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1. 发明申请

US20170274976A1 COMPLIANT STRUCTURE DESIGN FOR VARYING SURFACE CONTOURS 审中-公开
公开(公告)号：US20170274976A1
公开(公告)日：2017-09-28
申请号：US15621117
申请日：2017-06-13
申请人： FLEXSYS, INCL
发明人： Joel A. Hetrick , Sridhar Kota , Gregory F. Ervin
IPC分类号： B64C3/52 , B64C27/72 , B64C3/48 , B64C3/50 , B64C27/473 , B64C9/16 , B64C9/22
CPC分类号： B64C3/52 , B64C3/48 , B64C3/50 , B64C9/16 , B64C9/22 , B64C27/473 , B64C27/615 , B64C27/72 , B64C2003/445 , B64C2027/7222 , B64C2027/7266 , B64C2027/7294 , Y02T50/34 , Y10T74/18056 , Y10T74/18288
摘要： An edge morphing arrangement for an airfoil having upper and lower control surfaces is provided with an elongated edge portion that overlies the edge of the airfoil, the edge portion having a surface element having first and second edges that communicate with, and form extensions of, respective ones of the upper and lower control surfaces of the elongated airfoil. The surface elements are formed of deformable compliant material that extends cross-sectionally from the first surface element edge to an apex of the edge portion, and to the second surface element edge. There is additionally provided a driving link having first and second driving link ends, the first driving link end being coupled to the interior of one of the first and second rib portions. The second end is arranged to receive a morphing force, and the rib element is deformed in response to the morphing force.

2. 发明授权

US09440737B1 Apparatus to adjust airfoils of rotor blades 有权
标题翻译：调整转子叶片翼型的装置
公开(公告)号：US09440737B1
公开(公告)日：2016-09-13
申请号：US13469790
申请日：2012-05-11
申请人： Matthew H. Cawthorne , Robert P. Narducci , Perry Ray Ziegenbein
发明人： Matthew H. Cawthorne , Robert P. Narducci , Perry Ray Ziegenbein
IPC分类号： B64C27/467 , B64C27/615 , F03D7/02
CPC分类号： B64C27/467 , B64C27/615 , F03D1/0675 , F03D7/0232 , F05B2230/80 , Y02E10/721 , Y02P70/523 , Y02T50/166 , Y02T50/34
摘要： Apparatus to adjust airfoils of rotor blades are disclosed. An example apparatus includes a first surface to be attached to a trailing edge of a rotor blade; a forward edge having a first thickness; an aft edge having a second thickness; and a middle portion between the forward edge and the aft edge having a third thickness greater than the first and second thicknesses.
摘要翻译：公开了一种调整转子叶片翼型的装置。示例性设备包括要附接到转子叶片的后缘的第一表面; 具有第一厚度的前边缘; 具有第二厚度的后边缘; 前缘和后缘之间的中间部分具有大于第一和第二厚度的第三厚度。

3. 发明授权

US09278756B2 Dry lubricated linear actuator for in blade rotor control 有权
标题翻译：干式润滑线性执行器用于叶片转子控制
公开(公告)号：US09278756B2
公开(公告)日：2016-03-08
申请号：US13599843
申请日：2012-08-30
申请人： Paul R. Brewer , Reg R. Raval , Suat Bekircan
发明人： Paul R. Brewer , Reg R. Raval , Suat Bekircan
IPC分类号： B64C27/615 , B64C27/72 , B64C27/00 , F16H25/24
CPC分类号： B64C27/615 , B64C27/00 , B64C27/72 , B64C2027/7272 , F16H2025/249 , Y02T50/34
摘要： A rotor blade assembly includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator located inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant. A rotary-winged aircraft includes an airframe and a main rotor assembly operably connected to the airframe. The main rotor assembly includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis. At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator positioned inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant.
摘要翻译：转子叶片组件包括转子叶片和沿着转子叶片的跨度定位的可旋转翼片部分。位于转子叶片内部的线性致动器可操作地连接到翼片部分，以使翼片部分围绕翼片轴线旋转，并且不存在油，油脂或其它流体润滑剂。旋转飞机包括机身和可操作地连接到机身的主转子组件。主转子组件包括可围绕转子组件轴线旋转的多个转子叶片组件。多个转子叶片组件中的至少一个转子叶片组件包括转子叶片和沿着转子叶片的跨度定位的可旋转翼片部分。定位在转子叶片内部的线性致动器可操作地连接到翼片部分，以使翼片部分围绕翼片轴线旋转，并且不存在油，油脂或其它流体润滑剂。

