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1. 发明授权

US09963223B2 Aerodynamic force sensing apparatus 有权
公开(公告)号：US09963223B2
公开(公告)日：2018-05-08
申请号：US13007099
申请日：2011-01-14
申请人： Kurt M. Chankaya , Brant H. Maines
发明人： Kurt M. Chankaya , Brant H. Maines
IPC分类号： G06F19/00 , B64C23/06
CPC分类号： B64C23/076 , Y02T50/164
摘要： An aerodynamic force sensing apparatus for providing an air data computer with information to calculate air data. The apparatus includes a plurality of vanes supportable in a vane array extending from a distal end of an airfoil of an aircraft, and one or more sensors configured to sense the response of one or more vanes of the vane array to aerodynamic forces and to transmit corresponding signals to an air data computer (ADC) for use by the ADC in calculating air data.

2. 发明申请

US20180029696A1 ACTIVE WINGLET 审中-公开
公开(公告)号：US20180029696A1
公开(公告)日：2018-02-01
申请号：US15707991
申请日：2017-09-18
申请人： Tamarack Aerospace Group, Inc.
发明人： Nicholas R. Guida
IPC分类号： B64C23/06 , B64C13/16
CPC分类号： B64C23/065 , B64C13/16 , B64C23/076 , Y02T50/164
摘要： An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency.

3. 发明申请

US20170290214A1 AERODYNAMICALLY EFFICIENT LIGHTWEIGHT VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH MULTI-CONFIGURATION WING TIP MOUNTED ROTORS 审中-公开
公开(公告)号：US20170290214A1
公开(公告)日：2017-10-05
申请号：US15351463
申请日：2016-11-15
申请人： JOBY AVIATION, INC.
发明人： JOEBEN BEVIRT , EDWARD STILSON , ALEX STOLL , PRANAY SINHA
IPC分类号： B64C23/06 , B64C29/00 , B64D27/24 , B64D27/02
CPC分类号： B64C23/065 , B64C23/076 , B64C29/0025 , B64C29/0033 , B64D27/24 , B64D2027/026 , Y02T50/164 , Y02T50/44 , Y02T50/62
摘要： An aerial vehicle adapted for vertical takeoff and landing using a set of wing tip mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the wings in a horizontal flight attitude then transitions to a horizontal flight path. An aerial vehicle which uses different configurations of its wing tip mounted, VTOL enabling rotors to reduce drag in all flight modes.

4. 发明授权

US09567066B2 Controllable airflow modification device periodic load control 有权
标题翻译：可控气流修改装置定期进行负载控制
公开(公告)号：US09567066B2
公开(公告)日：2017-02-14
申请号：US14173746
申请日：2014-02-05
申请人： Tamarack Aerospace Group, Inc.
发明人： Nicholas R. Guida
IPC分类号： B64C23/06 , B64C13/16
CPC分类号： B64C13/16 , B64C23/076 , Y02T50/164 , Y02T50/44
摘要： An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, reduce torsional loads, alleviate flutter, and/or increase efficiency.
摘要翻译：主动翼延伸部包括基本上平行于飞行器的翼的主体部分，好像它是机翼的延伸部分。主体部分可附接到飞行器机翼并且包括耦合到其上的多个可控气流改变装置。由于具有多个可控气流改变装置，机翼延伸部能够响应于飞行中的条件来调节多个可控气流改变装置的控制表面，以减少机翼载荷，改善机翼疲劳特性，增加范围，减少扭转载荷，减轻颤动，和/或提高效率。

