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    Flight control system for an aircraft
    42.
    发明授权
    Flight control system for an aircraft 有权

    公开(公告)号：US11745852B2

    公开(公告)日：2023-09-05

    申请号：US18071469

    申请日：2022-11-29

    Applicant: EnExSys Research Inc.

    Inventor： James Henke

    IPC: B64C9/04 ,  B64C9/06 ,  B64C9/18 ,  B64C27/06 ,  B64C27/82 ,  B64C3/54 ,  B64C1/26 ,  B64C3/18

    CPC classification number: B64C3/546 ,  B64C1/26 ,  B64C3/185 ,  B64C9/04 ,  B64C9/06 ,  B64C9/18 ,  B64C27/06 ,  B64C27/82 ,  B64C2027/8272

    Abstract: A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.

    Variable camber adaptive compliant wing system
    43.
    发明授权
    Variable camber adaptive compliant wing system 有权

    公开(公告)号：US09896188B1

    公开(公告)日：2018-02-20

    申请号：US14559977

    申请日：2014-12-04

    Applicant: The United States of America, as represented by the Secretary of the Air Force

    Inventor： James J Joo

    IPC: B64C3/48 ,  B64C3/18 ,  B64C3/26 ,  B64C9/06

    CPC classification number: B64C3/48 ,  B64C3/185 ,  B64C3/187 ,  B64C3/26 ,  B64C9/06

    Abstract: A fixed compliant wing system is provided that is coupled to a rigid spar and a rigid stopper. The fixed compliant wing system includes an actuator and at least two compliant rib structures coupled to the rigid spar. The compliant rib structures include an outer compliant contoured structure, a drive member coupled to the outer compliant contoured structure and including a guiding slot consisting of at least two interconnected portions. The guiding slot encompasses and is in a sliding arrangement with the rigid stopper. The drive member is further connected to the actuator. Portions of the outer compliant contoured structures are configured to independently deform when force is applied from the actuator to the drive member thereby moving the rigid stopper from a first portion to a second portion of the guiding slot. The fixed complaint wing system further includes a skin encompassing the compliant rib structures.

    Variable camber flap system and method
    45.
    发明授权
    Variable camber flap system and method 有权
    可变外倾瓣系统及方法

    公开(公告)号：US09193440B2

    公开(公告)日：2015-11-24

    申请号：US14034940

    申请日：2013-09-24

    Applicant: The Boeing Company

    Inventor： Matthew A. Moser ,  Michael R. Finn ,  Mark J. Gardner ,  Mark S. Good ,  Sarah A. Jones

    IPC: B64C3/50 ,  B64C13/34 ,  B64C9/14 ,  B64C13/26

    CPC classification number: B64C13/34 ,  B64C3/50 ,  B64C9/06 ,  B64C9/12 ,  B64C9/14 ,  B64C13/26 ,  Y02T50/32

    Abstract: A variable camber system for an aircraft may include a variable camber trim unit (VCTU) positioned between an inboard device and an outboard device. The inboard device and the outboard device may be mounted to at least one of a leading edge and a trailing edge of a wing. The VCTU may include a speed sum gearbox having an inboard shaft coupled to the inboard device and an outboard shaft coupled to the outboard device. The VCTU may additionally include a VCTU electric motor engaged to the speed sum gearbox. The VCTU electric motor may be selectively operable in conjunction with the speed sum gearbox to rotate the outboard shaft independent of the inboard shaft in a manner causing the outboard device to be actuated independent of the inboard device.

    Abstract translation: 用于飞行器的可变外倾角系统可以包括位于内侧装置和外侧装置之间的可变外倾角装置单元（VCTU）。 内侧装置和外侧装置可以安装到机翼的前缘和后缘中的至少一个。 VCTU可以包括速度和齿轮箱，其具有联接到内侧装置的内侧轴和联接到外侧装置的外侧轴。 VCTU可以另外包括接合到速度和齿轮箱的VCTU电动机。 VCTU电动机可以选择性地与速度总和齿轮箱一起操作，以独立于内侧轴旋转外侧轴，使得外部装置独立于内侧装置被致动。