4. 发明授权

US09205919B1 Apparatus and method for roll moment equalization at high advance ratios for rotary wing aircraft 有权
标题翻译：用于旋转翼飞机的高提前比例的滚动力矩均衡装置和方法
公开(公告)号：US09205919B1
公开(公告)日：2015-12-08
申请号：US13999366
申请日：2014-02-13
申请人： Groen Brothers Aviation, Inc.
发明人： Walter Gerd Oskar Sonneborn
IPC分类号： B64C27/57 , B64C27/26 , B64C27/615 , B64C27/54 , B64C27/02 , B64C27/18 , B64C27/72
CPC分类号： B64C27/615 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/30 , B64C27/57 , B64C27/58 , B64C2027/7261
摘要： A method for equalizing rolling moments at high advance ratios is disclosed including impelling an aircraft in a forward direction at an airspeed by means of a thrust source and rotating a rotor of the aircraft at an angular velocity with respect to the airspeed effective to cause a positive total lift on each blade due to air flow over the blades in the retreating direction when the blade is moving in the retreating direction. The rotor includes an even number of blades placed at equal angular intervals around the rotor hub. One or both of cyclic pitch and rotor angle of attack are adjusted such that a rolling moment of the retreating blade due to reverse air flow is between 0.3 and 0.7 times a rolling moment on the advancing blade due to lift.
摘要翻译：公开了一种用于以高提前比率均衡滚动力矩的方法，包括通过推力源在空速下向前推动飞行器，并以相对于空速的角速度旋转飞机的转子，以有效地引起正向当叶片沿退回方向移动时，由于叶片在退回方向上的空气流过，在每个叶片上的总升力。转子包括在转子毂周围以相等的角度间隔放置的偶数个叶片。调节循环桨距和转子迎角的一个或两个，使得由于反向气流而导致的后退叶片的滚动力矩由于提升而在前进叶片上的滚动力矩的0.3至0.7倍之间。

5. 发明授权

US09180966B2 Actuation system for an active element in a rotor blade 有权
标题翻译：用于转子叶片中有源元件的驱动系统
公开(公告)号：US09180966B2
公开(公告)日：2015-11-10
申请号：US13596110
申请日：2012-08-28
申请人： Troy C. Schank , Peter H. Kintzinger , Jonathan A. Knoll , Christopher E. Foskey
发明人： Troy C. Schank , Peter H. Kintzinger , Jonathan A. Knoll , Christopher E. Foskey
IPC分类号： B64C27/615 , B64C27/72
CPC分类号： B64C27/615 , B64C2027/7266 , Y02T50/34
摘要： In accordance with one embodiment of the present application, an actuation system is configured for actuation of an airfoil member with a flap mechanism. The actuation system can include an upper drive tape and a lower drive tape, each partially wrapped around a first bearing and second bearing. An inboard frame can be actuated by at least one linear actuator. Similarly, an outboard frame can be actuated by at least one linear actuator. The inboard frame is coupled to the upper drive tape, while the outboard frame is coupled to the lower drive tape. An actuation of the inboard frame and outboard frame in a reciprocal manner acts move a flap input lever reciprocally upward and downward. A flap mechanism is configured to convert the movement of the flap input lever into rotational movements of the airfoil member.
摘要翻译：根据本申请的一个实施例，致动系统构造成用翼片机构致动翼型件。致动系统可以包括上部驱动带和下部驱动带，每个部分围绕第一轴承和第二轴承部分地缠绕。内部框架可以由至少一个线性致动器致动。类似地，外部框架可以由至少一个线性致动器致动。内侧框架联接到上驱动带，而外侧框架联接到下驱动带。内侧框架和外侧框架以互补方式的致动使得翼片输入杆往复地向上和向下移动。翼片机构构造成将翼片输入杆的运动转换成翼型件的旋转运动。

