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    AUTOMATIC PILOT PITCH ANGLE COMPENSATION
    5.
    发明申请
    AUTOMATIC PILOT PITCH ANGLE COMPENSATION 有权
    自动导向台角度补偿

    公开(公告)号：US20100222944A1

    公开(公告)日：2010-09-02

    申请号：US12394299

    申请日：2009-02-27

    申请人： Frederick Charles Henry Blechen

    发明人： Frederick Charles Henry Blechen

    IPC分类号： G05D1/08

    CPC分类号： G05D1/0623 ,  G05D1/044 ,  G05D1/085

    摘要： A method, apparatus, and computer program product are present for operating an aircraft. Responsive to a command to hold an altitude of the aircraft, an adjustment to a pitch angle of the aircraft needed to substantially maintain the altitude of the aircraft is identified using a lift for the aircraft to form an identified adjustment to the pitch angle to reduce altitude deviations from at least one of a change in configuration of a number of flight surfaces and changes in wind. The pitch angle of the aircraft is adjusted using the identified adjustment during flight.

    摘要翻译： 存在用于操作飞机的方法，装置和计算机程序产品。 响应于控制飞机的高度的命令，使用飞行器的升降机来确定飞机所需的基本保持飞机高度的俯仰角的调整，以形成对俯仰角的识别的调整以降低高度 与多个飞行表面的配置变化和风的变化中的至少一个的偏差。 在飞行期间使用所识别的调整来调整飞行器的桨距角。

    PROCESS AND DEVICE FOR CONTROLLING AT LEAST ONE AERODYNAMIC ELEVATOR SURFACE OF AN AIRCRAFT DURING A TAKEOFF
    6.
    发明申请
    PROCESS AND DEVICE FOR CONTROLLING AT LEAST ONE AERODYNAMIC ELEVATOR SURFACE OF AN AIRCRAFT DURING A TAKEOFF 有权
    用于在起飞期间控制飞机的至少一个动力电梯表面的过程和装置

    公开(公告)号：US20030004621A1

    公开(公告)日：2003-01-02

    申请号：US10156231

    申请日：2002-05-29

    发明人： Guy Bousquet

    IPC分类号： B64C013/00

    CPC分类号： G05D1/085 ,  G05D1/0083

    摘要： Process and device for controlling at least one aerodynamic elevator surface of an aircraft during a takeoff. The device (1) comprises a control member (3), calculation means (5) and motor means (7) for controlling the aerodynamic elevator surface (2), as a function of an attitude angle control law received from the calculation means (5). If the duration T between the moment at which the pilot actuates the control member (3) so as to control the aerodynamic elevator surface (2) in such a way as to increase the pitch attitude angle of the aircraft and the moment at which the aircraft should reach the minimum takeoff speed is less than or equal to a nominal duration, the calculation means (5) determine and transmit a minimum control law. Otherwise, they determine and transmit a modified control law which is such that at a duration T after the actuation of the control member (3), the pitch attitude angle is substantially equal to a nominal value.

    摘要翻译： 用于在起飞期间控制飞行器的至少一个空气动力学电梯表面的过程和装置。 装置（1）包括控制构件（3），计算装置（5）和用于根据从计算装置（5）接收的姿态角度控制定律来控制空气动力学电梯表面（2）的电机装置（7） ）。 如果飞行员致动控制构件（3）的时刻之间的持续时间T，以便以增加飞机的俯仰姿态角度和航空器的时刻的方式控制空气动力学提升表面（2） 应达到最小起飞速度小于或等于标称持续时间，计算装置（5）确定并传送最小控制律。 否则，它们确定并传送修改的控制规则，使得在控制构件（3）的致动之后的持续时间T，俯仰姿态角度基本上等于标称值。

    Helicopter integrated fire and flight control having azimuth and pitch control
    7.
    发明授权
    Helicopter integrated fire and flight control having azimuth and pitch control 失效
    直升机综合火力和飞行控制具有方位和俯仰控制

    公开(公告)号：US5331881A

    公开(公告)日：1994-07-26

    申请号：US885702

    申请日：1992-05-19

    申请人： Donald W. Fowler ,  Nicholas D. Lappos ,  James B. Dryfoos ,  James F. Keller

    发明人： Donald W. Fowler ,  Nicholas D. Lappos ,  James B. Dryfoos ,  James F. Keller

    IPC分类号： B64C13/18 ,  B64C27/04 ,  F41G3/22 ,  G05D1/08

    CPC分类号： F41G3/22 ,  G05D1/085

    摘要： A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920) the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference. During integration of the fire control system and the flight control system, the flight control system is made less sensitive to small pilot command stick inputs below a stick input threshold magnitude, so that small or inadvertent pilot commanded yaw and pitch maneuvers will not affect the yaw and pitch attitude reference commanded by the fire control system azimuth and elevation commands. However, intended pilot commanded yaw and pitch maneuvers (70) maintain full authority at all times.

    摘要翻译： 消防控制系统（55）方位指令和仰角命令提供飞行控制系统姿态参考，以响应飞行控制系统在耦合瞄准模式下的操作。 响应于导频开关（920）的连续操作，方位指令和仰角指令低于相应阈值（940,941）和消防控制系统（55）的操作。 在联合瞄准模式下，方位指令和仰角指令分别代替飞行姿态反馈误差信号和俯仰姿态误差信号作为飞机姿态参考。 在消防控制系统和飞行控制系统的集成期间，使飞行控制系统对小型导向指令杆输入的敏感度低于杆输入阈值大小，从而小型或无意的飞行员指挥的偏航和俯仰机动不会影响偏航 以及由消防控制系统方位角和仰角指令指示的俯仰姿态参考。 然而，预期的飞行员指挥偏航和俯仰机动（70）始终保持完全的权威。