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    AIRCRAFT CONTROL SYSTEM, AIRCRAFT, AIRCRAFT CONTROL METHOD, AND PROGRAM
    2.
    发明公开
    AIRCRAFT CONTROL SYSTEM, AIRCRAFT, AIRCRAFT CONTROL METHOD, AND PROGRAM 审中-公开

    公开(公告)号：US20230409050A1

    公开(公告)日：2023-12-21

    申请号：US18036527

    申请日：2022-01-13

    申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

    发明人： Toru KOJIMA ,  Satoshi MORI

    IPC分类号： G05D1/08

    CPC分类号： G05D1/0825 ,  G08G5/02

    摘要： An aircraft control system includes a target instruction value calculation unit acquires a target instruction value to set an aircraft in a target state, a reference velocity calculation unit inputs, to a reference model in which reference velocity corresponding to a reference value of aircraft velocity is set uniquely as an output value according to an input value, a value based on the target instruction value as the input value. A relative velocity calculation unit calculates relative velocity of the aircraft to a target position, the relative velocity being used in control of the aircraft. An estimated disturbance quantity calculation unit calculates an estimated disturbance quantity acting on the aircraft, based on a difference between the relative velocity and the reference velocity, and a correction target instruction value calculation unit corrects the target instruction value, based on the estimated disturbance quantity calculated at a previous timing.

    METHOD FOR MANAGING IMBALANCE IN A DISTRIBUTED PROPULSION SYSTEM
    4.
    发明申请
    METHOD FOR MANAGING IMBALANCE IN A DISTRIBUTED PROPULSION SYSTEM 审中-公开

    公开(公告)号：US20180305033A1

    公开(公告)日：2018-10-25

    申请号：US15955264

    申请日：2018-04-17

    申请人： Airbus (S.A.S.)

    发明人： Emmanuel Joubert ,  Laurent Juve ,  Thibault Baldivia ,  Clément Veillerot

    IPC分类号： B64D31/10 ,  G05D1/08

    CPC分类号： B64D31/10 ,  B64D27/24 ,  G05D1/0072 ,  G05D1/0825

    摘要： A method for managing unbalanced thrusts caused by engine failures in an aircraft provided with a distributed propulsion system, the distributed propulsion system including 2N powertrains (PTi), with N a strictly positive integer and i an integer lying between 1 and 2N inclusive, distributed symmetrically in relation to a plane of symmetry of the aircraft, according to which the power of at least one powertrain belonging to a first side of the plane of symmetry is reduced when a failure occurs in a powertrain belonging to the opposite side, such that the sum of the moments of the thrusts generated by the powertrains in relation to the center of gravity of the aircraft is nil, to within regulatory tolerances.

    MANEUVER PLANNING WITH HIGHER ORDER RATIONAL BEZIER CURVES
    6.
    发明申请
    MANEUVER PLANNING WITH HIGHER ORDER RATIONAL BEZIER CURVES 有权

    公开(公告)号：US20170213466A1

    公开(公告)日：2017-07-27

    申请号：US15006876

    申请日：2016-01-26

    申请人： Michel M. Azar

    发明人： Michel M. Azar

    IPC分类号： G08G5/00 ,  B64C39/02 ,  G01C21/20 ,  G05D1/00 ,  G05D1/10

    CPC分类号： G05D1/0088 ,  G01C21/20 ,  G05D1/0202 ,  G05D1/0212 ,  G05D1/0816 ,  G05D1/0825 ,  G08G5/0034 ,  G08G5/0069

    摘要： Systems and methods are provided for generating a maneuver on a propagated route for an unmanned vehicle from a series of waypoints. A planner interface is configured to receive the waypoints and at least one parameter representing constraints on the propagated route of the unmanned vehicle. A curve generation component is configured to determine respective positions for each of a set of N+1 control points for a rational Bezier curve of Nth order from the series of waypoints and the parameter. N is an integer greater than three. A weight generation component is configured to determine scalar weights for the set of N+1 control points from the parameter. A navigation interface is configured to provide the maneuver, generated from the positions for the set of control points and the scalar weights, to a control system of the unmanned vehicle, configured to execute the provided maneuver at the unmanned vehicle.

    FORMATION FLIGHT CONTROL
    10.
    发明申请
    FORMATION FLIGHT CONTROL 有权
    形成飞行控制

    公开(公告)号：US20140214243A1

    公开(公告)日：2014-07-31

    申请号：US13752119

    申请日：2013-01-28

    申请人： The Boeing Company

    发明人： Brian T. Whitehead ,  Stefan R. Bieniawski ,  David Halaas ,  Eugene Lavretsky

    IPC分类号： B64C19/00

    CPC分类号： B64C19/00 ,  G05D1/0202 ,  G05D1/0825 ,  G05D1/104

    摘要： An apparatus for controlling the formation flight of a trailing aircraft relative to a vortex generated by a leading aircraft includes a position module, peak-seeking module, limiter module, and control module. The position module is configured to determine a position of the vortex relative to the trailing aircraft. The peak-seeking module is configured to determine a desired position of the trailing aircraft for providing desired vortex-induced aerodynamic benefits based on the position of the vortex relative to the trailing aircraft and a mapping function of an individual performance metric. The limiter module is configured to modify the desired position of the trailing aircraft to avoid unintended crossings of the trailing aircraft into the vortex. Finally, the control module is configured to control flight of the trailing aircraft based on one of the desired position of the trailing aircraft and modified desired position of the trailing aircraft.

    摘要翻译： 用于控制尾飞机相对于由主飞机产生的涡流的飞行的装置包括位置模块，寻峰模块，限制模块和控制模块。 位置模块被配置成确定涡流相对于后方飞行器的位置。 峰值寻求模块被配置为基于相对于后方飞行器的涡流的位置以及单个性能度量的映射函数来确定拖尾飞行器的期望位置，以提供期望的涡流引起的空气动力学优点。 限制器模块被配置为修改拖尾飞行器的期望位置，以避免尾随飞机进入涡流的意外交叉。 最后，控制模块被配置成基于拖尾飞行器的期望位置和后方飞行器的修改的期望位置之一来控制尾翼飞行器的飞行。