6. 发明授权

US09022313B2 Rotor unloading apparatus and method 有权
标题翻译：转子卸载装置及方法
公开(公告)号：US09022313B2
公开(公告)日：2015-05-05
申请号：US13335541
申请日：2011-12-22
申请人： David Gerd Oskar Sonneborn
发明人： David Gerd Oskar Sonneborn
IPC分类号： B64C27/02 , B64C27/18 , B64C27/26 , B64C27/30
CPC分类号： B64C27/615 , B64C27/025 , B64C27/18 , B64C27/26 , B64C27/30 , B64C27/57 , B64C27/58 , B64C2027/7261
摘要： A method and apparatus for enabling high speed flight in a rotorcraft are disclosed. The method may include executing a flight with a rotorcraft. The flight may include a first portion and second portion ordered sequentially. During the first portion, the rotorcraft may be flown with the rotor exclusively in autorotation. Once sufficient airspeed is obtained, the flight may transition to the second portion. Wherein, substantially all of the weight of the rotorcraft may be supported by one or more fixed wing surfaces of the rotorcraft. Thus, during the second portion, the rotor may be completely unloaded. To keep the rotor stable by turning, the rotor may be powered during the second portion by an engine of the rotorcraft by way of a prerotation system.
摘要翻译：公开了一种用于在旋翼航空器中实现高速飞行的方法和装置。该方法可以包括执行具有旋翼航空器的飞行。飞行可以包括顺序排列的第一部分和第二部分。在第一部分期间，旋翼航空器可以独自在自转中与转子一起飞行。一旦获得足够的空速，飞行可以转变到第二部分。其中，旋翼航空器的基本上所有的重量可以由旋翼航空器的一个或多个固定翼面支撑。因此，在第二部分期间，转子可以完全卸载。为了通过转动来保持转子稳定，转子可以在第二部分期间由旋转飞机的发动机通过预旋转系统供电。

7. 发明申请

US20150037149A1 ROTORCRAFT CONTROL SYSTEM FOR ROTORCRAFT WITH TWO OR MORE ROTOR SYSTEMS 审中-公开
标题翻译：用于具有两个或更多转子系统的转子的转子控制系统
公开(公告)号：US20150037149A1
公开(公告)日：2015-02-05
申请号：US13956783
申请日：2013-08-01
申请人： Alfred Alan Gates , Fu-Shang John Wei
发明人： Alfred Alan Gates , Fu-Shang John Wei
IPC分类号： B64C27/615
CPC分类号： B64C27/615 , B64C27/08 , B64C27/20 , Y02T50/34
摘要： A multirotor rotorcraft control system for effectuating flight control. The multirotor rotorcraft has at least two or more rotor assemblies. The control system preferably includes at least one flap for each rotor blade and at least one actuator for each rotor assembly. The rotor assemblies and the flap(s) and actuator(s) for each assembly are used for flight control. This invention does not require a complex fixed pitch control system or a high frequency servo control system. This invention can control blade angle of attack during autorotation.
摘要翻译：用于实现飞行控制的多旋翼飞行器控制系统。多转子旋翼飞机具有至少两个或更多个转子组件。控制系统优选地包括用于每个转子叶片的至少一个翼片和用于每个转子组件的至少一个致动器。转子组件和每个组件的挡板和执行器用于飞行控制。本发明不需要复杂的固定桨距控制系统或高频伺服控制系统。本发明可以控制自动旋转时的叶片迎角。

