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    Variable camber flap system and method
    2.
    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 with vertical stabilizers arranged on a central fuselage body and method, as well as control unit, for compensating a negative pitching moment
    5.
    发明授权
    Aircraft with vertical stabilizers arranged on a central fuselage body and method, as well as control unit, for compensating a negative pitching moment 有权
    具有垂直稳定器的飞行器布置在中央机身和方法以及控制单元上，用于补偿负俯仰时刻

    公开(公告)号：US08496203B2

    公开(公告)日：2013-07-30

    申请号：US12913463

    申请日：2010-10-27

    Applicant: Malte Schwarze ,  Andreas Westenberger

    Inventor： Malte Schwarze ,  Andreas Westenberger

    IPC: B64C9/00

    CPC classification number: B64C9/12 ,  B64C9/16 ,  B64C2039/105 ,  Y02T50/12 ,  Y02T50/32

    Abstract: An aircraft includes, but is not limited to a central fuselage body without horizontal stabilizer, at least one high-lift control surface, at least one vertical stabilizer that is arranged on the central fuselage body and at least one extendable compensation control surface. The compensation control surface may be moved independently of the high-lift control surface of the aircraft and generates a positive tail-heavy pitching moment when it is moved into the flow against the aircraft. Due to this measure, a negative pitching moment during the actuation of high-lift control surfaces may be at least partially eliminated without influencing the high lift. Rudder segments that may be moved opposite to one another on two vertical stabilizers that are arranged mirror-symmetrical referred to the longitudinal axis of the aircraft preferably are used for this purpose.

    Abstract translation: 飞机包括但不限于没有水平稳定器的中央机身，至少一个高升程控制表面，设置在中央机身主体上的至少一个垂直稳定器和至少一个可延伸的补偿控制表面。 补偿控制表面可以独立于飞行器的高升程控制表面移动，并且当其移动到针对飞行器的流中时，产生正尾尾重的俯仰力矩。 由于这种措施，高升力控制表面致动期间的负倾斜力矩可以至少部分消除，而不会影响高升程。 优选地，为了这个目的，使用可以相对于飞行器的纵向轴线反射对称排列的两个垂直稳定器彼此相对移动的方向舵段。

    Method for improving roll steering of an aircraft and aircraft using same
    6.
    发明授权
    Method for improving roll steering of an aircraft and aircraft using same 有权
    使用相同方式改进飞机和飞机的侧倾转向的方法

    公开(公告)号：US07896288B2

    公开(公告)日：2011-03-01

    申请号：US11720818

    申请日：2005-12-05

    Applicant: Frederic Sauvinet

    Inventor： Frederic Sauvinet

    IPC: B64C5/02

    CPC classification number: B64C9/12

    Abstract: A roll steering method subdivides the direction of an aircraft control surface into two elements and, during a roll control operation using ailerons, steers an upper element of the control surface in the roll direction and a lower element in the opposite direction.

    Abstract translation: 滚动转向方法将飞行器控制面的方向分为两个部件，并且在使用副翼的滚动控制操作期间，沿着滚动方向转向控制表面的上部元件，并在相反方向上引导下部元件。

    Method and device for reducing the wake vortices of an aircraft in the approach/landing phase
    7.
    发明授权
    Method and device for reducing the wake vortices of an aircraft in the approach/landing phase 有权
    在接近/着陆阶段减少飞机尾流涡流的方法和装置

    公开(公告)号：US07850125B2

    公开(公告)日：2010-12-14

    申请号：US11737438

    申请日：2007-04-19

    Applicant: Franck Delaplace

    Inventor： Franck Delaplace

    IPC: G05D1/00

    CPC classification number: B64C9/12 ,  B64C23/06 ,  Y02T50/162

    Abstract: The invention relates to a method and device for reducing the wake vortices of an aircraft during the approach/landing phase. Spoilers are automatically ordered to deploy when lift-augmenting aerodynamic surfaces are ordered to deploy, and are automatically ordered to retract when at least one of the following three conditions holds: the angle of incidence α of the aircraft is equal to or greater than an incidence threshold αs; the speed Vc of the aircraft is equal to or less than a speed threshold Vs; and the aircraft is instigating a go-around maneuver.

