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    Turn coordination inhibit for rotary wing aircraft control system
    2.
    发明专利
    Turn coordination inhibit for rotary wing aircraft control system 未知

    公开(公告)号：AU681279B2

    公开(公告)日：1997-08-21

    申请号：AU2246895

    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 ,  G05D1/00

    Abstract: A turn coordination inhibit system (150) inhibits a rotary winged aircraft control 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 engaged (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) exceeds 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 inhibited until both aircraft bank angle falls below a reset threshold magnitude (230) and the sidearm controller is back in the detent position for the yaw axis (243).

    TURN COORDINATION INHIBIT FOR ROTARY WING AIRCRAFT CONTROL SYSTEM
    3.
    发明专利
    TURN COORDINATION INHIBIT FOR ROTARY WING AIRCRAFT CONTROL SYSTEM 未知

    公开(公告)号：CA2189455A1

    公开(公告)日：1995-11-09

    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).

    LOW SPEED TURN COORDINATION FOR ROTARY WING AIRCRAFT
    4.
    发明专利
    LOW SPEED TURN COORDINATION FOR ROTARY WING AIRCRAFT 未知

    公开(公告)号：CA2114551C

    公开(公告)日：1998-05-05

    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 syste m architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate hel icopter flight during a low speed banked turn. The control system processes information from a variety of helicopter sensors (3 1) in order to provide the coordinating yaw command signal on an output line (72) to the tail rotor (20) of the helicopter.

    Low speed turn coordination for rotary wing aircraft
    5.
    发明专利
    Low speed turn coordination for rotary wing aircraft 未知

    公开(公告)号：AU657359B2

    公开(公告)日：1995-03-09

    申请号：AU2474492

    申请日：1992-07-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GOLD PHILLIP J ,  FAULL WALTER R

    IPC: B64C13/18 ,  G05D1/08 ,  G05D1/00

    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.

    8.
    发明专利
    未知

    公开(公告)号：ES2121370T3

    公开(公告)日：1998-11-16

    申请号：ES95915655

    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 ,  G05D1/00

    Abstract: A turn coordination inhibit system (150) inhibits a rotary winged aircraft control 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 engaged (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) exceeds 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 inhibited until both aircraft bank angle falls below a reset threshold magnitude (230) and the sidearm controller is back in the detent position for the yaw axis (243).

    INERTIAL VELOCITY COMMAND SYSTEM
    9.
    发明专利
    INERTIAL VELOCITY COMMAND SYSTEM 未知

    公开(公告)号：CA2191861A1

    公开(公告)日：1995-12-14

    申请号：CA2191861

    申请日：1995-05-04

    Applicant: UNITED TECHNOLOGIES CORP SIKOR

    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.

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