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    Low Speed Turn Coordination for Rotary Wing Aircraft
    11.
    发明专利
    Low Speed Turn Coordination for Rotary Wing Aircraft 未知

    公开(公告)号：CA2114551A1

    公开(公告)日：1993-03-18

    申请号：CA2114551

    申请日：1992-07-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GOLD PHILLIP J ,  FAULL WALTER R

    IPC: B64C13/18 ,  G05D1/08

    Abstract: A helicopter flight control system (21) includes a model following control system architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate helicopter flight during a low speed banked turn. The control system processes information from a variety of helicopter sensors (31) in order to provide the coordinating yaw command signal on an output line (72) to the tail rotor (20) of the helicopter.

    12.
    发明专利
    未知

    公开(公告)号：ES2120206T3

    公开(公告)日：1998-10-16

    申请号：ES95919762

    申请日：1995-05-04

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GOLD PHILLIP J ,  FOGLER DONALD L JR ,  DRYFOOS JAMES B

    IPC: B64C13/00 ,  B64C13/18 ,  B64C27/57 ,  G05D1/08 ,  G05D1/10

    Abstract: A velocity command system is provided with a velocity stabilization mode wherein aircraft flight path referenced velocities are determined with respect to an inertial frame of reference, the flight path referenced velocities are held constant during pilot commanded yaw maneuvers so that the aircraft maintains a fixed inertial referenced flight path regardless of the pointing direction of the aircraft. Velocity control with respect to an inertial frame of reference is accomplished by controlling the aircraft flight path based on aircraft body referenced commanded lateral and longitudinal acceleration and based on aircraft body referenced lateral and longitudinal centrifugal acceleration. Operation in the velocity stabilization mode is provided in response to the manual activation of the velocity stabilization mode by the pilot, provided that the aircraft is already operating in the ground speed mode and the aircraft is not in a coordinated turn.

    13.
    发明专利
    未知

    公开(公告)号：ES2101872T3

    公开(公告)日：1997-07-16

    申请号：ES92920122

    申请日：1992-08-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GOLD PHILLIP J ,  WRIGHT STUART C

    IPC: G05D1/00 ,  G05D1/08 ,  G05D1/10 ,  B64C27/54

    Abstract: A helicopter fly-by-wire flight control system (21) includes a model following control system architecture which provides the pilot with maneuvering feel. Maneuvering feel is generated by varying the gain of a rate model (52) in the control system to schedule a constant sidearm controller force per g of load factor currently on the helicopter main rotor. This gain variation works in conjunction with control logic which requires the pilot to apply a nose up pitch command during steep banked turns in order to offset a control system induced downward (pitch) bias of the aircraft nose. The control system induced bias is generated only during steep banked turns, thus allowing the pilot to fly shallow banked coordinated turns without having to apply a nose up pitch command.

    14.
    发明专利
    未知

    公开(公告)号：ES2099832T3

    公开(公告)日：1997-06-01

    申请号：ES92918139

    申请日：1992-07-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GOLD PHILLIP J ,  STILLES LORREN ,  POST JOSEPH A

    IPC: G05D1/06

    Abstract: A vertical control system for a rotary winged aircraft receives inputs from a displacement collective stick and a sidearm controller. The system provides a set point for the vertical rate of change of the helicopter as a function of a vertical lift command signal from the sidearm controller. The set point is used as a reference for an altitude rate of change feedback path, and an integrated value of the set point is used for an altitude feedback path. The set point is also input to a feedforward control path having an inverse vehicle model to provide a command signal indicative of the command for aircraft collective pitch necessary to achieve the desired set point. Signals from all three paths (i.e., the altitude rate of change feedback path, the altitude feedback path, and the feedforward path) are summed to provide a signal to backdrive the displacement collective which controls main rotor collective pitch.

    Vertical Control System for Rotary Wing Aircraft
    18.
    发明专利
    Vertical Control System for Rotary Wing Aircraft 未知

    公开(公告)号：CA2114022A1

    公开(公告)日：1993-03-18

    申请号：CA2114022

    申请日：1992-07-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GOLD PHILLIP J ,  STILLES LORREN ,  POST JOSEPH A

    IPC: G05D1/06

    Abstract: A vertical control system for a rotary winged aircraft receives inputs from a displacement collective stick and a sidearm controller. The system provides a set point for the vertical rate of change of the helicopter as a function of a vertical lift command signal from the sidearm controller. The set point is used as a reference for an altitude rate of change feedback path, and an integrated value of the set point is used for an altitude feedback path. The set point is also input to a feedforward control path having an inverse vehicle model to provide a command signal indicative of the command for aircraft collective pitch necessary to achieve the desired set point. Signals from all three paths (i.e., the altitude rate of change feedback path, the altitude feedback path, and the feedforward path) are summed to provide a signal to backdrive the displacement collective which controls main rotor collective pitch.

    TURN COORDINATION INHIBIT FOR ROTARY WING AIRCRAFT CONTROL SYSTEM
    20.
    发明专利
    TURN COORDINATION INHIBIT FOR ROTARY WING AIRCRAFT CONTROL SYSTEM 未知

    公开(公告)号：CA2189455C

    公开(公告)日：2003-02-11

    申请号：CA2189455

    申请日：1995-04-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GOLD PHILLIP J ,  FOGLER DONALD L JR ,  SKONIECZNY JOSEPH ,  KELLER JAMES F

    IPC: B64C27/57 ,  G05D1/08 ,  B64C19/00

    Abstract: A turn coordination inhibit system (150) inhibits a rotary winged aircraft c ontrol system from operating in an automatic turn coordination mode when a pilot desired to perform a sideslip maneuver, e.g., a flat turn. When automatic turn coordination is not en gaged (132, 212, 215), e.g., the aircraft is not in a coordinated turn, and either aircraft bank angle (119) exceeds an inhibit threshold magnitude (210) or a pilot yaw command provided by a pilot sidearm controller (155) ex ceeds a minimum threshold value (243), e.g., the sidearm controller is out of detent in the yaw axis, automatic turn coordination is inhibited (152). Automatic turn coordination remains inh ibited until both aircraft bank angle falls below a reset threshold magnitude (230) and the sidearm controller is back in the detent positi on for the yaw axis (243).

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