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    1.
    发明专利
    未知

    公开(公告)号：IT1197788B

    公开(公告)日：1988-12-06

    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.

    2.
    发明专利
    未知

    公开(公告)号：DE3629758C2

    公开(公告)日：1995-07-20

    申请号：DE3629758

    申请日：1986-09-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MATUSKA DAVID G

    IPC: B29C70/16 ,  B29C53/56 ,  B29C53/60 ,  B29C70/06 ,  B29C70/34 ,  B29D99/00 ,  B29K105/08 ,  B29L31/08 ,  B32B1/00 ,  B64C27/32 ,  B64C27/48 ,  F16D3/72 ,  B29C70/32

    Abstract: A filament wound fiber reinforced resin matrix composite structure. The structure is particularly adapted for use as a torque drive diaphragm in a rotary wing aircraft hub. The structure comprises a substantially flat diaphragm, a rim, rim reinforcement fibers and at least one fiber reinforcement ring. The diaphragm has a central attachment means for receiving a shaft and the rim has an attachment means. An alternative embodiment of the structure is a hollow disc having first and second substantially flat diaphragm sides with a connecting rim, rim reinforcement fibers and at least one fiber reinforcing ring for each diaphragm side. The sides have centrally located attachment means. The structure comprises a resin matrix, fibers wound substantially tangentially to the central attachment means with sufficient tension in a multiple circuit pattern to form the structure, fibers wound with sufficient tension in an essentially circumferential manner to reinforce the rim of the structure and fibers wound substantially circularly to form rings for reinforcing the diaphragm. The structure is cured by molding with sufficient heat and temperature in a controlled cure cycle. The structure does not exhibit "oil-canning" in that the flat diaphragm or diaphragm sides do not displace from the substantially flat uniplanar mode when subjected to varying temperatures. In addition, the structure does not buckle under heavy torque loading. The spring characteristics of the structure when constrained as a torque drive remain approximately linear and buckling and snap-through are eliminated during operation.

    3.
    发明专利
    未知

    公开(公告)号：FR2587938A1

    公开(公告)日：1987-04-03

    申请号：FR8613609

    申请日：1986-09-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MATUSKA DAVID G

    IPC: B29C70/16 ,  B29C53/56 ,  B29C53/60 ,  B29C70/06 ,  B29C70/34 ,  B29D99/00 ,  B29K105/08 ,  B29L31/08 ,  B32B1/00 ,  B64C27/32 ,  B64C27/48 ,  F16D3/72 ,  B32B17/06 ,  B32B31/20 ,  B64C27/58

    Abstract: A filament wound fiber reinforced resin matrix composite structure. The structure is particularly adapted for use as a torque drive diaphragm in a rotary wing aircraft hub. The structure comprises a substantially flat diaphragm, a rim, rim reinforcement fibers and at least one fiber reinforcement ring. The diaphragm has a central attachment means for receiving a shaft and the rim has an attachment means. An alternative embodiment of the structure is a hollow disc having first and second substantially flat diaphragm sides with a connecting rim, rim reinforcement fibers and at least one fiber reinforcing ring for each diaphragm side. The sides have centrally located attachment means. The structure comprises a resin matrix, fibers wound substantially tangentially to the central attachment means with sufficient tension in a multiple circuit pattern to form the structure, fibers wound with sufficient tension in an essentially circumferential manner to reinforce the rim of the structure and fibers wound substantially circularly to form rings for reinforcing the diaphragm. The structure is cured by molding with sufficient heat and temperature in a controlled cure cycle. The structure does not exhibit "oil-canning" in that the flat diaphragm or diaphragm sides do not displace from the substantially flat uniplanar mode when subjected to varying temperatures. In addition, the structure does not buckle under heavy torque loading. The spring characteristics of the structure when constrained as a torque drive remain approximately linear and buckling and snap-through are eliminated during operation.

    4.
    发明专利
    未知

    公开(公告)号：DE3624219A1

    公开(公告)日：1987-02-05

    申请号：DE3624219

    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.

