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    System and method of VTOL vehicle flight control inceptors
    3.
    发明授权
    System and method of VTOL vehicle flight control inceptors 有权

    公开(公告)号：US11667375B2

    公开(公告)日：2023-06-06

    申请号：US17384343

    申请日：2021-07-23

    Applicant: EMBRAER S.A.

    Inventor： Rafael Desideri De Freitas ,  Yasser Mahmud Abdallah

    IPC: B64C13/04 ,  B64C13/22 ,  B64C13/50 ,  B64C29/00

    CPC classification number: B64C13/0421 ,  B64C13/22 ,  B64C13/503 ,  B64C29/0033

    Abstract: A VTOL inceptor arrangement is handled by a single pilot and consists of or comprises a first inceptor and a second inceptor. The first inceptor is capable of controlling at least one axis of movement and the second inceptor is capable of controlling at least three axes of movement. The first inceptor is configured to be operated by a first hand of the pilot, and the second inceptor is configured to be operated by a second hand of the pilot different from the first hand. These two hand-operated inceptors enable use of reliable operation based on stick motion (i.e., the pilot's respective hands each grasp a respective inceptor) instead of relying on movement of switches, knobs or the like—which may not allow precision control under vibration or turbulent environments or conditions.

    WING FOR AN AIRCRAFT
    4.
    发明申请
    WING FOR AN AIRCRAFT 审中-公开

    公开(公告)号：US20180273161A1

    公开(公告)日：2018-09-27

    申请号：US15928895

    申请日：2018-03-22

    Applicant: Airbus Operations GmbH

    Inventor： Bernhard Schlipf ,  Dort Daandels

    IPC: B64C13/34 ,  B64C9/14

    CPC classification number: B64C13/34 ,  B64C9/14 ,  B64C13/22 ,  B64C13/24 ,  B64C13/28

    Abstract: A wing for an aircraft including a slat, and a connection assembly for movably connecting the slat to the main wing. The connection assembly includes a first connection element movably mounted to the main wing and mounted to the slat, and a second connection element movably mounted to the main wing and mounted to the slat. The connection assembly includes a drive unit connected to the slat that includes a first and second drive station spaced apart in the wing span direction. The first drive station has a first input section, a first gear unit and a first output section connected to the slat. The second drive station has a second input section connected to the drive shaft, a second gear unit, and a second output section connected to the slat. The drive unit includes a sync shaft coupling the first output section to the second output section.

    AUTOPILOT AND MANUAL CONTROL SWITCHING
    6.
    发明申请
    AUTOPILOT AND MANUAL CONTROL SWITCHING 审中-公开

    公开(公告)号：US20170361921A1

    公开(公告)日：2017-12-21

    申请号：US15616005

    申请日：2017-06-07

    Applicant: Ratier-Figeac SAS

    Inventor： Pierre-Jacques LABRY ,  Benoit MAZARS

    IPC: B64C13/22 ,  G05G5/04 ,  H01H50/20 ,  H01H50/44

    CPC classification number: B64C13/22 ,  B64C13/044 ,  B64C13/16 ,  B64D31/04 ,  B64D31/06 ,  G05G5/04 ,  H01H50/20 ,  H01H50/44 ,  Y02T50/44

    Abstract: A positioning and position maintaining device comprises a solenoid having an armature and an electromagnetic holder. The solenoid is arranged to effect positioning of an object upon translation of the armature and the electromagnetic holder is arranged to effect position maintaining in order to maintain the object in the position effected by the solenoid. An apparatus for aircraft autopilot and manual control feel-force control switching comprises an autopilot mechanism and the positioning and position maintaining device. The positioning and position maintaining device is arranged to engage the autopilot mechanism and maintain the engagement thereof. A method of switching between autopilot and manual control in an aircraft is also envisaged.

    METHOD OF CONTROLLING A MAIN ROTOR OF A ROTORCRAFT, AN ASSOCIATED CONTROL SYSTEM, AND A ROTORCRAFT FITTED WITH SUCH A CONTROL SYSTEM
    7.
    发明申请
    METHOD OF CONTROLLING A MAIN ROTOR OF A ROTORCRAFT, AN ASSOCIATED CONTROL SYSTEM, AND A ROTORCRAFT FITTED WITH SUCH A CONTROL SYSTEM 有权

    公开(公告)号：US20170144752A1

    公开(公告)日：2017-05-25

    申请号：US15356733

    申请日：2016-11-21

    Applicant: AIRBUS HELICOPTERS

    Inventor： Jean-Baptiste VALLART

    IPC: B64C27/14 ,  B64C27/52 ,  B64D25/00 ,  B64C13/04

    CPC classification number: B64C27/14 ,  B64C13/04 ,  B64C13/22 ,  B64C27/52 ,  B64C27/57 ,  B64D25/00

    Abstract: A control method and system for controlling a main rotor of a rotorcraft to perform a stage of flight in auto-rotation. The control system has a control member for controlling the collective pitch of the blades of the main rotor. The control member is movable over an amplitude of positions between two extreme physical stops. A calculation unit calculates a collective pitch angle for the blades of the main rotor, referred to as an “auto-rotation collective pitch”. This enables the main rotor to rotate at a speed of rotation that is optimum for the stage of flight in auto-rotation of the rotorcraft. A motor means controls the position of the control member at a predetermined position, referred to as the “auto-rotation position”, in which the control member generates a control setpoint for servo-controlling the current collective pitch of the blades of the main rotor on the “auto-rotation collective pitch”.