5. 发明申请

US20120185181A1 Aerodynamic Force Sensing Apparatus 有权
标题翻译：气动力传感装置
公开(公告)号：US20120185181A1
公开(公告)日：2012-07-19
申请号：US13007099
申请日：2011-01-14
申请人： Kurt M. Chankaya , Brant H. Maines
发明人： Kurt M. Chankaya , Brant H. Maines
IPC分类号： G06F19/00
CPC分类号： B64C23/076 , Y02T50/164
摘要： An aerodynamic force sensing apparatus for providing an air data computer with information to calculate air data. The apparatus includes a plurality of vanes supportable in a vane array extending from a distal end of an airfoil of an aircraft, and one or more sensors configured to sense the response of one or more vanes of the vane array to aerodynamic forces and to transmit corresponding signals to an air data computer (ADC) for use by the ADC in calculating air data.
摘要翻译：一种用于向空中数据计算机提供计算空气数据的信息的空气动力感测装置。该装置包括可从飞行器的翼型件的远端延伸的叶片阵列中支撑的多个叶片，以及配置成感测叶片阵列的一个或多个翼片对于空气动力的响应的一个或多个传感器，并且传送相应的信号到空中数据计算机（ADC）供ADC用于计算空中数据。

6. 发明授权

US07988099B2 Winglet 有权
公开(公告)号：US07988099B2
公开(公告)日：2011-08-02
申请号：US10476257
申请日：2002-06-12
申请人： Robert M Bray
发明人： Robert M Bray
IPC分类号： B64C5/08
CPC分类号： B64C13/16 , B64C5/08 , B64C23/076 , Y02T50/164
摘要： A winglet for an aircraft wing is provided. The winglet has an airflow control arrangement, for example in the form of a trailing edge flap (20) by means of which lift generated by the winglet can be varied. The control arrangement desirably forms part of a manoeuvre load alleviation system (22) for the aircraft.
摘要翻译：提供飞机机翼的小翼。小翼具有气流控制装置，例如以后缘挡板（20）的形式，通过该后缘翼片可以改变由小翼产生的升力。控制装置理想地形成飞行器的机动负载减轻系统（22）的一部分。

7. 发明申请

US20110127383A1 ACTIVE WINGLET 审中-公开
标题翻译：活动WINGLET
公开(公告)号：US20110127383A1
公开(公告)日：2011-06-02
申请号：US12797742
申请日：2010-06-10
申请人： Nicholas R. Guida
发明人： Nicholas R. Guida
IPC分类号： B64C23/00
CPC分类号： B64C23/065 , B64C13/16 , B64C23/076 , Y02T50/164
摘要： An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing, and an angled portion that projects at an upward angle from the body portion. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and increase efficiency.
摘要翻译：活动小翼包括基本上平行于飞行器的机翼的主体部分，如同它是机翼的延伸部分，以及从身体部分以向上的角度突出的倾斜部分。主体部分可附接到飞行器机翼并且包括耦合到其上的可控气流改变装置。由于具有可控气流改变装置，小翼能够响应于飞行中的条件来调节可控气流改变装置的控制表面，以减少机翼载荷，增加范围并提高效率。

8. 发明授权

US07661629B2 Systems and methods for destabilizing an airfoil vortex 有权
标题翻译：使翼型涡流不稳定的系统和方法
公开(公告)号：US07661629B2
公开(公告)日：2010-02-16
申请号：US11370099
申请日：2006-03-07
申请人： Arvin Shmilovich , Yoram Yadlin , Roger W. Clark , Donald H. Leopold
发明人： Arvin Shmilovich , Yoram Yadlin , Roger W. Clark , Donald H. Leopold
IPC分类号： B64C23/00 , B64C21/04
CPC分类号： B64C23/076 , B64C23/065 , Y02T50/164
摘要： Apparatuses and methods for the controlled trailing wake flows. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device carried by the airfoil, with the vortex dissipation device including a fluid flow nozzle, a valve device, and a controller. The fluid flow nozzle can be coupleable to a source of pressurized fluid and can include an orifice positioned to direct a flow of fluid outwardly from the tip. The valve device can be coupled in fluid communication with the fluid flow nozzle to selectively control the flow passing through the orifice. The controller can be coupled to the valve device to direct the operation of the valve device. Accordingly, the vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated.
摘要翻译：用于受控拖尾尾流的装置和方法。根据一个实施例的装置涉及一种飞行器系统，其包括具有第一和第二相对面向的流动表面和尖端的翼型件。该系统还可以包括由翼型件携带的涡流消散装置，涡流消散装置包括流体流动喷嘴，阀装置和控制器。流体流动喷嘴可以耦合到加压流体源，并且可以包括定位成将流体流从尖端向外引导的孔。阀装置可以与流体流动喷嘴流体连通地联接，以选择性地控制通过孔口的流动。控制器可以联接到阀装置以引导阀装置的操作。因此，可以启动涡流消散装置以加速涡流（例如，翼尖涡流）在其产生之后消散的速率。

