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    Force Feel Using a Brushless DC Motor
    2.
    发明申请
    Force Feel Using a Brushless DC Motor 审中-公开

    公开(公告)号：US20180197385A1

    公开(公告)日：2018-07-12

    申请号：US15402497

    申请日：2017-01-10

    Applicant: Woodward, Inc.

    Inventor： Ganga P. Jayaraman ,  Michael L. Lyles ,  Zenon P. Szulyk ,  Bryan R. Haack

    IPC: G08B6/00 ,  H02P6/14 ,  H02P23/00

    CPC classification number: G08B6/00 ,  B64C13/0421 ,  B64C13/0427 ,  B64C13/46 ,  G05G9/047 ,  H02P6/085 ,  H02P6/14 ,  H02P6/17 ,  H02P21/06 ,  H02P23/0004

    Abstract: The subject matter of this specification can be embodied in, among other things, a motion control apparatus that includes a brushless DC motor to actuate a mechanical output based on a collection of phase power signals, a collection of first Hall effect sensors configured to provide a collection of first feedback signals in response to a sensed motor position and a sensed motor speed, a controller configured to determine a speed and position of the motor based on the feedback signals, and determine an electrical current level based on a collection of operational parameters and feedback signals including a position of the mechanical output, the motor speed, and the motor position, a current controller configured to provide electrical phase sequence output signals based on the electrical current level, and a motor driver configured to provide the collection of phase power signals based on the electrical phase sequence output signals.

    ROTORCRAFT FLIGHT CONTROL STICK TILTABLY MOUNTED ON A SUPPORT BY A FLEXIBLE ROD WITH A FIXED END
    3.
    发明申请
    ROTORCRAFT FLIGHT CONTROL STICK TILTABLY MOUNTED ON A SUPPORT BY A FLEXIBLE ROD WITH A FIXED END 审中-公开
    旋转飞行员控制系统通过灵活的支架固定安装在支架上

    公开(公告)号：US20140353433A1

    公开(公告)日：2014-12-04

    申请号：US14288781

    申请日：2014-05-28

    Applicant: AIRBUS HELICOPTERS

    Inventor： Bernard GEMMATI ,  Brice LEBERNICHEUX ,  Jean-Evrard BRUNEL

    IPC: B64C27/56 ,  B64C27/58

    CPC classification number: G05G9/047 ,  B64C13/0421 ,  B64C13/0427 ,  B64C27/04 ,  G05G2009/04722

    Abstract: A fly-by-wire control mechanism for a rotorcraft, the mechanism comprising a stick (1) hinged to tilt in multiple directions on a support (2), detector means (6) for detecting the tilting position of the stick (1) and generating electrical signals (7), and force feedback means providing the pilot with a sensation of forces (12) opposing tilting of the stick (1). The stick (1) includes a rod (13) having its distal end held in fixed manner in the support (2), while providing a movable mount for the stick (1) on the support (2). Causing the stick (1) to tilt leads to flexing of the rod (13) from its anchor zone (16) in the support (2), with the resistance of the rod (13) to flexing deformation serving to develop the opposing forces (12) and also being measured in order to generate the electrical signals (7).

    Abstract translation: 一种用于旋翼航空器的线控线控制机构，该机构包括铰链以在支撑件（2）上沿多个方向倾斜的杆（1），用于检测杆（1）的倾斜位置的检测器装置（6）和 产生电信号（7），以及强制反馈装置，为飞行员提供与棒（1）倾斜相反的力（12）的感觉。 棒（1）包括杆（13），杆（13）的远端以固定的方式保持在支撑件（2）中，同时为支撑件（2）上的棒（1）提供可移动的支架。 使棒（1）倾斜导致杆（13）从支撑件（2）中的锚定区域（16）弯曲，杆（13）的阻力发生弯曲变形以产生相反的力（ 12），并且还被测量以产生电信号（7）。

    AIRCRAFT, SYSTEMS, AND METHODS FOR TRIM CONTROL IN FLY-BY-WIRE AIRCRAFT SYSTEMS
    4.
    发明申请
    AIRCRAFT, SYSTEMS, AND METHODS FOR TRIM CONTROL IN FLY-BY-WIRE AIRCRAFT SYSTEMS 审中-公开
    飞行器飞行器系统的飞行器，系统和方法

    公开(公告)号：US20160152323A1

    公开(公告)日：2016-06-02

    申请号：US14513125

    申请日：2014-10-13

    Applicant: Gulfstream Aerospace Corporation

    Inventor： Kevin Claffy ,  Jong-Yeob Shin

    IPC: B64C13/50 ,  G05D1/08 ,  G05D1/00

    CPC classification number: B64C13/506 ,  B64C13/0421 ,  B64C13/0427 ,  B64C13/503

    Abstract: Aircraft, fly-by-wire systems, and controllers are provided. An aircraft includes a trim control system and a fly-by-wire system. The trim control system is configured for controlling surfaces of the aircraft. The fly-by-wire system is communicatively coupled with the trim control system and includes an input device and a controller. The input device is configured to receive a re-trim input from a user. The controller is communicatively coupled with the input device and is configured to control the trim control system, to obtain the re-trim input from the user, and to set a pitch trim of the aircraft based on a stable flight condition at a present airspeed of the aircraft in response to the re-trim input from the input device.

