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    Alternative piloting system for integrating in a pre-existing aircraft
    2.
    发明授权
    Alternative piloting system for integrating in a pre-existing aircraft 有权

    公开(公告)号：US12111658B2

    公开(公告)日：2024-10-08

    申请号：US17416179

    申请日：2019-12-19

    申请人： SAFRAN ELECTRONICS & DEFENSE

    发明人： Eric Walter ,  Hoon Ta Huang Jackson ,  Julien Farjon ,  Loïc Fougeres ,  Mikaël Diaz ,  Ng Kwee Chye ,  Nicolas Cadalen ,  Philippe Tranie

    IPC分类号： G05D1/00 ,  B64C13/18

    CPC分类号： G05D1/0061 ,  G05D1/0011 ,  B64C13/18

    摘要： An alternative piloting system arranged to be integrated in a pre-existing aircraft that includes original systems having flight control and autopilot systems. The autopilot system includes a piloting device independent of the original systems, having a positioning unit arranged to produce positioning data relating to the aircraft, and a control unit arranged to produce an alternative piloting setpoint for the aircraft; an acquisition and analysis device, including acquisition device arranged to acquire data produced by the original systems, positioning data and alternative piloting setpoint as produced by the piloting device, and decision device arranged to decide whether the alternative piloting setpoint should or should not be used for piloting the aircraft; and an interface device arranged to control the flight control system on the basis of the alternative piloting setpoint when the decision device of the acquisition and analysis device decide that said alternative piloting setpoint should be used for piloting the aircraft.

    FLYING OBJECT CONTROL METHOD
    4.
    发明公开
    FLYING OBJECT CONTROL METHOD 审中-公开

    公开(公告)号：US20240067329A1

    公开(公告)日：2024-02-29

    申请号：US18259658

    申请日：2020-01-01

    申请人： AERONEXT INC.

    发明人： Yoichi SUZUKI

    IPC分类号： B64C13/18 ,  B64C39/02

    CPC分类号： B64C13/18 ,  B64C39/024

    摘要： Provided is a method for controlling the directional orientation of a flying object so that the flying object faces in a direction that increases the efficiency of flight over the immediately preceding state based on predetermined information. To provide a method of flight control whereby a flying object having directional characteristics according to such a configuration can fly in an attitude suitable for the relative wind direction and wind speed in flight in order to actively utilize lift, reduce drag, and the like. According to such a configuration, the optimal flight attitude can be obtained by adjusting the wind direction and aircraft direction, thereby increasing safety while improving fuel efficiency.

    AUTOMATIC ROTOR TILT CONTROL
    8.
    发明公开
    AUTOMATIC ROTOR TILT CONTROL 审中-公开

    公开(公告)号：US20230202651A1

    公开(公告)日：2023-06-29

    申请号：US17561195

    申请日：2021-12-23

    申请人： Textron Innovations Inc.

    发明人： Kevin Thomas Christensen ,  Sang Gyun Park

    IPC分类号： B64C29/00 ,  B64C13/22 ,  B64C13/18

    CPC分类号： B64C29/0033 ,  B64C13/18 ,  B64C13/22

    摘要： A flight control computer (FCC) may implement automatic rotor tilt control by gathering or receiving, as inputs, airspeed or a commanded airspeed for the aircraft, acceleration or a commanded acceleration for the aircraft, pitch attitude of the aircraft and pilot pitch bias commands for the aircraft, a rotor tilt angle, and/or the like. The FCC calculates, from the airspeed, the commanded airspeed, the acceleration, the commanded acceleration, the pitch attitude, the pilot pitch bias commands, and/or the like, a commanded rotor tilt angle for the aircraft. From the aircraft rotor tilt angle and the commanded rotor tilt angle, the FCC calculates a rotor tilt angle error for the aircraft, and from the rotor tilt angle error, calculates a rotor tilt rate command for the aircraft. The FCC outputs the resulting rotor tilt rate command to (an) aircraft flight control element actuator(s) to tilt the aircraft rotor.

    UAV AND CONTROL METHOD THEREOF
    9.
    发明公开
    UAV AND CONTROL METHOD THEREOF 审中-公开

    公开(公告)号：US20230202644A1

    公开(公告)日：2023-06-29

    申请号：US17563919

    申请日：2021-12-28

    申请人： INDUSTRIAL TECHNOLOGY RESEARCH INSTITUTE

    发明人： Yi-Lun WEN ,  Yu-Kai WANG

    IPC分类号： B64C13/18 ,  B64C39/02 ,  G01C5/06 ,  G01C5/00 ,  G05D1/10

    CPC分类号： B64C13/18 ,  B64C39/024 ,  G01C5/06 ,  G01C5/005 ,  G05D1/101 ,  B64C2201/146 ,  B64C2201/141

    摘要： A UAV including a first barometer and a processing unit is provided. The first barometer provides a first air pressure value. The processing unit is coupled to the first barometer for receiving the first air pressure value from the first barometer, performing timing-synchronization on the first air pressure value provided by the first barometer and an external reference air pressure value provided by an external reference barometer to obtain a timing-synchronized first air pressure value and recalculating the timing-synchronized first air pressure value to generate a compensated air pressure value, wherein the processing unit performs data fusion calculation on the first air pressure value, the compensated air pressure value and a sensor data to obtain a target fused data and real-timely controls the altitude and the posture of the UAV according to the target fused data.

    SYSTEMS, METHODS, AND APPARATUS TO CONTROL AIRCRAFT ROLL OPERATIONS USING WING ACTUATORS
    10.
    发明申请
    SYSTEMS, METHODS, AND APPARATUS TO CONTROL AIRCRAFT ROLL OPERATIONS USING WING ACTUATORS 有权

    公开(公告)号：US20230125050A1

    公开(公告)日：2023-04-20

    申请号：US17898132

    申请日：2022-08-29

    申请人： The Boeing Company

    发明人： Neal Van Huynh

    IPC分类号： B64C13/50 ,  B64C13/40 ,  B64C13/18

    摘要： Systems, methods, and apparatus for controlling aircraft roll operations are disclosed. An example system includes an aileron actuator including a mode selector valve to control fluid flow through the aileron actuator, and a valve spring coupled to the mode selector valve, the valve spring to adjust the mode selector valve from the active position to a block position, the block position to prevent fluid flow through the aileron actuator, a wing cable system coupled to the aileron actuator, a wing actuator coupled to the wing cable system, the wing actuator to control displacement of the aileron of the aircraft in response to the mode selector valve being in the block position, and a differential linkage coupled to the wing actuator and the aileron, the differential linkage to translate the displacement of the wing actuator into rotational movement to adjust the aileron from a first position to a second position.