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公开(公告)号：DE3416242C2
公开(公告)日：1995-09-21
申请号：DE3416242
申请日：1984-05-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FISCHER WILLIAM C , WRIGHT STUART C , VERZELLA DAVID JOHN
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公开(公告)号：FR2579339A1
公开(公告)日：1986-09-26
申请号：FR8604061
申请日：1986-03-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MURPHY RICHARD D , FISCHER WILLIAM C
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公开(公告)号：IT8420760D0
公开(公告)日：1984-05-02
申请号：IT2076084
申请日：1984-05-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FISCHER WILLIAM C , WRIGHT STUART C , VERZELLA DAVID JOHN
Abstract: In a dual actuator system, runaways are identified by comparing the position and rate of one actuator to another. When there is a threshold position discrepancy and a sustained rate discrepancy, a fault is indicated. The faster actuator is identified as the runaway.
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公开(公告)号：FR2579339B1
公开(公告)日：1992-09-18
申请号：FR8604061
申请日：1986-03-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MURPHY RICHARD D , FISCHER WILLIAM C
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公开(公告)号：IT1173944B
公开(公告)日：1987-06-24
申请号：IT2076284
申请日：1984-05-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FISCHER WILLIAM C , ADAMS DON LUIS , WRIGHT STUART C , VERZELLA DAVID J
IPC: B64C13/00 , B64C13/08 , B64C13/18 , B64C13/44 , B64C27/56 , B64C27/57 , G05B9/03 , G05D1/08 , B64C
Abstract: The directions of travel of an inner and an outer loop actuator are monitored for movement in opposite directions within selected ranges and the outer loop actuator is disabled under selected conditions. These conditions may include movement of both the inner and outer loop actuators in opposite directions, any one of which has been detected moving at a rate greater than a selected rate or to a position outside a selected range. The invention is particularly suited for an aircraft trim actuator shutdown monitor system.
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Patent Agency Ranking
公开(公告)号：GB2140174A
公开(公告)日：1984-11-21
申请号：GB8410987
申请日：1984-04-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FISCHER WILLIAM C , WRIGHT STUART C , VERZELLA DAVID JOHN , ADAMS DON LUIS
Abstract: The directions of travel of an inner and an outer loop actuator are monitored for movement in opposite directions within selected ranges and the outer loop actuator is disabled under selected conditions. These conditions may include movement of both the inner and outer loop actuators in opposite directions, any one of which has been detected moving at a rate greater than a selected rate or to a position outside a selected range. The invention is particularly suited for an aircraft trim actuator shutdown monitor system.
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公开(公告)号：GB2140172A
公开(公告)日：1984-11-21
申请号：GB8410985
申请日：1984-04-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FISCHER WILLIAM C , WRIGHT STUART C , VERZELLA DAVID JOHN
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公开(公告)号：CA1153810A
公开(公告)日：1983-09-13
申请号：CA367869
申请日：1981-01-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FISCHER WILLIAM C , SIVAHOP ALBERT
Abstract: Tested, Dissimilar Helicopter Stability Augmentation The main roll and yaw axes of a helicopter having a main rotor operative in response to cyclic and collective pitch commands and a tail rotor operative in response to pitch commands, include stability inputs to actuators which are selectively provided by an analog channel, a digital channel, or one half by each, the digital channels being manifested in a digital computer system which includes programs of self-test, in-flight comparison between the inputs and outputs of corresponding analog and digital channels, and ground tests of testable rate gyro inputs to the various digital and analog channels and the outputs thereof.
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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
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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公开(公告)号：IT1188453B
公开(公告)日：1988-01-14
申请号：IT1978286
申请日：1986-03-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MURPHY RICHARD D , FISCHER WILLIAM C
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