    Abstract translation: 提供飞机，线控系统和控制器。 一架飞机包括一个修剪控制系统和一个线控飞行系统。 修剪控制系统被配置为控制飞行器的表面。 线控线系统与调整控制系统通信耦合，并包括输入设备和控制器。 输入设备被配置为从用户接收修剪输入。 控制器与输入设备通信耦合，并且被配置为控制修剪控制系统，以获得来自用户的修剪输入，以及基于当前空速的稳定飞行条件来设置飞行器的俯仰微调 飞机响应于从输入设备的重新修剪输入。

    AIRCRAFT FLIGHT COMPENSATOR
    6.
    发明公开
    AIRCRAFT FLIGHT COMPENSATOR 审中-公开

    公开(公告)号：US20240286738A1

    公开(公告)日：2024-08-29

    申请号：US18570563

    申请日：2022-06-15

    Applicant: Safran Electronics & Defense

    Inventor： Alexis Perez-Duarte ,  Fabien Dugail

    IPC: B64C13/50 ,  B64C13/04 ,  G05G5/03

    CPC classification number: B64C13/507 ,  B64C13/0427 ,  G05G5/03

    Abstract: This aircraft flight trim system comprises a friction module that has variable friction and is coupled on one side to a drive shaft and on the other side to an output shaft via a kinematic chain.
    It has a control circuit which controls the friction module on the basis of an angular displacement value of the output shaft provided by a position sensor and on the basis of a force feedback control signal provided by a flight control computer.

    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。

    ACTIVE TRIM SYSTEM OF A FLIGHT CONTROL SYSTEM OF AN AIRCRAFT
    9.
    发明公开
    ACTIVE TRIM SYSTEM OF A FLIGHT CONTROL SYSTEM OF AN AIRCRAFT 审中-公开

    公开(公告)号：US20240217650A1

    公开(公告)日：2024-07-04

    申请号：US18509862

    申请日：2023-11-15

    Applicant: AIRBUS DEFENCE AND SPACE S.A.U.

    Inventor： Andrés JIMÉNEZ OLAZÁBAL

    IPC: B64C13/04 ,  B64C13/08 ,  B64C13/28

    CPC classification number: B64C13/0427 ,  B64C13/08 ,  B64C13/28

    Abstract: An active trim system of a flight control system of an aircraft that transmits a tactile feel to a pilot of the aircraft in response to a manoeuvre. The active trim system includes: a manual control member (6) an elastic deformation means (1) and a reversible actuator (2), intermediate linkage member (4) and a controller. The actuator (2) includes a rod (5) and a motor (3) parallel to the elastic deformation means (1) and is movable by the motor (3) and by the motion of the manual control member (6). The intermediate linkage member (4) is linked to the manual control member (6) between the manual control member (6) and the elastic deformation means (1) and the reversible actuator (2), a controller configured to: move the reversible actuator (2) to a predetermined zero position, and to provide stiffness against a displacement of the intermediate linkage member (4).

    Error Monitors for Collective and Cyclic Sticks
    10.
    发明公开
    Error Monitors for Collective and Cyclic Sticks 审中-公开

    公开(公告)号：US20240017820A1

    公开(公告)日：2024-01-18

    申请号：US17813128

    申请日：2022-07-18

    Applicant: Textron Innovations Inc.

    Inventor： Jillian Samantha Alfred ,  Lan Nam Hoang ,  Clifton Lee Harrell

    IPC: B64C13/04

    CPC classification number: B64C13/0421 ,  B64C13/0427

    Abstract: In an embodiment, a rotorcraft includes a control element; a first detent sensor connected to the control element, the first detent sensor being operable to generate detent slip rate data indicating movement of the control element and detent state data indicating pilot control of the control element; a first trim motor connected to the control element and operable to generate trim rate data; and an FCC in signal communication with the first detent sensor and the first trim motor, the FCC including an error monitor operable to compare the detent slip rate data with the trim rate data and determine whether the first detent sensor is functional or defective, operable to provide a first flight management function when the first detent sensor is determined to be functional, and operable to provide a second flight management function when the first detent sensor is determined to be defective.

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