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公开(公告)号：US11834186B2
公开(公告)日：2023-12-05
申请号：US17006965
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon , Andrew Breeze-Stringfellow
CPC classification number: B64D27/02 , B64C23/00 , B64D27/24 , B64D31/12 , F04D25/166
Abstract: An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.
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公开(公告)号：US20170096212A1
公开(公告)日：2017-04-06
申请号：US15206546
申请日：2016-07-11
Applicant: Sikorsky Aircraft Corporation
Inventor： Razvan Virgil Florea , Patrick Bowles , Barbara Brenda Botros , ByungYoung Min , Claude G. Matalanis , Brian E. Wake
Abstract: A rotor hub fairing system for use in a counter-rotating, coaxial rotor system is provided including an upper hub fairing defined about an axis and a lower hub fairing defined about the axis. A shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The geometry of the shaft fairing is configured to encourage a wake adjacent the upper hub fairing to form collectively with a wake adjacent the lower hub fairing.
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公开(公告)号：US20160325823A1
公开(公告)日：2016-11-10
申请号：US14705547
申请日：2015-05-06
Applicant: The Boeing Company
Inventor： Diane C. Rawlings , Timothy Leroy Williams , James C. McGarvey , James M. Kestner , Alan G. Burg
IPC: B64C21/10
CPC classification number: B64C21/10 , B32B3/30 , B41M3/00 , B42D25/324 , B44B5/0047 , B44B5/0095 , B44F1/02 , B64C23/00 , B64C2230/26 , B64D45/00 , F15D1/00 , G09F19/12 , G09F19/14 , G09F21/08 , Y02T50/166
Abstract: Aerodynamic microstructures having sub-microstructure are disclosed herein. One disclosed example apparatus includes an aerodynamic microstructure defining an external surface of a vehicle, and a pattern of sub-microstructures superimposed on the microstructure to convey a representation of an image.
Abstract translation: 本文公开了具有亚微观结构的气动微结构。 一个公开的示例性装置包括限定车辆的外表面的空气动力学微结构和叠加在微结构上以传送图像的表示的子微结构的图案。
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公开(公告)号：US09132914B2
公开(公告)日：2015-09-15
申请号：US13561399
申请日：2012-07-30
Applicant: Claude G. Matalanis , Brian E. Wake
Inventor： Claude G. Matalanis , Brian E. Wake
Abstract: A rotor hub fairing system for use in a counter-rotating, coaxial rotary wing aircraft is provided including an upper hub fairing defined about an axis. A lower hub fairing is similarly defined about the axis. An airfoil shaped shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The airfoil shaped shaft fairing has a thickness to chord (t/c) ratio in the range of about 20% and about 45%.
Abstract translation: 提供了一种用于逆向旋转同轴旋转翼飞行器的转子轮毂整流罩系统，其包括围绕轴线限定的上部轮毂整流罩。 下部轮毂整流罩类似地定义在轴上。 上部翼形整流罩和下部轮毂整流罩之间设置翼型轴整流罩。 翼型整流罩的厚度与弦（t / c）的比值在约20％和约45％之间。
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公开(公告)号：US09067674B2
公开(公告)日：2015-06-30
申请号：US13821196
申请日：2010-09-15
Applicant: Pontus Nordin , Göte Strindberg
Inventor： Pontus Nordin , Göte Strindberg
CPC classification number: B64C23/00 , B64C23/005 , B64C2230/12 , B82Y30/00 , F15D1/0075 , H05H1/2406 , H05H2001/2418 , Y02T50/166 , Y10T137/206
Abstract: The invention regards a plasma-enhanced active laminar flow actuator system (1) adapted to an aerodynamic surface (3) which has a nano-engineered composite material layer (5) comprising a set of electrodes arranged (7′, 7″) in at least an upper (P1) and a lower (P2) plane extending parallel with the aerodynamic surface (3); the electrodes (7′, 7″) comprising nano filaments (9); the electrodes (7′) of the upper plane (P1) are arranged in the aerodynamic surface (3) such that they define a smooth and hard aerodynamic surface (3); conductors (11, 11′) of nano filaments (9″) arranged for electrical communication between a control unit (13) and each of the electrodes (7′, 7″), wherein the control unit (13) is adapted to address current between cooperating electrodes (7′, 7″) of the upper and lower plane (P1, P2) from a current supply depending upon air flow characteristic signals fed from air flow sensor means (19).
