(公告)号：US20180201362A1
公开(公告)日：2018-07-19
申请号：US15849250
申请日：2017-12-20
申请人： Airbus Operations, S.L.
发明人： Alberto Arana Hidalgo , Raúl Carlos Llamas Sandín , Jesús Javier Vázquez Castro
IPC分类号： B64C21/10 , B64C21/06 , B64D29/04
CPC分类号： B64C21/10 , B64C1/0009 , B64C21/00 , B64C21/06 , B64D27/14 , B64D27/20 , B64D29/04 , B64D33/02 , B64D2033/0226 , B64D2033/0273 , B64D2033/0286 , Y02T50/12 , Y02T50/166
摘要： An aircraft including a propulsion system formed by engines arranged to ingest boundary layer air. These engines are placed inside of nacelles partially embedded in the aircraft fuselage and, thus, their intake conduits are delimited by specific fuselage areas and the nacelles. For the specific fuselage areas skins are disclosed with a flexible portion and actuation systems over them for changing their surfaces to adapt them to the needs of the propulsion system.

4. 发明申请

US20180148162A1 AIRCRAFT HAVING A DRAG COMPENSATION DEVICE BASED ON A BOUNDARY LAYER INGESTING FAN 审中-公开
公开(公告)号：US20180148162A1
公开(公告)日：2018-05-31
申请号：US15820593
申请日：2017-11-22
申请人： Airbus Operations GmbH
发明人： Bernd Trahmer
IPC分类号： B64C21/00 , B64C11/30 , B64C1/00
CPC分类号： B64C21/00 , B64C1/0009 , B64C11/30 , B64C21/06 , B64C2230/04 , B64C2230/28 , B64D27/02 , B64D27/24 , B64D2027/026 , Y02T50/166
摘要： An aircraft includes a fuselage having a tapered rear shape, a landing gear for moving the aircraft on a runway, a wing attached to the fuselage, at least a main engine for providing a main thrust and a rear fan, wherein the rear fan is attached to a tail section of the fuselage, wherein the aircraft is designed for conducting a take-off rotation around the landing gear during take-off from the runway, such that the tail section of the fuselage approaches the runway, wherein the rear fan is an open fan having fan blades extending in a radial direction to a longitudinal axis of the fuselage, wherein the fan blades are dimensioned to equal at least a boundary layer thickness of the flow along the fuselage and to be smaller than the gap between the runway and the tail section of the fuselage during the take-off rotation.

5. 发明申请

US20170341726A1 OPTICAL WINDOW SYSTEM WITH AERO-OPTICAL CONDUCTIVE BLADES 审中-公开
公开(公告)号：US20170341726A1
公开(公告)日：2017-11-30
申请号：US15678589
申请日：2017-08-16
申请人： Raytheon Company
发明人： David A. Vasquez , Michael Ushinsky , Joseph J. Ichkhan
IPC分类号： B64C1/14 , B64C23/06 , F42B10/46 , B32B37/30 , H05B3/84 , B64C21/00 , F42B15/34 , B64D47/08
CPC分类号： B64C1/1484 , B32B37/30 , B64C1/1492 , B64C21/00 , B64C23/06 , B64C2230/10 , B64D47/08 , F42B10/46 , F42B15/34 , H05B3/84 , Y02T50/162 , Y02T50/166
摘要： A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive material—each having an edge adjacent to, parallel with, and at least partially coextensive with each other—is described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window.

6. 发明授权

US09725159B2 Mitigating shock using plasma 有权
公开(公告)号：US09725159B2
公开(公告)日：2017-08-08
申请号：US14936953
申请日：2015-11-10
申请人： The Boeing Company
发明人： Mark Joseph Clemen, Jr. , Donald V. Drouin, Jr. , Alan F. Stewart
IPC分类号： B64C23/00 , B64C21/00
CPC分类号： B64C21/00 , B64C23/00 , B64C23/005 , B64C30/00 , B64C2230/12
摘要： A method, apparatus, and system for mitigating undesired effects of a vehicle traveling at a speed greater than a critical Mach number for the vehicle. Ultraviolet energy is generated using a plurality of ultraviolet energy sources associated with an interior structure of the vehicle that travels at the speed greater than the critical Mach number for the vehicle. The ultraviolet energy is transported from the plurality of ultraviolet energy sources past an exterior of the vehicle around a selected location of the vehicle. A plasma is created around the selected location to mitigate the undesired effects of the vehicle traveling at the speed greater than the critical Mach number for the vehicle.

7. 发明申请

US20170190436A1 DISTRIBUTED ELECTRIC DUCTED FAN WING 审中-公开
公开(公告)号：US20170190436A1
公开(公告)日：2017-07-06
申请号：US15374771
申请日：2016-12-09
申请人： David G. Ullman , Vincent Homer
发明人： David G. Ullman , Vincent Homer
IPC分类号： B64D27/24 , B64D29/02 , B64C3/32 , B64C3/44 , B64D31/06
CPC分类号： B64D27/24 , B64C3/32 , B64C21/00 , B64D29/02 , B64D31/06 , Y02T50/166 , Y02T50/44 , Y02T50/64
摘要： The Distributed Electric Ducted Fan Wing concept incorporates multiple electric ducted fans on lifting surfaces configured to provide integrated aerodynamics and propulsion resulting in enhanced aerodynamic characteristics and thus aircraft performance. The concept uses a plurality of electric ducted fans (EDFs) to not only provide thrust, but to also blow air across the upper surface of a substantial portion of the lifting surface area increasing lift at little loss in efficiency. Not only can the total lift on the surfaces be enhanced, but the lift distribution managed: to aid in aircraft control; ameliorate the effects of turbulence: reduce shed vortices; mitigate the effects of system failures; eliminate stalls; and compensate for crosswinds. This concept offers the potential for increasing electric airplane efficiency and performance, enhancing Short Takeoff and Landing (STOL) capabilities, improving passenger comfort, and reducing the structural stress and cost of aircraft.

