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1. 发明授权

US10081420B2 Simplified fluidic oscillator for controlling aerodynamics of an aircraft 有权
公开(公告)号：US10081420B2
公开(公告)日：2018-09-25
申请号：US14955692
申请日：2015-12-01
申请人： THE BOEING COMPANY
发明人： Matthew T. Lakebrink , Mortaza Mani
IPC分类号： B64C1/00 , B64C21/02
CPC分类号： B64C21/025 , B64C21/04 , B64C2230/04 , B64C2230/18 , B64C2230/20 , B64C2230/22 , Y02T50/166
摘要： Method and apparatus for controlling the aerodynamics of an aircraft using an active flow control system is disclosed herein. In one example, the active flow control system includes an airframe and a plurality of fluidic oscillators. The airframe includes an inlet configured for flight speeds ranging from subsonic to hypersonic. The plurality of fluidic oscillators is mounted about a curvature of the airframe. Each fluidic oscillator includes a body and an integral nozzle coupled to the body. The body has an inflow portion and a narrow nozzle inlet formed opposite the inflow portion. The integral nozzle is coupled to the body by the narrow nozzle inlet. The narrow nozzle inlet forms a single fluid flow path from the inflow portion to the narrow nozzle inlet.

2. 发明申请

US20180251211A1 Fluid Systems That Include a Co-Flow Jet 审中-公开
公开(公告)号：US20180251211A1
公开(公告)日：2018-09-06
申请号：US15968786
申请日：2018-05-02
申请人： COFLOW JET, LLC
发明人： Gecheng Zha
IPC分类号： B64C21/02
CPC分类号： B64C21/025 , B64C3/141 , B64C2003/143 , B64C2230/04 , B64C2230/06 , Y02T50/12 , Y02T50/166
摘要： Fluid systems are described herein. An example embodiment of a fluid system has a lengthwise axis, a chord length, a first body portion, a second body portion, a spacer, and a fluid pressurizer. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. The first body portion defines a cavity that is sized and configured to filter debris that enters the channel during use and provide a mechanism for removing the debris from the system.

3. 发明授权

US10054048B2 Suprression of shock-induced airflow separation 有权
公开(公告)号：US10054048B2
公开(公告)日：2018-08-21
申请号：US13952088
申请日：2013-07-26
申请人： Lockheed Martin Corporation
发明人： Dan J. Baruzzini , Daniel N. Miller , Neal D. Domel , Jeff G. Hakes
IPC分类号： B64C21/04 , F02C7/04 , F15D1/00 , B64C21/02 , B64D33/02
CPC分类号： F02C7/04 , B64C21/025 , B64D2033/0226 , B64D2033/026 , F15D1/0095 , Y02T50/166 , Y10T137/0318 , Y10T137/0536
摘要： An apparatus for suppressing shock-induced separation of high speed airflow from a relatively low-energy boundary layer. The apparatus may include an actuator or array of actuators configured to alternately inhale and exhale fluid and positioned to alternately inhale fluid from and exhale fluid into a boundary layer of a fluid mass flowing along the wall. The actuator may be positioned to inhale fluid from a boundary layer separation bubble induced by a supersonic shock wave propagated in the fluid mass.

4. 发明申请

US20180079489A1 AIRFOIL FOR AN AIRCRAFT HAVING REDUCED NOISE GENERATION 审中-公开
公开(公告)号：US20180079489A1
公开(公告)日：2018-03-22
申请号：US15270634
申请日：2016-09-20
申请人： Gulfstream Aerospace Corporation
发明人： Judith Gallman , Thomas Van de Ven , Tyler Relf
IPC分类号： B64C9/18 , B64C21/02
CPC分类号： B64C9/18 , B64C21/025 , B64C21/08 , B64C2230/06 , B64C2230/14 , B64C2230/20 , Y02T50/166
摘要： An airfoil is provided having reduced noise generation for use with an aircraft. The airfoil includes a body and a cover. The body has a leading edge spaced from a trailing edge and a side surface disposed between the leading edge and the trailing edge. The body defines an inlet proximate the leading edge and configured to receive air. The side surface defines an outlet in fluid communication with the inlet. The outlet is configured to exhaust air away from the side surface. The cover overlies the inlet and is movable between a first and a second cover position. The cover is configured to prevent movement of air through the inlet when the cover is in the first cover position and configured to permit movement of air through the inlet when the cover is in the second cover position.

