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    COMPOSITE HELICOPTER SWASHPLATE
    31.
    发明专利
    COMPOSITE HELICOPTER SWASHPLATE 未知

    公开(公告)号：CA1320708C

    公开(公告)日：1993-07-27

    申请号：CA571525

    申请日：1988-07-08

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FERRIS DONALD L ,  BYRNES FRANCIS E ,  VARHOLAK LAWRENCE N JR

    IPC: B64C27/605 ,  B64C27/32

    Abstract: Composite Helicopter Swashplate A helicopter composite swashplate ring that has a triaxial braided tubular ring that withstands both forces in-plane and normal to the plane of the swashplate. The triaxial braided tubular ring comprises substantially circumferential fibers interwoven with angled fibers oriented at a predetermined angle to the circumferential fibers. The tubular ring contains a composite circumferential spacer ring that comprises an upper ring plate connected to a lower ring plate by a plurality of first tubular support members. The upper ring plate and lower ring plate are adjacent the inside upper and insider lower surfaces of the tubular ring, respectively. The upper and lower plates have openings in alignment with the first tubular support members. The ring plates have a plurality of sections extending radially outward. the sections have lug openings that are in alignment with a plurality of second vertical support members to form channels therethrough for accepting servo or control rod lugs.

    32.
    发明专利
    未知

    公开(公告)号：DE3878084D1

    公开(公告)日：1993-03-18

    申请号：DE3878084

    申请日：1988-07-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FERRIS DONALD L ,  BYRNES FRANCIS E ,  VARHOLAK LAWRENCE N

    IPC: B64C27/605 ,  B64C27/32

    Abstract: The helicopter composite swashplate ring (3) has a triaxial braided tubular ring (9) that withstands both forces in-plane and normal to the plane of the swashplate. The triaxial braided tubular ring (9) comprises substantially circumferential fibers interwoven with angled fibers oriented at a predetermined angle to the circumferential fibers. The tubular ring (9) contains a composite circumferential spacer ring (6) that comprises an upper ring plate (12) connected to a lower ring plate (15) by a plurality of first tubular support members (18) The upper ring plate (12) and lower ring plate (15) are adjacent the inside upper and insider lower surfaces of the tubular ring (9), respectively. The upper and lower plates (12,15) have openings (21) in alignment with the first tubular support members (18). The ring plates (12, 15) have a plurality of sections (27) extending radially outward. The sections (27) have lug openings (30) that are in alignment with a plurality of second vertical support members (33) to form channels therethrough for accepting servo or control rod lugs.

    33.
    发明专利
    未知

    公开(公告)号：FR2585327B1

    公开(公告)日：1988-01-15

    申请号：FR8610413

    申请日：1986-07-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FERRIS DONALD L ,  MATUSKA DAVID G

    IPC: B64C27/35 ,  B64C27/51

    Abstract: Apparatus for damping blade lead/lag motion on a hingeless helicopter rotor assembly, including a hub, blades and flexbeam(s) interposed between the root end of the blades and the hub. Rigid, radial links extend the length of the flexbeams for attachment to the outboard ends thereof. Lead/lag motion at the outboard end of the flexbeam causes flexbeam bending, which is converted to radial translation of the links. This radial translation of the links and likewise the blade lead/lag motion is damped by damper means connected between the inboard ends of the links and the hub.

    34.
    发明专利
    未知

    公开(公告)号：FR2585327A1

    公开(公告)日：1987-01-30

    申请号：FR8610413

    申请日：1986-07-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FERRIS DONALD L ,  MATUSKA DAVID G

    IPC: B64C27/35 ,  B64C27/51

    Abstract: Apparatus for damping blade lead/lag motion on a hingeless helicopter rotor assembly, including a hub, blades and flexbeam(s) interposed between the root end of the blades and the hub. Rigid, radial links extend the length of the flexbeams for attachment to the outboard ends thereof. Lead/lag motion at the outboard end of the flexbeam causes flexbeam bending, which is converted to radial translation of the links. This radial translation of the links and likewise the blade lead/lag motion is damped by damper means connected between the inboard ends of the links and the hub.

    36.
    发明专利
    未知

    公开(公告)号：IT8621189D0

    公开(公告)日：1986-07-21

    申请号：IT2118986

    申请日：1986-07-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FERRIS DONALD L ,  MATUSKA DAVID G

    IPC: B64C27/35 ,  B64C27/51 ,  B64D

    Abstract: Apparatus for damping blade lead/lag motion on a hingeless helicopter rotor assembly, including a hub, blades and flexbeam(s) interposed between the root end of the blades and the hub. Rigid, radial links extend the length of the flexbeams for attachment to the outboard ends thereof. Lead/lag motion at the outboard end of the flexbeam causes flexbeam bending, which is converted to radial translation of the links. This radial translation of the links and likewise the blade lead/lag motion is damped by damper means connected between the inboard ends of the links and the hub.

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