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31. 发明授权

US09637223B1 Aircraft and missile afterbody flow control device and method of controlling flow 有权
公开(公告)号：US09637223B1
公开(公告)日：2017-05-02
申请号：US13457686
申请日：2012-04-27
申请人： Jack DiCocco , Troy Prince , Mehul Patel , Tsun Ming Terry Ng
发明人： Jack DiCocco , Troy Prince , Mehul Patel , Tsun Ming Terry Ng
IPC分类号： B64C21/00
CPC分类号： B64C21/00 , B64C5/12 , F41G7/00 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , G05D1/0088
摘要： An afterbody flow control system is used for aircraft or missile flow control to provide enhanced maneuverability and stabilization. A method of operating the flow control system is also described. The missile or aircraft comprises an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.

32. 发明授权

US09567056B2 Devices, systems and methods for passive control of flow 有权
标题翻译：用于流量被动控制的设备，系统和方法
公开(公告)号：US09567056B2
公开(公告)日：2017-02-14
申请号：US14199899
申请日：2014-03-06
申请人： General Atomics Aeronautical Systems, Inc.
发明人： Siegfried Hermann Zerweckh , Michael Rudolf Ruith , Steven James Ruther , Pritesh Chetan Mody
IPC分类号： F15B21/00 , B64C21/00 , B64C1/00 , B64C7/00 , B64D43/00 , F15D1/00 , F15D1/12 , B64C23/06
CPC分类号： B64C1/0009 , B64C7/00 , B64C21/00 , B64C23/06 , B64D43/00 , F15D1/003 , F15D1/0085 , F15D1/12 , Y02T50/162 , Y10T137/2082 , Y10T137/2224
摘要： Systems, devices and methods are disclosed for controlling the flow of a fluid over the window of an optical instrument housing in a freestream flow field. For example, the flow upstream of the housing may be split to create a flow region over the window that is conducive to successful operation of the instrument. The flow region may be maintained for various rotations of the housing about yaw, pitch, and roll axes. The disclosed features in some embodiments induce flow regions with reduced spatial and temporal density gradients of the flow over the window.
摘要翻译：公开了用于控制在自由流动流场中光学仪器壳体的窗口上的流体流动的系统，装置和方法。例如，壳体上游的流动可以被分开以在窗口上方形成有助于仪器成功运行的流动区域。流动区域可以保持围绕偏转，俯仰和滚动轴线的壳体的各种旋转。在一些实施例中公开的特征引起具有减小的窗口上的流动的空间和时间密度梯度的流动区域。

33. 发明申请

US20160332741A1 AIRCRAFT 审中-公开
标题翻译：飞机
公开(公告)号：US20160332741A1
公开(公告)日：2016-11-17
申请号：US15135040
申请日：2016-04-21
申请人： ROLLS-ROYCE plc
发明人： Matthew MOXON
IPC分类号： B64D33/02 , B64C11/00 , B64D33/04 , B64D27/10 , B64D29/04 , B64C3/50 , B64D27/24
CPC分类号： B64D33/02 , B64C3/50 , B64C11/001 , B64C15/00 , B64C21/00 , B64D27/02 , B64D27/10 , B64D27/24 , B64D29/04 , B64D33/04 , B64D2027/026 , B64D2033/0226 , Y02T50/166 , Y02T50/44
摘要： An aircraft including trailing edge flaps, a wing mounted propulsor positioned such that the flaps are located in a slipstream of the first propulsor in use when deployed. The aircraft further including a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor includes a ducted fan configurable between a first mode, in which the fan provides net forward thrust to the aircraft, and a second mode in which the fan provides net drag to the aircraft. The fan is positioned to ingest a boundary layer airflow in use when operating in the first mode.
摘要翻译：一种包括后缘翼片的飞行器，安装在机翼上的推进器，其被定位成使得当展开时，翼片位于第一推进器的滑流中。所述飞机还包括推力可矢量的推进器，其构造成在至少一个平面中选择性地改变推进器的排气流出矢量。可推力可推动推进器包括可在第一模式之间配置的管道风扇，其中风扇向飞机提供净前推力，以及第二模式，其中风扇向飞机提供净拖动。当在第一模式下操作时，风扇被定位成摄取使用中的边界层气流。

