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    AUTOMATIC APPROACH TO HOVER SYSTEM
    3.
    发明专利
    AUTOMATIC APPROACH TO HOVER SYSTEM 未知

    公开(公告)号：CA1081830A

    公开(公告)日：1980-07-15

    申请号：CA271669

    申请日：1977-02-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MURPHY RICHARD D ,  COTTON LOU S

    IPC: B64C27/57 ,  G05D1/10 ,  G05D1/00

    Abstract: In a helicopter having an automatic pilot system for controlling the main rotor collective pitch, main rotor longitudinal and lateral cyclic pitch, and tail rotor collective pitch, in response to inputs provided from normal sensors, navigational instruments and controls,(which include a among others is known, doppler radar, a pilot panel, an air speed indicator, a radar altimeter. a barometric altimeter and a longitudinal accelerometer). commands to control automatic approach to a desired hover position are provided to the autopilot system in response to signals normally supplied by a TACNAV unit as well as the sensors, navigational units and controls; controls are provided for altitude and rate of descent, so as to terminate in hover at a desired altitude, as well as for turns, courses, and speed so as to approach the desired point of hover upwind and to decelerate in a controlled fashion to hover.

    5.
    发明专利
    未知

    公开(公告)号：NO146947C

    公开(公告)日：1983-01-05

    申请号：NO802804

    申请日：1980-09-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ADAMS DON L ,  MURPHY RICHARD D ,  FISCHER WILLIAM C

    IPC: B64C13/00 ,  B64C13/04 ,  B64C27/54 ,  G05D1/00

    Abstract: A helicopter having an automatic flight control system including an inner, stability loop is rendered less sensitive to short-term, inadvertent pilot inputs by applying a washed-out derivative of a stick position signal to the inner stability loop in a sense to countermand the pilot action. Using a washed-out signal countermands only short-term rapid stick motions, which may be induced by the pilot actively, but inadvertently, or inactively due to coupling between the pilot or the stick and motion of the fuselage, while permitting purposeful, long-term stick positions to have the full, intended effect.

    SENSOR FAULT DETECTION BY ACTIVITY MONITORING
    9.
    发明专利
    SENSOR FAULT DETECTION BY ACTIVITY MONITORING 未知

    公开(公告)号：CA1164067A

    公开(公告)日：1984-03-20

    申请号：CA376457

    申请日：1981-04-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MURPHY RICHARD D ,  CLELFORD DOUGLAS H

    IPC: G05B23/02 ,  G01D18/00 ,  G01R19/00 ,  G01R31/02 ,  G01R31/28 ,  G05D1/00 ,  G08B29/00

    Abstract: Sensor Fault Detection By Activity Monitoring Faults in a sensor (10) are detected by excess rate fault determination by taking the differentiated (58, 107), rate limited (60, 100, 111) integral (64, 112) from the raw sensor output (72, 113) and indicating a fault (15, 117) in the event that the difference exceeds a predetermined magnitude (76, 114). A null fault (22, 91) is provided in the event that the sensor output does not show a significant change (52, 88) within a given time interval (20, 80) whenever a related sensor (31) indicates (29, 84) that the first sensor (10) should have measurable activity. Both analog (Fig. 1) and digital (Fig. 2, Fig. 3) embodiments are disclosed.

    DESENSITIZING HELICOPTER CONTROL RESPONSE TO INADVERTENT PILOT INPUT
    10.
    发明专利
    DESENSITIZING HELICOPTER CONTROL RESPONSE TO INADVERTENT PILOT INPUT 未知

    公开(公告)号：DE3065491D1

    公开(公告)日：1983-12-15

    申请号：DE3065491

    申请日：1980-01-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ADAMS DON L ,  MURPHY RICHARD D ,  FISCHER WILLIAM C

    IPC: B64C13/00 ,  B64C13/04 ,  B64C27/54 ,  G05D1/00

    Abstract: A helicopter having an automatic flight control system including an inner, stability loop is rendered less sensitive to short-term, inadvertent pilot inputs by applying a washed-out derivative of a stick position signal to the inner stability loop in a sense to countermand the pilot action. Using a washed-out signal countermands only short-term rapid stick motions, which may be induced by the pilot actively, but inadvertently, or inactively due to coupling between the pilot or the stick and motion of the fuselage, while permitting purposeful, long-term stick positions to have the full, intended effect.

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