公开(公告)号：ES2110517T3

公开(公告)日：1998-02-16

申请号：ES92918348

申请日：1992-07-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GOLD PHILLIP J ,  FAULL WALTER R

IPC: G05D1/08 ,  B64C13/18

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 low speed 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.

公开(公告)号：ES2089550T3

公开(公告)日：1996-10-01

申请号：ES92917949

申请日：1992-07-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GOLD PHILLIP J ,  LAPPOS NICHOLAS D ,  ADAMS DON L ,  WRIGHT STUART C

IPC: G05D1/08

Abstract: A helicopter flight control system includes an automatic turn coordination system which provides a coordinating yaw command signal to the tail rotor of the helicopter. The system stores on command a trim attitude (e.g., signals indicative of bank angle, lateral ground speed, and lateral acceleration) about which automatic turn coordination is provided, thus providing the pilot with automatic turn coordination about attitudes other than wings level.

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

IPC: B64C27/57 ,  G05D1/08 ,  G05D1/00

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).

公开(公告)号：CA2113731A1

公开(公告)日：1993-03-18

申请号：CA2113731

申请日：1992-07-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GOLD PHILLIP J ,  LAPPOS NICHOLAS D ,  ADAMS DON L ,  WRIGHT STUART C

IPC: G05D1/08

Abstract: A helicopter flight control system includes an automatic turn coordination system which provides a coordinating yaw command signal to the tail rotor of the helicopter. The system stores on command a trim attitude (e.g., signals indicative of bank angle, lateral ground speed, and lateral acceleration) about which automatic turn coordination is provided, thus providing the pilot with automatic turn coordination about attitudes other than wings level.