34. 发明授权

US09120552B2 Fuselage and method for reducing drag 有权
标题翻译：机身和减少阻力的方法
公开(公告)号：US09120552B2
公开(公告)日：2015-09-01
申请号：US13605920
申请日：2012-09-06
申请人： Gennady Trofimovich Kreshchishin , Larisa Trofimovna Kreshchishina
发明人： Gennady Trofimovich Kreshchishin , Larisa Trofimovna Kreshchishina
IPC分类号： B64C1/00 , B64C1/26 , B64C5/02 , B64D27/14 , B64C21/00 , B64C1/14
CPC分类号： B64C1/0009 , B64C1/14 , B64C1/26 , B64C5/02 , B64C21/00 , B64D27/14 , Y02T50/12 , Y02T50/166
摘要： Aircraft engineering applicable for improving aerodynamic quality of helicopters, airplanes, including big airbuses and amphibian airplanes, aerodynamic ground-effect and air-cushion vehicles, by reducing contact area between the external fuselage tail section surface and a high-speed air flow, area of contact is reduced by increasing surface area of holes in the fuselage tail section. To increase lifting force without increasing pressure resistance, the aerodynamic channel bottom is convex upwards, for example, curved upwards according to the shape of the airfoil convex side. The upper hole for the aerodynamic channel in the fuselage skin may be located along the fin middle portion divided lengthwise by the fin to right and left, in two. The aerodynamic channel is made through and may be open. The upper front edge aligned hole of the aerodynamic channel has a greater surface area than the rear hole aligned with the fuselage end.
摘要翻译：飞机工程适用于通过减少外部机身尾部截面与高速气流之间的接触面积，改善直升机，飞机，包括大型空中客车和两栖飞机，空气动力地面效应和气垫车辆的空气动力学质量，通过增加机身尾部的孔的表面积来减少接触。为了在不增加耐压性的情况下增加提升力，空气动力通道底部向上凸起，例如，根据翼型凸侧的形状向上弯曲。机身皮肤空气动力学通道的上部孔可以沿翅片中间部分沿翅片左右方向分成两部分。空气动力学通道通过并且可以是开放的。空气动力学通道的上前缘对齐孔具有比与机身端对准的后孔更大的表面积。

35. 发明申请

US20130240667A1 Aircraft comprising fairings for correcting its dissymmetry or lateral asymmetry 审中-公开
标题翻译：飞机包括校正其不对称或侧向不对称的整流罩
公开(公告)号：US20130240667A1
公开(公告)日：2013-09-19
申请号：US13793222
申请日：2013-03-11
申请人： AIRBUS OPERATIONS (SAS)
发明人： Cyril Guichot , Fabien Latourelle
IPC分类号： B64C7/00
CPC分类号： B64C7/00 , B64C17/00 , B64C21/00 , Y02T50/166
摘要： An aircraft having an asymmetry or a lateral geometric dissymmetry and comprising at least one pair of wings to each of which are fixed at least one fairing, each fairing comprising a surface connected to the lower surface of the wing and extending longitudinally in the direction of a longitudinal axis of the fuselage. The surface of at least one of the fairings has at least one local geometric deformation which is suitable for producing a corrective rolling moment to compensate for the undesirable rolling moment produced by the asymmetry or the lateral dissymmetry of the aircraft.
摘要翻译：具有不对称或侧向几何不对称的飞机，并且包括至少一对翼，每个翼固定至少一个整流罩，每个整流罩包括连接到翼的下表面的表面，并且沿着机身纵轴。至少一个整流罩的表面具有至少一个局部几何变形，其适于产生校正滚动力矩以补偿由飞行器的不对称性或侧向不对称性产生的不期望的滚动力矩。