Abstract translation: 本发明涉及一种适用于空气动力学表面（3）的等离子体增强型有源层流致动器系统（1），其具有纳米工程复合材料层（5），所述纳米工程复合材料层（5）包括一组电极（7'，7“） 至少与空气动力学表面（3）平行延伸的上部（P1）和下部（P2）平面; 包括纳米细丝（9）的电极（7'，7“）; 上平面（P1）的电极（7'）布置在空气动力学表面（3）中，使得它们限定平滑且硬的空气动力学表面（3）; 布置成用于在控制单元（13）和每个电极（7'，7“）之间电连通的纳米长丝（9”）的导体（11,11'），其中控制单元（13）适于寻址电流 根据从空气流量传感器装置（19）馈送的空气流特性信号，从电流源供应上和下平面（P1，P2）的配合电极（7'，7“）。
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Patent Agency Ranking
公开(公告)号：US20140312166A1
公开(公告)日：2014-10-23
申请号：US13745235
申请日：2013-01-18
Applicant: Xiaoyi ZHU
Inventor： Xiaoyi ZHU
IPC: B64C27/467 , B64C27/473 , B64C27/06
CPC classification number: B64C27/467 , B64C11/18 , B64C11/20 , B64C21/025 , B64C21/08 , B64C23/00 , B64C27/473 , Y02T50/166
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US20140224926A1
公开(公告)日：2014-08-14
申请号：US14176865
申请日：2014-02-10
Applicant: Gulfstream Aerospace Corporation
Inventor： Donald Freund
CPC classification number: B64C23/00 , B64C3/185 , B64C3/20 , B64C3/38 , B64C3/42 , B64C9/00 , B64C17/10 , B64C30/00 , B64D37/00 , Y02T50/14 , Y02T50/44
Abstract: A system for controlling a magnitude of a sonic boom includes a first sensor configured to detect a first condition of the supersonic aircraft. The system further includes a pair of wings configured to move fore and aft. The system further includes a processor communicatively coupled with the sensor and operatively coupled with the pair of wings. The processor is configured to (1) receive a first information from the first sensor indicative of the first condition, (2) calculate a lift distribution of the supersonic aircraft based on the first information, (3) determine an existence of a deviation of the lift distribution from a desired lift distribution based on the flight condition, and (4) control the pair of wings to move to redistribute the lift in a manner that more closely conforms to the desired lift distribution. The magnitude of the sonic boom is reduced when the deviation is reduced.
Abstract translation: 用于控制声波起重臂的大小的系统包括被配置为检测超音速飞行器的第一状态的第一传感器。 该系统还包括一对构造成前后移动的翼。 所述系统还包括处理器，其与所述传感器通信地耦合并且与所述一对机翼可操作地耦合。 处理器被配置为（1）从第一传感器接收指示第一条件的第一信息，（2）基于第一信息计算超音速飞机的升力分布，（3）确定存在 基于飞行条件从所需的升力分布提升分配，以及（4）控制所述一对翼移动以以更符合期望的升力分布的方式重新分配升力。 当偏差减小时，声音臂的大小减小。
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公开(公告)号：US08783337B2
公开(公告)日：2014-07-22
申请号：US11633082
申请日：2006-12-01
Applicant: Roderick A. Hyde , Nathan P. Myhrvold , Lowell L. Wood, Jr. , Alistair K. Chan , Clarence T. Tegreene
Inventor： Roderick A. Hyde , Nathan P. Myhrvold , Lowell L. Wood, Jr. , Alistair K. Chan , Clarence T. Tegreene
CPC classification number: B64C23/005 , B63B1/34 , B64C3/48 , B64C23/00 , B64C2230/02 , F15D1/12 , F28F13/02 , F28F13/06 , F28F27/00 , Y02T50/14 , Y02T50/166 , Y02T70/121
Abstract: A system and method for producing surface deformations on a surface of a body. The system and method relate to changing the convective heat transfer coefficient for a surface. The system includes a first surface being a surface of a body exposed to a fluid flow and at least one actuator affecting deformation of the first surface. The system also includes a control system providing control commands to the at least one actuator, the control commands configured to change deformations on the first surface in order to change the convective heat transfer coefficient of the first surface. Further, the system includes a sensor providing environmental characteristic information to the control system.