8. 发明授权

US08475127B2 Method and device for controlling a rotary wing aircraft 有权
标题翻译：用于控制旋翼飞机的方法和装置
公开(公告)号：US08475127B2
公开(公告)日：2013-07-02
申请号：US12685012
申请日：2010-01-11
申请人： Peter Jänker , Valentin Klöppel
发明人： Peter Jänker , Valentin Klöppel
IPC分类号： B64C27/615
CPC分类号： B64C27/615 , B64C2027/7266 , Y02T50/34
摘要： The invention relates to a method for controlling a rotary wing aircraft with at least one main rotor, comprising a rotor head and rotor blades (12), arranged such that each rotor blade (12) is supported to be able to pivot or twist around the lengthwise axis of its blade on the rotor head and has at least one control flap (14) that can be deflected. According to the invention, the rotary wing aircraft is controlled solely by changing the respective blade pitch angle (X) by means of changing the flap control angle (Y) of the assigned control flaps (14) by the resulting blade pitch angle (X3) being set by applying the resulting flap angle (Y4) to the control flap (14), and the flap angle (Y4) being computed using an algorithm, the input quantities comprising the flap control angle (Y1) depending on the pilot primary control and the flap correction angle (Y2) depending on the secondary control.
摘要翻译：本发明涉及一种用于控制具有至少一个主转子的旋翼机飞行器的方法，所述主转子包括转子头和转子叶片（12），其被布置成使得每个转子叶片（12）被支撑以能够围绕其叶片在转子头上的纵向轴线并具有至少一个能够被偏转的控制翼片（14）。根据本发明，通过利用所得到的叶片间距角（X3）改变分配的控制翼片（14）的翼片控制角（Y），仅通过改变相应叶片俯仰角（X）来控制旋翼飞机，通过将所得到的翼片角度（Y4）施加到控制翼片（14），并且使用算法计算的翼片角度（Y4）来设定，所述输入量包括取决于飞行员初级控制的翼片控制角度（Y1）皮瓣矫正角（Y2）取决于二次控制。

9. 发明申请

US20120305698A1 Method and Apparatus for Actively Manipulating Aerodynamic Surfaces 有权
标题翻译：积极操纵气动表面的方法和装置
公开(公告)号：US20120305698A1
公开(公告)日：2012-12-06
申请号：US13577633
申请日：2010-11-04
申请人： Troy C. Schank , Peter H. Kitzinger , Paul B. Sherrill , Thomas C. Parham , David A. Popelka
发明人： Troy C. Schank , Peter H. Kitzinger , Paul B. Sherrill , Thomas C. Parham , David A. Popelka
IPC分类号： B64C27/615 , B64C13/30
CPC分类号： B64C27/615 , B64C27/001 , B64C2027/7266 , B64C2027/7272 , Y02T50/34
摘要： A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a cross-axis flexure pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements.
摘要翻译：提供了一种方法和装置，包括可以连接到翼架以用于控制有源元件的致动器系统。致动器系统可以包括可沿着平行于机翼的跨度轴线的轴线移动的滑动元件。滑动元件可以连接到固定元件和曲柄元件，曲柄元件通常包括梁元件和横轴挠曲枢轴元件。梁元件可以从枢转元件偏移，使得曲柄元件可以在倾向于将滑动元件拉离固定元件的外力作用下具有负刚度的情况下围绕枢转元件旋转。

10. 发明申请

US20120261508A1 ACTIVE GURNEY FLAP 有权
标题翻译：活动GURNEY FLAP
公开(公告)号：US20120261508A1
公开(公告)日：2012-10-18
申请号：US13449617
申请日：2012-04-18
申请人： Paul R. Brewer , Steven Shorcott , Reg R. Raval
发明人： Paul R. Brewer , Steven Shorcott , Reg R. Raval
IPC分类号： B64C27/57 , B64C13/24 , B64C3/50
CPC分类号： B64C3/58 , B64C27/615 , B64C2003/145 , B64C2027/7266 , Y02T50/12 , Y02T50/34
摘要： According to an embodiment disclosed herein, a gurney flap assembly includes an actuator, and a flexible body attaching to the actuator, the body having a downwardly depending flap for moving into and out of an airstream in a pressure side of a wing, wherein the flexible body flexes in reaction to motion of the actuator. This increases the lift force of the rotor blade, wing or aerofoil blade.
摘要翻译：根据本文公开的实施例，一种摇床组件包括致动器和连接到致动器的柔性主体，该主体具有向下悬挂的翼片，用于移入和移出机翼的压力侧中的气流，其中柔性身体反应于致动器的运动而弯曲。这增加了转子叶片，机翼或机翼叶片的升力。

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