9. 发明授权

US07597289B2 Apparatus and method for the control of trailing wake flows 有权
标题翻译：用于控制尾流尾流的装置和方法
公开(公告)号：US07597289B2
公开(公告)日：2009-10-06
申请号：US11332835
申请日：2006-01-13
申请人： Arvin Shmilovich , Yoram Yadlin , Roger Clark , Donald Leopold
发明人： Arvin Shmilovich , Yoram Yadlin , Roger Clark , Donald Leopold
IPC分类号： B64C23/00
CPC分类号： B64C23/076 , B64C23/065 , Y02T50/164
摘要： A system and method for dissipating vortices that form at the wingtips on aircraft and from other airfoils. A jet air stream is discharged in a location at or proximate to the outer end portion of the airfoil into the vortex flow, and the jet air stream is moved cyclically back and forth. The cyclic movement can be at lower or higher frequencies to alleviate at least in part intensity of the vortex or accelerate instability of the vortex which leads to vortex dissipation.
摘要翻译：一种用于消散在飞机和其他翼型上的翼尖处形成的涡流的系统和方法。喷气空气流在翼型的外端部分处或附近的位置被排放到涡流中，并且喷气流被循环地前后移动。循环运动可以在较低或更高的频率以减轻涡流的至少部分强度或加速导致涡流耗散的涡流的不稳定性。

10. 发明申请

US20080042013A1 ACTIVE SYSTEMS AND METHODS FOR CONTROLLING AN AIRFOIL VORTEX 有权
标题翻译：用于控制航空VORTEX的主动系统和方法
公开(公告)号：US20080042013A1
公开(公告)日：2008-02-21
申请号：US11747112
申请日：2007-05-10
申请人： Arvin Shmilovich , Yoram Yadlin , Roger Clark
发明人： Arvin Shmilovich , Yoram Yadlin , Roger Clark
IPC分类号： B64C23/06
CPC分类号： B64C23/076 , B64C23/065 , Y02T50/164
摘要： Active systems and methods for controlling aircraft vortices are disclosed. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device carried by the airfoil, with the vortex dissipation device including an orifice positioned to direct a flow of fluid outwardly from the tip, an actuator operatively coupled to the fluid flow orifice and positioned to change a manner in which flow is directed outwardly from the tip, and a controller operatively coupled to the actuator to direct the operation of the actuator. The vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated, for example, by alternately pulsing flow inwardly and outwardly through the fluid flow orifice.
摘要翻译：公开了用于控制飞行器旋涡的主动系统和方法。根据一个实施例的装置涉及一种飞行器系统，其包括具有第一和第二相对面向的流动表面和尖端的翼型件。该系统还可以包括由翼型件承载的涡流耗散装置，其中涡流消散装置包括定位成将流体流从尖端向外引导的孔口，致动器可操作地联接到流体流动孔口并且定位成改变该流动从尖端向外指向，并且控制器可操作地联接到致动器以引导致动器的操作。涡流消散装置可以被激活以加速涡流（例如，翼尖涡流）在其产生之后消散的速率，例如通过交替地脉冲流动通过流体流动孔口向内和向外流动。

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