5. 发明申请

US20170267342A1 CROSS FLOW FAN WITH EXIT GUIDE VANES 审中-公开
公开(公告)号：US20170267342A1
公开(公告)日：2017-09-21
申请号：US15072657
申请日：2016-03-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Wesley K. Lord
IPC分类号： B64C39/00 , B64C23/02 , B64C11/00 , B64C21/02
CPC分类号： B64C39/005 , B64C11/006 , B64C21/025 , B64C23/02 , B64C2230/04 , F04D17/04 , Y02T50/166
摘要： A cross flow fan to be incorporated into an aircraft comprises a cross flow fan rotor to be positioned in an aircraft, a drive arrangement for the cross flow fan rotor, and a plurality of vanes positioned downstream of the cross flow fan rotor. An aircraft is also disclosed.

6. 发明申请

US20170267332A1 BOUNDARY-LAYER-INFLUENCING AERODYNAMIC PART AND METHOD FOR PRODUCING THE SAME 审中-公开
公开(公告)号：US20170267332A1
公开(公告)日：2017-09-21
申请号：US15458505
申请日：2017-03-14
申请人： Airbus Operations GmbH
发明人： Bernd Ruppert , Volker Robrecht
IPC分类号： B64C21/02
CPC分类号： B64C21/025 , B64C2230/20 , B64C2230/22 , Y02T50/166
摘要： A boundary-layer-influencing aerodynamic part comprises a carrier element provided with at least one air passage aperture for guiding an air flow through the carrier element, an air guiding layer disposed on the carrier element and a cover layer constituting at least a part of a flow surface and being configured to have air flow there through at least in sections. The air guiding layer is configured to have air flow there through with an air flow supplied to the part, at least in certain operating phases of the part, through the cover layer and flowing in the direction of the carrier element or through the air passage aperture of the carrier element and flowing in the direction of the cover layer. The cover layer is applied directly to the air guiding layer via an additive manufacturing method.

7. 发明申请

US20160376918A1 AIRCRAFT VAPOUR TRAIL CONTROL SYSTEM 审中-公开
标题翻译：飞机蒸汽拖车控制系统
公开(公告)号：US20160376918A1
公开(公告)日：2016-12-29
申请号：US15163318
申请日：2016-05-24
申请人： ROLLS-ROYCE plc
发明人： Peter SWANN , Andrew M. ROLT , Paul FLETCHER
IPC分类号： F01D21/00 , B64D27/18 , F02K3/06 , B64D27/24 , F02C3/04 , F02C7/22
CPC分类号： F01D21/003 , B64C21/025 , B64C23/065 , B64D27/18 , B64D27/24 , B64D2027/026 , F01D15/10 , F01D17/24 , F02C3/04 , F02C7/22 , F02K3/06 , F02K3/075 , F05D2220/323 , F05D2260/42 , F05D2270/306
摘要： The invention concerns an aircraft propulsion system having an engine core within which fuel is combusted to produce an exhaust containing water produced from the combustion of fuel, at least one propulsive fan for generating a mass flow of air which mixes with the exhaust of the engine core, and one or more sensor arranged to sense a condition indicative of vapour trail formation by the exhaust flow from the engine; and a controller arranged to control the ratio of the mass flow of water in the exhaust to the mass flow of air propulsed by the propulsive fan such that the ratio is reduced upon sensing of said condition by the one or more sensor.
摘要翻译：本发明涉及一种具有发动机芯的飞行器推进系统，其中燃料被燃烧以产生包含由燃料燃烧产生的水的排气，至少一个推进风扇，用于产生与发动机芯的排气混合的大量空气流以及一个或多个传感器，其被布置成感测通过来自发动机的排气流指示蒸气轨道形成的状况; 以及控制器，其布置成控制排气中的水质量流与由推进风扇推进的空气的质量流量的比率，使得在通过一个或多个传感器感测到所述条件时，比率减小。