Abstract translation: 一种用于在身体表面上产生表面变形的系统和方法。 该系统和方法涉及改变表面的对流传热系数。 该系统包括第一表面，其是暴露于流体流动的主体的表面，以及影响第一表面的变形的至少一个致动器。 该系统还包括一个向至少一个致动器提供控制命令的控制系统，所述控制命令被配置为改变第一表面上的变形，以便改变第一表面的对流传热系数。 此外，该系统包括向控制系统提供环境特性信息的传感器。
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9.发明授权Ejector driven flow control for reducing velocity deficit profile downstream of an aerodynamic body 有权喷射器驱动的流量控制，用于减少气动体下游的速度差异曲线公开(公告)号：US08690106B1
公开(公告)日：2014-04-08
申请号：US12723678
申请日：2010-03-14
Applicant: Mark A. Reissig
Inventor： Mark A. Reissig
CPC classification number: B64C21/025 , B64C23/00 , B64C2230/04 , B64C2230/14 , B64D29/04 , B64D2027/005 , Y02T50/166 , Y02T50/66
Abstract: A system and method for reducing a velocity deficit from an aerodynamic body is disclosed. An air jet is injected into an ejector mixing chamber in the aerodynamic body. The air jet creates a suction effect in the ejector mixing chamber, which suctions boundary layer air from a perforated surface in at least one side of the aerodynamic body into a plenum chamber and into the ejector mixing chamber. The air jet ejects the boundary layer air and the air jet from a trailing edge slot of the ejector mixing chamber. Suctioning the boundary layer air and ejecting the boundary layer air and the air jet from the trailing edge slot reduces a velocity deficit on a trailing edge of the aerodynamic body. The reduced velocity deficit and the suctioning of boundary layer air reduce noise, turbulence, blade stress, and blade deformation.
Abstract translation: 公开了一种用于减少空气动力学体的速度缺陷的系统和方法。 将空气射流注入到空气动力体中的喷射器混合室中。 空气喷射器在喷射器混合室中产生吸入效应，喷射器混合室从空气动力体的至少一侧的穿孔表面吸入边界层空气进入增压室并进入喷射器混合室。 空气喷射器从喷射器混合室的后缘狭缝喷射边界层空气和空气射流。 吸入边界层空气并喷射边界层空气和来自后缘槽的空气射流减少了空气动力体的后缘上的速度缺陷。 减少的速度缺陷和边界层空气的吸力减少噪音，湍流，叶片应力和叶片变形。
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公开(公告)号：US20140030103A1
公开(公告)日：2014-01-30
申请号：US13561399
申请日：2012-07-30
Applicant: Claude G. Matalanis , Brian E. Wake
Inventor： Claude G. Matalanis , Brian E. Wake
IPC: B64C27/46
Abstract: A rotor hub fairing system for use in a counter-rotating, coaxial rotary wing aircraft is provided including an upper hub fairing defined about an axis. A lower hub fairing is similarly defined about the axis. An airfoil shaped shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The airfoil shaped shaft fairing has a thickness to chord (t/c) ratio in the range of about 20% and about 45%.
Abstract translation: 提供了一种用于逆向旋转同轴旋转翼飞行器的转子轮毂整流罩系统，其包括围绕轴线限定的上部轮毂整流罩。 下部轮毂整流罩类似地定义在轴上。 上部翼形整流罩和下部轮毂整流罩之间设置翼型轴整流罩。 翼型整流罩的厚度与弦（t / c）的比值在约20％和约45％之间。
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