8. 发明授权

US09541106B1 Plasma optimized aerostructures for efficient flow control 有权
标题翻译：等离子体优化航空结构，实现有效的流量控制
公开(公告)号：US09541106B1
公开(公告)日：2017-01-10
申请号：US11710750
申请日：2007-02-26
申请人： Mehul Patel , Thomas Corke , Alan B. Cain
发明人： Mehul Patel , Thomas Corke , Alan B. Cain
IPC分类号： B64C29/00 , F15D1/00 , B64C21/00
CPC分类号： F15D1/0065 , B64C15/14 , B64C21/00 , B64C2230/12 , F15D1/0075 , Y02T50/166
摘要： The present invention relates to a method of designing or optimizing a control surface for use with plasma actuators for controlling an aircraft, missile, munition or automobile, and more particularly to controlling fluid flow across their surfaces or other surfaces using plasma actuators, which would benefit from such a method. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and automobiles. The method of flow control also provides a means for reducing aircraft, missile's, munition's and automobile's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices.
摘要翻译：本发明涉及一种设计或优化用于控制飞机，导弹，弹药或汽车的等离子体致动器的控制表面的方法，更具体地涉及使用等离子致动器来控制流过其表面或其它表面的流体，这将有利于从这样的方法。各种实施例提供了增加飞机，导弹，弹药和汽车的效率的步骤。流量控制方法还为减少飞机，导弹，弹药和汽车的电力需求提供了手段。这些方法还提供了使用低功率无铰链等离子体致动器装置的空气动力学控制的替代方法。

9. 发明申请

US20160009360A1 OPTICAL WINDOW SYSTEM WITH AERO-OPTICAL CONDUCTIVE BLADES 审中-公开
标题翻译：具有光电导电叶片的光学窗系统
公开(公告)号：US20160009360A1
公开(公告)日：2016-01-14
申请号：US14330493
申请日：2014-07-14
申请人： Raytheon Company
发明人： David A. Vasquez , Michael Ushinsky , Joseph J. Ichkhan
IPC分类号： B64C1/14 , B32B37/30 , H05B3/84
CPC分类号： B64C1/1484 , B32B37/30 , B64C1/1492 , B64C21/00 , B64C23/06 , B64C2230/10 , B64D47/08 , F42B10/46 , F42B15/34 , H05B3/84 , Y02T50/162 , Y02T50/166
摘要： A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive material—each having an edge adjacent to, parallel with, and at least partially coextensive with each other—is described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window.
摘要翻译：本文描述了改善在流体流动中操作并且具有第一和第二透光材料的光学窗口的光学特性的方法，每个光学透镜材料具有彼此相邻，平行并且至少部分共同延伸的边缘。该方法包括在导光材料的第一和第二窗玻璃的两个相邻边缘之间插入导热叶片; 以及通过将导热叶片从光学窗口的窗格的外表面突出到流体流中来提升光学窗口向前的不利的流动停滞区域。

10. 发明申请

US20150232172A1 AIRFOIL ASSEMBLY AND METHOD 审中-公开
标题翻译：气翼组件和方法
公开(公告)号：US20150232172A1
公开(公告)日：2015-08-20
申请号：US14185804
申请日：2014-02-20
申请人： Donald Steve Morris
发明人： Donald Steve Morris
IPC分类号： B64C21/00 , B64C5/02
CPC分类号： B64C21/00 , B64C23/005 , Y02T50/166
摘要： Airfoil assemblies and methods of using them are provided to accelerate air flow relative to the airfoil assemblies and to improve laminar air flow over airfoils. The airfoil may include a cathode disposed near a leading portion of the airfoil to ionize on rushing air and for initiating an electric field. An anode disposed near an opposite portion of the airfoil completes the electric field to accelerate ionized air flowing relative to the airfoil, whereby ionized positively charged air particles tend to separate and accelerate continuously toward the anode in a substantially smooth laminar path of travel uninterruptedly. An air ionizing antenna may be employed for radiating an electromagnetic field transversely to the electric field to cause the electromagnetic field to ionize additional air flowing relative to the airfoil.
摘要翻译：提供翼型组件和使用它们的方法以加速相对于翼型组件的空气流动并且改善翼型件上的层流空气流动。翼型件可以包括设置在翼型件的引导部分附近的阴极，以在冲刷空气中离子化并且用于启动电场。设置在翼型件的相对部分附近的阳极完成电场以加速相对于翼型流动的电离空气，由此离子化的带正电的空气颗粒趋向于以不间断的基本平滑的层流路径朝向阳极分离和加速。可以使用空气电离天线来辐射横向于电场的电磁场，以使电磁场离开相对于翼型流动的附加空气。

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