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公开(公告)号：NO146947B
公开(公告)日：1982-09-27
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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公开(公告)号：DE3609267A1
公开(公告)日：1986-10-09
申请号：DE3609267
申请日：1986-03-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MURPHY RICHARD D , FISCHER WILLIAM C
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公开(公告)号：CA1166720A
公开(公告)日：1984-05-01
申请号：CA383393
申请日：1981-08-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CLELFORD DOUGLAS H , MURPHY RICHARD D
Abstract: Helicopter Attitude and Airspeed Acquisition And Retention System A helicopter pitch axis autopilot system, including airspeed hold at cruise speeds and pitch attitude hold below cruise speeds, includes integrated longitudinal acceleration drift corrected by heavily filtered Pitot static airspeed as a filtered airspeed reference, use of a beeper to nudge the airspeed reference above cruise speeds or the pitch attitude reference below cruise speeds, resynchronizing of airspeed reference, pitch attitude reference, pitch autopilot integrator and stick trim position reference, momentarily in response to airspeed transitions between cruise and sub-cruise speeds or in response to initiation of beeping, and continuously during trim release. Pilot override without disengagement of the autopilot and ultimate return to a previous speed or attitude is achieved by sensing pilot activity and causing the pitch autopilot integrator value to be held during pilot override, and limiting the value of airspeed error that drives the pitch autopilot integrator once the pilot activity has subsided.
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公开(公告)号：NO802804L
公开(公告)日：1980-09-23
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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Patent Agency Ranking
公开(公告)号：GB2172722B
公开(公告)日：1989-06-28
申请号：GB8606033
申请日：1986-03-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MURPHY RICHARD D , FISCHER WILLIAM C
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公开(公告)号：GB2172722A
公开(公告)日：1986-09-24
申请号：GB8606033
申请日：1986-03-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MURPHY RICHARD D , FISCHER WILLIAM C
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公开(公告)号：DK146588C
公开(公告)日：1984-04-30
申请号：DK385780
申请日：1980-09-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ADAMS DON LUIS , 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：DK146588B
公开(公告)日：1983-11-14
申请号：DK385780
申请日：1980-09-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ADAMS DON LUIS , 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：CA1127133A
公开(公告)日：1982-07-06
申请号：CA343973
申请日：1980-01-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ADAMS DON L , MURPHY RICHARD D , FISCHER WILLIAM C
Abstract: Desensitizing Helicopter Control Response To Inadvertent Pilot Inputs 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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