公开(公告)号：DE3210817A1

公开(公告)日：1982-10-21

申请号：DE3210817

申请日：1982-03-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WRIGHT STUART CAMMETT ,  ADAMS DON LUIS ,  FISCHER WILLIAM CHRISTIAN ,  VERZELLA DAVID JOHN

IPC: B64C13/18 ,  B64C27/56 ,  G05D1/00 ,  G05D1/08 ,  B64C13/16

Abstract: In an aircraft automatic flight control system having a reference parameter synchronizing system (70) operable in response to a trim release switch (44), an initial trim release period (139), on the order of a large fraction of a second (137) causes (217, 218) a relatively slow effect trim reference integrator (208, 211) time constant, for smooth transitions of any error signal, followed by a relatively fast (216) effective reference integrator time constant for close, rapid tracking of the reference signal with the actual aircraft parameter.

公开(公告)号：IT8220489D0

公开(公告)日：1982-03-30

申请号：IT2048982

申请日：1982-03-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WRIGHT STUART CAMMETT ,  ADAMS DON LUIS ,  FISCHER WILLIAM CHRISTIAN ,  VERZELLA DAVID JOHN

IPC: B64C27/57 ,  B64C13/18 ,  G05D1/08 ,  B64D

Abstract: In an automatic flight control system (FIG. 1) an airspeed control engage function (84) is automatically engaged (136, FIG. 2; 244, FIG. 4) in response to airspeed above a threshold magnitude, such as 45 knots (88, FIG. 2) and will remain engaged (subject to a fault condition, 135) until the airspeed command (75) reaches a predetermined, insignificant magnitude (132). An airspeed error integrator 241 which accommodates the difference between a reference attitude and an attitude required for a reference airspeed, does not react to large airspeed errors as a consequence of pilot maneuvering due to pilot force on the control stick (35, 109) opening the input (252, FIG. 4) to the airspeed error integrator.

公开(公告)号：AU5484880A

公开(公告)日：1980-07-31

申请号：AU5484880

申请日：1980-01-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ADAMS DON LUIS ,  MURPHY RICHARD DENNIS ,  FISCHER WILLIAM CHRISTIAN

IPC: B64C13/00 ,  B64C13/04 ,  B64C27/54 ,  G05D1/00 ,  B64C13/16

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.