公开(公告)号：KR820001712B1

公开(公告)日：1982-09-21

申请号：KR780003194

申请日：1978-10-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COOPER DEAN E

IPC: B64C13/30

Abstract: A safety device for the fiying controls of an aircraft makes use of redundant members, A double quadrant(16) forming part of the control system is connected by cavbles(20,22) to a second similar double quadrant(24) so that the driven double quadrant rotates in the same direction as the driving double quadrant(16). In addition, the end of each cable(20,22) is connected by a tension spring(48,50) to the opposite arm of the driven double quadrant(24). In the event of a cable breaking the spring(48 or 50) exerts a force in the same direction as the cable does when operating.

公开(公告)号：CA1092579A

公开(公告)日：1980-12-30

申请号：CA312065

申请日：1978-09-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COOPER DEAN E

IPC: B64C13/30 ,  B64C13/04

Abstract: REDUNDANT FLIGHT CONTROL SYSTEM A flight control system utilizing pilot actuated flexible cables to selectively move a control quadrant and utilizing preloaded bungees additionally connecting each cable to the quadrant so that the quadrant can be pilot actuated despite the severance of one of the cables.

公开(公告)号：CA1094037A

公开(公告)日：1981-01-20

申请号：CA312066

申请日：1978-09-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DURNO RONALD A ,  COOPER DEAN E

IPC: B64C13/30 ,  F16H21/44

Abstract: REDUNDANT FLIGHT CONTROL SYSTEM A flight control system utilizing pilot actuated flexible cables to selectively move a control quadrant and utilizing balanced, preloaded springs connected to the quadrant to be selectively automatically releasable in response to cable severance so that the quadrant can be pilot actuated through its full control regime despite the severance of one of the cables.

公开(公告)号：CA1246717A

公开(公告)日：1988-12-13

申请号：CA458431

申请日：1984-07-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COOPER DEAN E ,  HOWLETT JAMES J

IPC: B64C27/14 ,  B64C27/00 ,  B64C27/12 ,  B64D31/00 ,  B64D31/06 ,  G05D1/08 ,  H02P23/00

Abstract: Rotorcraft Load Factor Enhancer Rotor speed is maintained at a reference speed by a closed-loop fuel control system. Load factor potential is enhanced by increasing the reference speed as a function of the helicopter pitch rate when undergoing positive pitch rate maneuvers.

公开(公告)号：CA1053211A

公开(公告)日：1979-04-24

申请号：CA257613

申请日：1976-07-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COOPER DEAN E ,  KLINGLOFF ROBERT F

IPC: B64C27/80

Abstract: A control for a helicopter having dual, coaxial, counterrotating rigid rotors which varies the cyclic control phase angle of each rotor in flight as a function of vehicle forward speed to thereby control the coupling of lateral cyclic pitch with longitudinal cyclic pitch so as to introduce differential cyclic pitch inputs which automatically produce aerodynamic moments in each rotor to minimize maneuver generated gyroscopic precession moments, which also produce optimum lateral lift vector displacement for all flight speeds.