    Aircraft spiralling mechanism - c
    47.
    发明申请
    Aircraft spiralling mechanism - c 有权
    飞机螺旋机构 - c

    公开(公告)号：US20050116085A1

    公开(公告)日：2005-06-02

    申请号：US10762267

    申请日：2004-01-23

    Applicant: Tom Kusic

    Inventor： Tom Kusic

    IPC: B64C5/04 ,  B64C9/02 ,  B64C39/12 ,  F42B10/00 ,  F41A9/61

    CPC classification number: B64C5/04 ,  B64C9/02 ,  B64C9/06 ,  B64C39/12

    Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiralling motion without the aircraft rolling. Two fins 6 and 17 are attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The fins 6, 17 are able to rotate in a pivoting manner on the rotatable tube 3a with respect to the rotatable tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 3a. Rotation of the rotatable tube is achieved by using an electric motor 3b turning a wheel 3c. The wheel 3c makes contact with the rotatable tube. When pitched at an angle to the longitudinal axis in unison, both fins 6, 17 would exert a lateral force on the rotatable tube 3a. But as the rotatable tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiralling motion of the aircraft when in flight. The rotation of one fin causes the rotation of another fin.

    Abstract translation: 具有螺旋诱导组件2的飞机1，其能够使飞机以不间断的旋转运动而飞行，而不会飞行。 两个翅片6和17连接到能够围绕机身的环绕部分旋转的管3a。 翅片6,17能够相对于可旋转管3a以可枢转的方式旋转在可旋转管3a上，从而相对于可旋转管3a的纵向轴线改变它们的俯仰。 通过使用转动车轮3c的电动机3b来实现可旋转管的旋转。 轮3c与可旋转管接触。 当与纵向轴线成一定角度倾斜时，两个翼片6,17将在可旋转管3a上施加横向力。 但是当可旋转管被侧向推动时，其旋转，因此推动的横向方向恒定地旋转，导致飞行器在飞行中的螺旋运动。 一个翅片的旋转导致另一个翅片的旋转。

    Spiralling missile—A
    48.
    发明授权
    Spiralling missile—A 失效
    螺旋导弹-A

    公开(公告)号：US06644587B2

    公开(公告)日：2003-11-11

    申请号：US10067963

    申请日：2002-02-08

    Applicant: Tom Kusic

    Inventor： Tom Kusic

    IPC: F42B1000

    CPC classification number: B64C9/06 ,  B64C5/04

    Abstract: A missile 1 with a missile attachment 2 according to this invention. The missile attachment 2 consists of a tube 3 with a protruding section 4. The protruding section 4 has a concave forward facing surface area 5. The concave curvature is such that it is noticeable when the protruding section 4 is at the highest position on the tube 3. The tube is in the form of a cylindrical tube and is fitted to the missile 1 so that it encircles part of the missile and such that it can rotate continuously relative to the missile 1 during flight of the missile.

    Abstract translation: 具有根据本发明的导弹附件2的导弹1。 导弹附件2由具有突出部分4的管3组成。突出部分4具有凹入的前向表面区域5.凹曲面使得当突出部分4处于管子上的最高位置时是显着的 3.管是圆柱形管的形式，并装配在导弹1上，以便它围绕导弹的一部分，并使其能够在导弹飞行期间相对于导弹1连续旋转。

    Spiralling missile - B
    49.
    发明申请
    Spiralling missile - B 失效
    螺旋导弹 - B