36. 发明申请

US20130193268A1 BLUFF BODY NOISE CONTROL 有权
标题翻译： BLUFF身体噪音控制
公开(公告)号：US20130193268A1
公开(公告)日：2013-08-01
申请号：US13680598
申请日：2012-11-19
申请人： AIRBUS OPERATIONS LIMITED
发明人： Leung Choi CHOW , Matthew SPITERI , Xin ZHANG , David ANGLAND , Michael GOODYER
IPC分类号： B64C1/40
CPC分类号： B64C1/40 , B64C21/00 , B64C23/00 , B64C25/001 , B64C25/16 , B64C2025/003 , B64C2230/14 , Y02T50/166
摘要： An aircraft noise-reduction apparatus comprise a flow-facing element (1) and a flow control device (2) positioned downstream of the flow-facing element (1). The flow control device (2) is arranged, in use, to reduce noise induced by unsteady flow downstream of the flow-facing element (1).
摘要翻译：飞机降噪装置包括位于流向元件（1）下游的流动元件（1）和流量控制装置（2）。流量控制装置（2）在使用中被布置为减少由流动元件（1）下游的不稳定流引起的噪声。

37. 发明申请

US20130062460A1 FUSELAGE AND METHOD FOR REDUCING DRAG 审中-公开
标题翻译：用于减少DRAG的熔融和方法
公开(公告)号：US20130062460A1
公开(公告)日：2013-03-14
申请号：US13605920
申请日：2012-09-06
申请人： Gennady Trofimovich KRESHCHISHINA , Larisa Trofimovna KRESHCHISHINA
发明人： Gennady Trofimovich KRESHCHISHINA , Larisa Trofimovna KRESHCHISHINA
IPC分类号： B64C1/38 , B64C1/26 , B64C1/14 , B64C5/00 , B64C5/02 , B64D27/14 , B64C23/00
CPC分类号： B64C1/0009 , B64C1/14 , B64C1/26 , B64C5/02 , B64C21/00 , B64D27/14 , Y02T50/12 , Y02T50/166
摘要： Aircraft engineering applicable for improving aerodynamic quality of helicopters, airplanes, including big airbuses and amphibian airplanes, aerodynamic ground-effect and air-cushion vehicles, by reducing contact area between the external fuselage tail section surface and a high-speed air flow, area of contact is reduced by increasing surface area of holes in the fuselage tail section. To increase lifting force without increasing pressure resistance, the aerodynamic channel bottom is convex upwards, for example, curved upwards according to the shape of the airfoil convex side. The upper hole for the aerodynamic channel in the fuselage skin may be located along the fin middle portion divided lengthwise by the fin to right and left, in two. The aerodynamic channel is made through and may be open. The upper front edge aligned hole of the aerodynamic channel has a greater surface area than the rear hole aligned with the fuselage end.
摘要翻译：飞机工程适用于通过减少外部机身尾部截面与高速气流之间的接触面积，改善直升机，飞机，包括大型空中客车和两栖飞机，空气动力地面效应和气垫车辆的空气动力学质量，通过增加机身尾部的孔的表面积来减少接触。为了在不增加耐压性的情况下增加提升力，空气动力通道底部向上凸起，例如，根据翼型凸侧的形状向上弯曲。机身皮肤空气动力学通道的上部孔可以沿翅片中间部分沿翅片左右方向分成两部分。空气动力学通道通过并且可以是开放的。空气动力学通道的上前缘对齐孔具有比与机身端对准的后孔更大的表面积。