    Abstract translation: 本发明涉及一种在接近/着陆阶段减少飞机尾流涡流的方法和装置。 当升降增压气动表面被命令部署时，自动命令铲斗，以便在以下三个条件中的至少一个条件成立时被自动命令缩回：飞行器的入射角α等于或大于入射角 阈值αs; 飞行器的速度Vc等于或小于速度阈值Vs; 飞机正在引发复飞机动。

    Dynamic Adjustment of Wing Surfaces for Variable Camber
    8.
    发明申请
    Dynamic Adjustment of Wing Surfaces for Variable Camber 有权
    可变弯曲翼面的动态调整

    公开(公告)号：US20080255713A1

    公开(公告)日：2008-10-16

    申请号：US11734842

    申请日：2007-04-13

    Applicant: Dan Onu ,  John D. Winter ,  Candy L. Carr ,  Paul M. Vijgen ,  Gary A. Emch ,  Michael E. Renzelmann

    Inventor： Dan Onu ,  John D. Winter ,  Candy L. Carr ,  Paul M. Vijgen ,  Gary A. Emch ,  Michael E. Renzelmann

    IPC: G05D1/00 ,  B64C13/00

    CPC classification number: B64C9/12 ,  Y02T50/32 ,  Y02T50/44

    Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

    Abstract translation: 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用改变飞行器条件的输入，如高度，马赫数，重量，重心，垂直速度和飞行阶段。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。

    Aircraft with topside only spoilers
    9.
    发明授权
    Aircraft with topside only spoilers 有权
    飞机只有顶部只有扰流板

    公开(公告)号：US07108230B2

    公开(公告)日：2006-09-19

    申请号：US10456176

    申请日：2003-06-06

    Applicant: Walter D. Clark

    Inventor： Walter D. Clark

    IPC: B64C3/58

    CPC classification number: B64C1/0009 ,  B64C5/08 ,  B64C9/12 ,  B64C9/32 ,  B64C9/323 ,  B64C9/34 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/22 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

    Abstract: An aircraft with swept back wings and spoilers inlaid into the top surface near the tips of the wings. The aircraft also includes an elevator formed in the center back portion of the aircraft, which is also aft of the spoilers. It is aft to allow an auxiliary control in the elevator signal to cancel the unwanted pitch up moment caused by the spoilers only going up and being aft of the center of gravity of the aircraft. Roll is achieved with these spoilers by the direct action of the lift dumping on one side or the other and by taking advantage of the transformation of yaw into roll by the sweep back of the wings.

    Abstract translation: 一架飞机将翅膀和扰流板扫到靠近机翼尖端的顶面。 飞机还包括形成在飞行器的中心后部的电梯，其也是扰流板的后部。 这是为了允许电梯信号中的辅助控制来消除由扰流板仅上升并且处于飞机重心的后方引起的不期望的俯仰上升时刻。 通过电梯倾倒在一侧或另一侧上的直接作用，并且通过翼的扫掠利用偏转转动的优点，利用这些扰流板实现滚动。

    Control system for an aircraft
    10.
    发明申请
    Control system for an aircraft 审中-公开
    飞机控制系统

    公开(公告)号：US20060108472A1

    公开(公告)日：2006-05-25

    申请号：US10993497

    申请日：2004-11-19

    Applicant: Walter Clark

    Inventor： Walter Clark

    IPC: B64C9/00

    CPC classification number: B64C3/16 ,  B64C5/02 ,  B64C9/12

    Abstract: The invention is a system for controlling an aircraft, the aircraft having a longitudinal axis, vertical and horizontal axis and right and left wings and right and left ailerons mounted on the right and left wings. In detail, the system includes a right stabilizer mounted to the right wing, the right stabilizer canted from the right wing such that the outer end thereof is down and deflectable about an axis of rotation parallel to the span axis of the stabilizer. A left stabilizer is mounted to the left wing, the left stabilizer canted from the left wing such that the outer end thereof is down and deflectable about an axis of rotation parallel to the span axis of the stabilizer. A control system is provided to simultaneously deflect the right aileron and stabilizer downward and the left aileron and stabilizer upward to turn left and to deflect the right aileron and stabilizer upward and the left aileron and stabilizer downward to turn right.

    Abstract translation: 本发明是一种用于控制飞行器的系统，飞行器具有纵向轴线，垂直和水平轴线，以及安装在右翼和左翼上的左右翼和左右副翼。 详细地说，该系统包括一个安装在右翼上的右侧稳定器，右侧稳定器从右侧翼倾斜，使得其外端向下并可绕平行于稳定器跨度轴线的旋转轴偏转。 左稳定器安装到左翼，左稳定器从左翼倾斜，使得其外端向下并且可绕平行于稳定器的跨度轴线的旋转轴线偏转。 提供一种控制系统，同时使右副翼和稳定器向下偏转，左副翼和稳定器向上转动左转，并使右副翼和稳定器向上偏转，左副翼和稳定器向下偏转右转。

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