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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
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).
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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
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).
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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
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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公开(公告)号：ES2080512T3
公开(公告)日：1996-02-01
申请号：ES92917911
申请日：1992-07-31
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SKONIECZNY JOSEPH P , FOGLER DONALD L JR , GOLD PHILIPP J , KELLER JAMES F , DRYFOOS JAMES B
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 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.
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Patent Agency Ranking
公开(公告)号：AU657165B2
公开(公告)日：1995-03-02
申请号：AU2462992
申请日：1992-07-31
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SKONIECZNY JOSEPH P , FOGLER DONALD L JR , GOLD PHILIPP J , KELLER JAMES F , DRYFOOS JAMES B
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 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.
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公开(公告)号：CA2118024A1
公开(公告)日：1993-11-25
申请号：CA2118024
申请日：1993-05-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LAPPOS NICHOLAS D , DRYFOOS JAMES B , KELLER JAMES F , FOWLER DONALD W
Abstract: 2118024 9323715 PCTABScor01 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.
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公开(公告)号：CA2116564A1
公开(公告)日：1993-03-18
申请号：CA2116564
申请日：1992-07-31
Applicant: UNITED TECHNOLOGIES CORP , BOEING CO
Inventor： SKONIECZNY JOSEPH P , FOGLER DONALD L JR , GOLD PHILLIP J , KELLER JAMES F , DRYFOOS JAMES B
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 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.
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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
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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公开(公告)号：AU2246895A
公开(公告)日：1995-11-29
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
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).
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