    公开(公告)号：US20020109040A1

    公开(公告)日：2002-08-15

    申请号：US10067964

    申请日：2002-02-08

    Inventor： Tom Kusic

    IPC: F42B010/06 ,  F42B010/00

    CPC classification number: B64C9/06 ,  B64C5/04

    Abstract: A cross-section of a missile 1 with the missile attachment 2. The missile attachment consists of a cylindrical tube 3 which encircles part of the missile 1, and a protruding section 4 with a concave forward facing surface area 5. Shown also is a friction inducing moveable component in the form of a lever 11 pivotly attached to the missile by a bracket 12, such that the lever 11 can be pivotly moved an actuating mechanism which is in the form of an electric motor 13 using a rotor arm 14. When the lever is pivoted by the electric motor 13, using the rotor arm 14, a part of the lever is pressed through a hole 15 in the missile 1 so that the part of the lever that is pressed through the hole can reach the cylindrical tube. As the rotor arm 14 presses harder against the lever, the lever is pressed harder against the cylindrical tube. With the friction that occurs between the lever and the cylindrical tube, the rotation of the cylindrical tube relative to the missile can be controlled, so that the spiralling motion of the missile can be controlled. A computer 16 controls the action of the electric motor 13, and a battery 17 provides electrical power for the computer and the electrical motor.

    Abstract translation: 具有导弹附件2的导弹1的横截面。导弹附件包括环绕导弹1的一部分的圆柱形管3和具有凹入的前向表面区域5的突出部分4.还示出了摩擦 引导杠杆11的形式的可移动部件，其通过支架12枢转地附接到导弹，使得杠杆11可以使用转子臂14以电动马达13形式的致动机构枢转运动。当 杠杆由电动马达13枢转，使用转子臂14，杆的一部分通过导弹1中的孔15被按压，使得通过孔按压的杆的部分可以到达圆柱形管。 当转子臂14更加压靠杠杆时，杆被更加压紧在圆柱形管上。 由于杠杆和圆柱形管之间发生摩擦，可以控制圆柱形管相对于导弹的旋转，从而可以控制导弹的螺旋运动。 计算机16控制电动机13的作用，并且电池17为计算机和电动机提供电力。

    Aileron segment control for a flaperon system
    50.
    发明授权
    Aileron segment control for a flaperon system 失效
    襟副翼系统的副翼段控制

    公开(公告)号：US4180222A

    公开(公告)日：1979-12-25

    申请号：US754823

    申请日：1976-12-27

    Applicant: Francis L. Thornburg

    Inventor： Francis L. Thornburg

    IPC: B64C9/06 ,  B64C9/12

    CPC classification number: B64C9/06 ,  B64C9/12 ,  Y02T50/44 ,  Y10T74/18056 ,  Y10T74/18888

    Abstract: An improved control system for the aileron segment of a combined flap and aileron (flaperon) wherein the flaperon, supported, extended and retracted by conventional means, is described. It consists of a splined shaft rotatably mounted on an aircraft wing, its longitudinal axis being substantially aligned with the extension and retraction path of the flap. A transfer gear box slidably engages the splined shaft and is supported by a roller assembly engaging a support track which is mounted in the wing and runs substantially parallel to the splined shaft. The transfer gear box incorporates gears to transfer rotation of the splined shaft, via a second angularly adjustable shaft, to an aileron segment rotation mechanism located on the flaperon at the axis of rotation of the aileron segment. Rotation of the aileron segment is accomplished by rotating the splined shaft, regardless of the location or movement of the flap; this by virtue of the fact that the transfer gear box slides along the splined shaft, maintaining at all times a fixed distance between itself and the aileron segment rotation mechanism. A torque multiplier increases that torque when transmitted through small light-weight components, to the magnitude required for aileron actuation.

    Abstract translation: 描述了一种用于组合的翼片和副翼（襟副翼）的副翼段的改进的控制系统，其中通过常规装置支撑，延伸和缩回的襟副翼。 它包括可旋转地安装在飞机机翼上的花键轴，其纵向轴线基本上与翼片的延伸和缩回路径对齐。 传动齿轮箱可滑动地接合花键轴，并且由与安装在机翼中并基本上平行于花键轴延伸的支撑轨道的滚子组件支撑。 传动齿轮箱包括齿轮，用于将花键轴的旋转经由第二可角度调节的轴传递到位于襟副翼上的副翼段旋转机构，该翼片在副翼段的旋转轴线处。 不管翼片的位置或运动如何，通过旋转花键轴实现副翼段的旋转; 这是由于传动齿轮箱沿着花键轴滑动的事实，其始终保持在其与副翼段旋转机构之间的固定距离。 转矩乘数在通过小型重量轻的部件传递时增加扭矩，达到副翼驱动所需的大小。

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