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108 条记录 (耗时 0.016 秒)

    Flight guidance panels with joystick controls
    1.
    发明授权
    Flight guidance panels with joystick controls 有权

    公开(公告)号：US11993393B2

    公开(公告)日：2024-05-28

    申请号：US18297114

    申请日：2023-04-07

    申请人： Gulfstream Aerospace Corporation

    发明人： Jeffrey Hausmann ,  Kristin Medin ,  Jim Jordan ,  Scott Bohanan

    IPC分类号： B64D43/00 ,  B64C13/04 ,  B64D11/06

    CPC分类号： B64D43/00 ,  B64C13/0421 ,  B64D11/0646 ,  B64D11/0689

    摘要： A flight guidance panel for an aircraft includes a subpanel display, a joystick, rotary encoders, a deflection sensor, and a processor. The subpanel display indicates autopilot modes and flight value goals and has a top-level state and a subpanel control state. The joystick is for user interaction with the subpanel display. The rotary encoder is coupled with the joystick to receive rotation inputs from a user of the joystick. The deflection sensor is coupled with the joystick to detect a deflection input from the user of the joystick. The processor is programmed to: change a state of the subpanel display to the subpanel control state corresponding to a selected subpanel in response to receiving the deflection input while the subpanel display is in the top-level state; and change the flight value goals in response to receiving the rotation inputs while the subpanel display is in the subpanel control state.

    SYSTEM AND METHOD FOR CONTROLLING FLIGHT PATH OF A BLOWN LIFT AIRCRAFT
    3.
    发明公开
    SYSTEM AND METHOD FOR CONTROLLING FLIGHT PATH OF A BLOWN LIFT AIRCRAFT 审中-公开

    公开(公告)号：US20240045447A1

    公开(公告)日：2024-02-08

    申请号：US18489228

    申请日：2023-10-18

    申请人： Electra Aero, Inc.

    发明人： Oliver MASEFIELD ,  Christopher B. COURTIN ,  Robert John HANSMAN, JR.

    IPC分类号： G05D1/08 ,  B64D45/00 ,  B64D31/06 ,  B64D27/24 ,  B64C13/04

    CPC分类号： G05D1/0808 ,  B64D45/00 ,  B64D31/06 ,  B64D27/24 ,  B64C13/0421

    摘要： In accordance with some embodiments, a system for controlling an aircraft is provided. The system can include a computing device, wherein the computing device includes at least one processor configured to control a flight path angle of the aircraft, and wherein the aircraft is a blown lift aircraft. The system can also include a control operator communicatively coupled to the computing device, wherein the control operator is configured to have at least two selectable settings. The system can also include at least two thrust-producing devices operatively coupled to a pair of wings on the aircraft and communicatively coupled to the computing device. The computing device may control the flight path angle of the aircraft by selectively operating the at least two thrust-producing devices based on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected setting of the control operator.

    Systems and methods for simulating an electric vertical take-off and landing aircraft
    4.
    发明授权
    Systems and methods for simulating an electric vertical take-off and landing aircraft 有权

    公开(公告)号：US11840324B1

    公开(公告)日：2023-12-12

    申请号：US18325628

    申请日：2023-05-30

    申请人： Archer Aviation, Inc.

    发明人： Nathan Thomas Depenbusch ,  Jeffery Scott Greenwood

    IPC分类号： B64C13/00 ,  B64C13/04 ,  B64C13/50 ,  G05D1/08

    CPC分类号： B64C13/0421 ,  B64C13/503 ,  G05D1/0858

    摘要： Disclosed are systems and methods for controlling an electric vertical take-off and landing (eVTOL) aircraft. In one embodiment, a system comprises a processor, a first inceptor, communicatively coupled to the processor, the first inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, and a second inceptor, communicatively coupled to the processor, the second inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, wherein the processor is configured to control a heading of an aircraft using a signal received from the second inceptor corresponding to lateral linear movement of the second inceptor. Some embodiments may additionally include at least one sensor and a thumb stick for each inceptor.

    Flight guidance panels with joystick controls
    6.
    发明授权
    Flight guidance panels with joystick controls 有权

    公开(公告)号：US11649066B2

    公开(公告)日：2023-05-16

    申请号：US16947281

    申请日：2020-07-27

    申请人： Gulfstream Aerospace Corporation

    发明人： Jeffrey Hausmann ,  Kristin Medin ,  Jim Jordan ,  Scott Bohanan

    IPC分类号： B64D43/00 ,  B64D11/06 ,  B64C13/04

    CPC分类号： B64D43/00 ,  B64C13/0421 ,  B64D11/0646 ,  B64D11/0689

    摘要： A flight guidance panel for an aircraft includes a subpanel display, a joystick, rotary encoders, a deflection sensor, and a processor. The subpanel display indicates autopilot modes and flight value goals and has a top-level state and a subpanel control state. The joystick is for user interaction with the subpanel display. The rotary encoder is coupled with the joystick to receive rotation inputs from a user of the joystick. The deflection sensor is coupled with the joystick to detect a deflection input from the user of the joystick. The processor is programmed to: change a state of the subpanel display to the subpanel control state corresponding to a selected subpanel in response to receiving the deflection input while the subpanel display is in the top-level state; and change the flight value goals in response to receiving the rotation inputs while the subpanel display is in the subpanel control state.

    ROTORCRAFT CONTROL MODE TRANSITION SMOOTHING
    9.
    发明申请
    ROTORCRAFT CONTROL MODE TRANSITION SMOOTHING 审中-公开

    公开(公告)号：US20180251207A1

    公开(公告)日：2018-09-06

    申请号：US15446911

    申请日：2017-03-01

    申请人： Bell Helicopter Textron Inc.

    发明人： Sung Kyun Kim

    IPC分类号： B64C13/04 ,  B64C13/50 ,  G05D1/08 ,  B64C27/04

    CPC分类号： G05D1/0858 ,  B64C13/0421 ,  B64C13/503 ,  B64C13/506 ,  B64C13/507 ,  B64C27/04

    摘要： In accordance with an embodiment, a method of operating a rotorcraft includes transitioning from a first mode to a second mode when a velocity of the rotorcraft exceeds a first velocity threshold. Transitioning between the first and second modes includes fading out a gain of a dynamic controller over a first period of time, and decreasing a value of an integrator of the dynamic controller over a second period of time. In the first mode, the translational speed of the rotorcraft is determined based on a pilot stick signal, and in the second mode, an output of an attitude rate controller is proportional to an amplitude of the pilot stick signal.

    Force Feel Using a Brushless DC Motor
    10.
    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

    申请人： Woodward, Inc.

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

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

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

    摘要： 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.