    ARTIFICIAL FORCE FEEL GENERATING DEVICE FOR A VEHICLE CONTROL SYSTEM OF A VEHICLE AND, IN PARTICULAR, OF AN AIRCRAFT
    8.
    发明申请
    ARTIFICIAL FORCE FEEL GENERATING DEVICE FOR A VEHICLE CONTROL SYSTEM OF A VEHICLE AND, IN PARTICULAR, OF AN AIRCRAFT 审中-公开
    机动车辆特别是飞机的车辆控制系统的人造力感生装置

    公开(公告)号：US20160304190A1

    公开(公告)日：2016-10-20

    申请号：US15071657

    申请日：2016-03-16

    Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    Inventor： Boris GROHMANN ,  Thomas ROHR ,  Jens KLAUBERT

    IPC: B64C13/46 ,  B64C13/08 ,  B64C27/605 ,  B64C27/64 ,  B64C13/22 ,  B64C27/04

    CPC classification number: B64C13/507 ,  B64C13/0421 ,  B64C13/0427 ,  B64C13/044 ,  B64C13/08 ,  B64C13/22 ,  B64C13/341 ,  B64C13/505 ,  B64C27/04 ,  B64C27/605 ,  B64C27/64 ,  Y02T50/44

    Abstract: An artificial force feel generating device for generation of an artificial feeling of force on an inceptor of a vehicle control system, the inceptor being adapted for controlling a servo-assisted control unit of the vehicle control system via a mechanical linkage, wherein at least one first force generating device and at least one second force generating device are mechanically connected to the inceptor, the first force generating device being provided for generating a nominal force acting in operation on the inceptor and the second force generating device being provided for generating a tactile cue force acting in operation on the inceptor, the first and second force generating devices being arranged in parallel. The invention relates further to an aircraft comprising such an artificial force feel generating device.

    Abstract translation: 一种用于在车辆控制系统的受体上产生人为感觉的人造力感觉产生装置，所述受体适于经由机械连杆来控制所述车辆控制系统的伺服辅助控制单元，其中至少一个第一 力产生装置和至少一个第二力产生装置机械连接到所述受体，所述第一力产生装置被设置用于产生在所述受体上作用的标称力，并且所述第二力产生装置用于产生触觉提示力 在受体上起作用，第一和第二力产生装置并列布置。 本发明进一步涉及包括这种人造力感觉发生装置的飞行器。

    METHOD AND APPARATUS FOR AUTOMATICALLY CONTROLLING AIRCRAFT FLIGHT CONTROL TRIM SYSTEMS
    9.
    发明申请
    METHOD AND APPARATUS FOR AUTOMATICALLY CONTROLLING AIRCRAFT FLIGHT CONTROL TRIM SYSTEMS 有权
    用于自动控制航空器飞行控制系统的方法和装置

    公开(公告)号：US20110137496A1

    公开(公告)日：2011-06-09

    申请号：US12959418

    申请日：2010-12-03

    Applicant: Michael Louis Everett ,  Louis Jackson Everett ,  Mario Ruiz

    Inventor： Michael Louis Everett ,  Louis Jackson Everett ,  Mario Ruiz

    IPC: G05D1/00

    CPC classification number: B64C13/08 ,  B64C13/18 ,  B64C13/22

    Abstract: An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a tinier. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated. If the force sensor continues to sense a force after the tinier times for a predetermined time, the trim can he adjusted in the appropriate direction until the force sensor measures no significant pilot input force.

    Abstract translation: 公开了一种用于自动修整飞机的飞行控制表面的自动装饰系统和方法。 力传感器测量由飞行员施加到飞行控制系统致动器的力。 然后由飞行员施加力的时间长度由一个较高的时间计时。 减少施加力的装饰系统包括在飞行控制表面上。 如果基于力传感器测量超过预定量的时间，则处理器确定是否需要修剪。 处理器可以将修剪系统设置为其中所需的修整。 空速传感器用于验证飞机是否具有足够的飞行速度。 力传感器可用于测量由飞行员施加的输入力。 如果飞行员输入力施加到控制器并且飞行器处于稳定状态，则定时器可​​以被激活。 如果力传感器在更长时间后继续感测力达预定时间，则可以在适当的方向上调节装饰，直到力传感器不测量重要的先导输入力。

    Manual override device, in particular for aircraft flight control
    10.
    发明授权
    Manual override device, in particular for aircraft flight control 有权
    手动超驰装置，特别适用于飞机飞行控制

    公开(公告)号：US06491148B2

    公开(公告)日：2002-12-10

    申请号：US09728355

    申请日：2000-12-01

    Applicant: Fernand Rodrigues

    Inventor： Fernand Rodrigues

    IPC: B64C1300

    CPC classification number: F16D23/12 ,  B64C13/22 ,  B64C13/28

    Abstract: An override device is presented having a manual control, an inlet gear, and an outlet gear, which are mounted to rotate about the same axis. The inlet gear rotates the outlet gear. The manual control has a cam which, in co-operation with an intermediate part suitable for following the cam, serves to disengage the rotation of the inlet gear under torque exerted on the manual control. The manual control drives the outlet gear. The Inlet gear rotates by having a set of friction disks and spring part suitable for exerting a force to compress the disks against one another. The intermediate part carries at least one pusher-forming element, which at the end of a displacement exerts force opposing that of the spring part and relaxes the friction force on at least some of the disks.

    Abstract translation: 提供了具有手动控制，进口齿轮和出口齿轮的超控装置，其被安装成围绕同一轴线旋转。 入口齿轮旋转出口齿轮。 手动控制装置具有凸轮，该凸轮与适合于跟随凸轮的中间部件配合，用于在施加在手动控制器上的扭矩下使入口齿轮的旋转脱离。 手动控制驱动出口齿轮。 入口齿轮通过具有一组摩擦盘和弹簧部分来适应于施加力以将盘相互压缩的旋转。 中间部分承载至少一个推动器形成元件，其在位移结束时施加与弹簧部件的力相反的力并且松弛至少一些盘上的摩擦力。

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