8. 发明授权

US09315264B2 Helicopter and aircraft power device 有权
标题翻译：直升机和飞机动力装置
公开(公告)号：US09315264B2
公开(公告)日：2016-04-19
申请号：US13745235
申请日：2013-01-18
申请人： Xiaoyi Zhu
发明人： Xiaoyi Zhu
IPC分类号： B64C27/467 , B64C27/473 , B64C11/18 , B64C11/20 , B64C21/02 , B64C21/08 , B64C23/00
CPC分类号： B64C27/467 , B64C11/18 , B64C11/20 , B64C21/025 , B64C21/08 , B64C23/00 , B64C27/473 , Y02T50/166
摘要： A helicopter and aircraft power device has a plurality of fluid inlets on a windward side of a blade housing and a plurality of fluid outlets on a leeward side in a manner that the fluid inlets communicate with the fluid outlets. The path where the fluid flows in the lengthwise direction on the windward side of the blade housing is far greater than the path where the fluid flows in the widthwise direction on the leeward side of the blade housing, generating a very large pressure difference between the leeward side and the windward side. The action of the centrifugal force and a suction force from a suction motor significantly increase the flowing speed on the windward side of the blade and in the fluid passage, generating bigger pressure difference on either sides of the propeller and thus forming more powerful lift force and driving force.
摘要翻译：直升机和飞机动力装置具有在叶片壳体的迎风侧上的多个流体入口和在背风侧上的多个流体出口，使得流体入口与流体出口连通。流体在叶片壳体的迎风侧沿长度方向流动的路径远大于流体在叶片壳体的背风侧沿宽度方向流动的路径，从而在背风之间产生非常大的压力差侧面和迎风面。离心力的作用和来自抽吸马达的抽吸力明显增加了叶片迎风侧和流体通道中的流动速度，从而在螺旋桨两侧产生较大的压力差，从而形成更强大的提升力，推动力。

9. 发明授权

US09243622B2 Bellows synthetic jet 有权
标题翻译：波纹管合成射流
公开(公告)号：US09243622B2
公开(公告)日：2016-01-26
申请号：US13899754
申请日：2013-05-22
申请人： The Boeing Company
发明人： Steven Griffin , Edward A. Whalen , Shawn Haar
IPC分类号： B64C21/00 , F04B43/00 , F15D1/00 , B64C21/02 , B64C21/08
CPC分类号： F04B43/00 , B64C21/025 , B64C21/08 , B64C2230/18 , F15D1/0095 , Y02T50/166
摘要： A device for generating a synthetic jet is described. The device can include a flap, an actuator coupled to the flap and a chamber including an aperture. The flap forms a portion of the chamber. The flap is configured to oscillate in a flapping motion such that fluid is alternately drawn into the chamber via the aperture and expelled from the chamber via the aperture to form the synthetic jet. In some embodiments, multiple flaps can be used on a device to generate the synthetic jet.
摘要翻译：描述了一种用于产生合成射流的装置。该装置可以包括翼片，联接到翼片的致动器和包括孔的腔室。翼片形成腔室的一部分。翼片被构造成以扑动运动振荡，使得流体经由孔被交替地吸入腔室并经由孔从腔室排出以形成合成射流。在一些实施例中，可以在设备上使用多个翼片以产生合成射流。

10. 发明申请

US20160009391A1 Stable Low Aspect Ratio Flying Wing 审中-公开
标题翻译：稳定的低纵横比飞翼
公开(公告)号：US20160009391A1
公开(公告)日：2016-01-14
申请号：US14070586
申请日：2013-11-04
申请人： Eric Walter Friesel
发明人： Eric Walter Friesel
IPC分类号： B64C39/10 , B64C21/06 , B64C25/34 , B64C5/10 , B64C1/00
CPC分类号： B64C39/10 , B64C3/10 , B64C5/08 , B64C21/025 , B64C2039/105 , B64C2230/20 , Y02T50/12 , Y02T50/166
摘要： A low aspect ratio flying wing provides aerodynamic stability throughout the flight envelope with improved aerodynamic efficiency. Insufficient stability and reduced aerodynamic efficiency typical of low aspect ratio flying wings is improved through wing design and proper application and placement of horizontal stabilizers and boundary layer control. Lateral asymmetric boundary layer manipulation is employed to alter flying wing orientation in flight. Lateral extension and retraction of the main structure wing optimizes efficiency. This novel flying wing is not found in literature or “prior art” and provides improvement in aerodynamic stability and efficiency over previous designs. Given the large amount of research, literature, patents and activity in the field since the 1930's and the absence of a practical design indicates the non-obvious nature of these disclosures. In addition, those skilled in the art teach away from present disclosures failing to realize the better than predicted advantages.
摘要翻译：飞行翼的低纵横比提供了整个飞行范围内的空气动力学稳定性，并提高了空气动力学效率。通过机翼设计和水平稳定器和边界层控制的适当应用和布置，改进了低纵横比飞翼的稳定性和降低的空气动力学效率。采用横向不对称边界层操纵来改变飞行中的飞翼方位。主结构翼的横向延伸和缩回优化了效率。这种新颖的飞翼在文学或“现有技术”中没有找到，并提供了空气动力学稳定性和效率与先前设计相比的改进。鉴于自20世纪30年代以来，该领域的研究，文献，专利和活动量大，缺乏实用设计，表明这些披露的不明显性质。此外，本领域技术人员教导了不能实现优于预测优点的当前披露。

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