    FILAMENT WOUND STRUCTURE FOR USE AS A TORQUE DRIVE
    7.
    发明专利
    FILAMENT WOUND STRUCTURE FOR USE AS A TORQUE DRIVE 未知

    公开(公告)号：GB2181107A

    公开(公告)日：1987-04-15

    申请号：GB8621191

    申请日：1986-09-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MATUSKA DAVID G

    IPC: B29C70/16 ,  B29C53/56 ,  B29C53/60 ,  B29C70/06 ,  B29C70/34 ,  B29D99/00 ,  B29K105/08 ,  B29L31/08 ,  B32B1/00 ,  B64C27/32 ,  B64C27/48 ,  F16D3/72 ,  B65H81/02 ,  F16D3/78 ,  B64C27/14

    Abstract: A filament wound fiber reinforced resin matrix composite structure. The structure is particularly adapted for use as a torque drive diaphragm in a rotary wing aircraft hub. The structure comprises a substantially flat diaphragm, a rim, rim reinforcement fibers and at least one fiber reinforcement ring. The diaphragm has a central attachment means for receiving a shaft and the rim has an attachment means. An alternative embodiment of the structure is a hollow disc having first and second substantially flat diaphragm sides with a connecting rim, rim reinforcement fibers and at least one fiber reinforcing ring for each diaphragm side. The sides have centrally located attachment means. The structure comprises a resin matrix, fibers wound substantially tangentially to the central attachment means with sufficient tension in a multiple circuit pattern to form the structure, fibers wound with sufficient tension in an essentially circumferential manner to reinforce the rim of the structure and fibers wound substantially circularly to form rings for reinforcing the diaphragm. The structure is cured by molding with sufficient heat and temperature in a controlled cure cycle. The structure does not exhibit "oil-canning" in that the flat diaphragm or diaphragm sides do not displace from the substantially flat uniplanar mode when subjected to varying temperatures. In addition, the structure does not buckle under heavy torque loading. The spring characteristics of the structure when constrained as a torque drive remain approximately linear and buckling and snap-through are eliminated during operation.

    8.
    发明专利
    未知

    公开(公告)号：DE3629758A1

    公开(公告)日：1987-04-09

    申请号：DE3629758

    申请日：1986-09-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MATUSKA DAVID G

    IPC: B29C70/16 ,  B29C53/56 ,  B29C53/60 ,  B29C70/06 ,  B29C70/34 ,  B29D99/00 ,  B29K105/08 ,  B29L31/08 ,  B32B1/00 ,  B64C27/32 ,  B64C27/48 ,  F16D3/72 ,  B29C67/14

    Abstract: A filament wound fiber reinforced resin matrix composite structure. The structure is particularly adapted for use as a torque drive diaphragm in a rotary wing aircraft hub. The structure comprises a substantially flat diaphragm, a rim, rim reinforcement fibers and at least one fiber reinforcement ring. The diaphragm has a central attachment means for receiving a shaft and the rim has an attachment means. An alternative embodiment of the structure is a hollow disc having first and second substantially flat diaphragm sides with a connecting rim, rim reinforcement fibers and at least one fiber reinforcing ring for each diaphragm side. The sides have centrally located attachment means. The structure comprises a resin matrix, fibers wound substantially tangentially to the central attachment means with sufficient tension in a multiple circuit pattern to form the structure, fibers wound with sufficient tension in an essentially circumferential manner to reinforce the rim of the structure and fibers wound substantially circularly to form rings for reinforcing the diaphragm. The structure is cured by molding with sufficient heat and temperature in a controlled cure cycle. The structure does not exhibit "oil-canning" in that the flat diaphragm or diaphragm sides do not displace from the substantially flat uniplanar mode when subjected to varying temperatures. In addition, the structure does not buckle under heavy torque loading. The spring characteristics of the structure when constrained as a torque drive remain approximately linear and buckling and snap-through are eliminated during operation.

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