38. 发明授权

US08191833B1 Aircraft and missile afterbody flow control device and method of controlling flow 有权
标题翻译：飞机和导弹后体流量控制装置及流量控制方法
公开(公告)号：US08191833B1
公开(公告)日：2012-06-05
申请号：US11415534
申请日：2006-05-02
申请人： Jack DiCocco , Troy Prince , Mehul Patel , Tsun Ming Terry Ng
发明人： Jack DiCocco , Troy Prince , Mehul Patel , Tsun Ming Terry Ng
IPC分类号： B64C21/00
CPC分类号： B64C21/00 , B64C5/12 , F41G7/00 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , G05D1/0088
摘要： The present invention relates to an afterbody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization. The present invention further relates to a method of operating the flow control system.In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor each having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.
摘要翻译：本发明涉及后体流量控制系统，更具体地涉及用于增强机动性和稳定性的飞机或导弹流量控制系统。本发明还涉及一种操作流量控制系统的方法。在一个实施例中，本发明包括一个包括后身体和前体的导弹或飞机; 在导弹或飞机后身上至少有一个可激活的流动执行器; 每个具有信号的至少一个传感器，所述至少一个传感器被定位成检测导弹或飞机后身上的力或流动状况; 和闭环控制系统; 其中所述闭环控制系统用于至少部分地基于所述至少一个传感器的信号来激活和去激活所述至少一个可激活的流动效应器。

39. 发明授权

US07977615B1 Aircraft and missile forebody flow control device and method of controlling flow 有权
标题翻译：飞机和导弹前身流量控制装置及流量控制方法
公开(公告)号：US07977615B1
公开(公告)日：2011-07-12
申请号：US11800606
申请日：2007-05-07
申请人： Troy Prince , Frederick J. Lisy , Mehul P. Patel , Jack M. DiCocco , Reed Carver , Robert N. Schmidt
发明人： Troy Prince , Frederick J. Lisy , Mehul P. Patel , Jack M. DiCocco , Reed Carver , Robert N. Schmidt
IPC分类号： F42B15/01 , F42B15/10 , B64C5/10
CPC分类号： B64C21/00 , B64C5/12 , F41G7/00 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , G05D1/0088
摘要： A forebody flow control system and more particularly to aircraft or missile flow control systems for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one flow effector on the missile or aircraft forebody; at least one sensor having a signal associated therewith, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one flow effector based on at least in part the signal of the at least one sensor.
摘要翻译：前身流量控制系统，更具体地涉及飞机或导弹流量控制系统，用于在高攻角下增强机动性和稳定性。本发明还涉及一种操作流量控制系统的方法。在一个实施例中，本发明包括一个包括后身体和前体的导弹或飞机; 导弹或飞机前身上至少有一个流动执行器; 至少一个传感器具有与之相关联的信号，所述至少一个传感器被定位成检测导弹或飞行器前体上的流动分离; 和闭环控制系统; 其中所述闭环控制系统用于至少部分地基于所述至少一个传感器的信号来激活和去激活所述至少一个流动效应器。

40. 发明授权

US07907038B2 Electromagnetic flow control, methods and uses 有权
标题翻译：电磁流量控制，方法和用途
公开(公告)号：US07907038B2
公开(公告)日：2011-03-15
申请号：US12100890
申请日：2008-04-10
申请人： Frank K. Lu , Donald R. Wilson , J. Craig Dutton
发明人： Frank K. Lu , Donald R. Wilson , J. Craig Dutton
IPC分类号： H01F3/00 , F16K31/02
CPC分类号： B64C21/00 , B64C23/005 , B64C2230/12 , Y02T50/166
摘要： Actuation for control of surfaces is provided through use of a conducting material comprising electrolyte particles electrically charged with electromagnetic fields in boundary layers. Interactions of the electrically charged particles with electromagnetic fields in boundary layers are coordinated for generation of control forces for various applications.
摘要翻译：通过使用包含在边界层中带有电磁场的电解质颗粒的导电材料来提供用于控制表面的致动。带电粒子与边界层中的电磁场的相互作用被协调以产生用于各种应用的控制力。

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