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    PIVOTAL JOINT
    25.
    发明授权
    PIVOTAL JOINT 失效

    公开(公告)号：KR820002366B1

    公开(公告)日：1982-12-27

    申请号：KR790001936

    申请日：1979-06-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BRAMWELL F

    IPC: F16C11/04

    Abstract: The pivotal joint has a member(12) with a wheel-shaped end(18) pivoted to a second member(14) having a forked end(22) enveloping the wheel end(18). It includes a primary pivot bolt arrangement(30) extending through the members at the center of the wheel end(18) to pivotally join the parts. The forked end presents a circumferential array of three friction surfaces (24, 26, 28) which will cooperate with the periphery (20) of the wheel end to pivotally join the two parts(12, 14) as a secondary pivotal connection between them if the first pivot connection fails.

    FLIGHT CONTROL SYSTEM
    26.
    发明授权
    FLIGHT CONTROL SYSTEM 失效

    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.

    VARIABLE INCIDENCE HELICOPTER STABILATOR AND FAIL SAFE ACTUATOR
    27.
    发明授权
    VARIABLE INCIDENCE HELICOPTER STABILATOR AND FAIL SAFE ACTUATOR 失效

    公开(公告)号：KR820001684B1

    公开(公告)日：1982-09-17

    申请号：KR780000600

    申请日：1978-03-08

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： JOHNSON RAYMOND G ,  COTTON LOU S ,  VERZELLA DAVID J

    IPC: B64C13/16

    Abstract: The helicopter stabilator(22), combining the functions of tail stabilizer and aircraft elevator, has its angle of incidence with respect to the helicopter controlled by a pair of reversibie actuators(30, 31) acting in series and controlled by a slosed-loop. The controls are disconnected when the actuators fail to track within a threshold disparity of either position or rate of change of position of each other. A test switch introduces an imbalance to test the fault circutry. The stabilator is biased to assume a miximum incidence position at low speeds, including hover.

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