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    COMBINED BEARING SUBUNIT FOR MAIN ROTORS OF UNMANNED FLYING VEHICLE
    12.
    发明专利
    COMBINED BEARING SUBUNIT FOR MAIN ROTORS OF UNMANNED FLYING VEHICLE 未知

    公开(公告)号：RU2113378C1

    公开(公告)日：1998-06-20

    申请号：RU95106358

    申请日：1993-06-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CYPON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FURNES KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

    IPC: B64C11/02 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/02 ,  F02B75/02

    Abstract: FIELD: aircraft manufacture; designing of combined bearing subunits for unmanned flying vehicles. SUBSTANCE: combined subunit includes upper or lower main rotors and bush embracing the respective shaft and coaxial with it; end portion of shaft and surface of bush embracing it are provided with many radial splines which are external splines for shaft and inner splines for bush; splines of shaft and bush are mutually alternating providing for engagement between shaft and bush for setting it in rotation. Main rotor shaft is provided with main and end cylindrical parts of different diameter: D1 and D2 with taper adapter portion formed between them at angle of inclination beta of surface relative to shaft axis. According to invention, each spline of bush has lower portion bevelled outside forming angle theta relative to axis of bush which is equal to angle beta of taper adapter portion of shaft of main rotor. Bush rests on taper adapter portion of respective shaft by its bevelled lower portions of splines. Distance D3 of such combined subunit between edges of splines of main rotor shaft may be equal to diameter Dl of its main portion in diametral plane. EFFECT: optimization of construction of subunit. 2 cl, 32 dwg.

    A flexbeam for a helicopter bearingless main rotor assembly
    13.
    发明专利
    A flexbeam for a helicopter bearingless main rotor assembly 未知

    公开(公告)号：AU7512294A

    公开(公告)日：1994-12-20

    申请号：AU7512294

    申请日：1994-05-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BYRNES FRANCIS E ,  KRAUSS TIMOTHY A ,  SCHMALING DAVID N

    IPC: B64C27/46 ,  B64C27/33 ,  B64C27/473

    Abstract: A flexbeam for a soft inplane bearingless main rotor assembly has six spanwise regions: a hub attachment region; a first tapered region; a second tapered region; a pitch region; a tapered outboard transition region; and a main rotor blade, torque tube attachment region. One described embodiment of the flexbeam is fabricated from continuous unidirectional fiberglass plies having a 0 DEG fiber orientation, unidirectional fiberglass plies of varying lengths having a 0 DEG fiber orientation, and graphite cross plies having +/-45 DEG fiber orientations. The pitch region is formed solely by the continuous fiberglass plies which define a rectangular cross section therefor. The second tapered region is formed solely by the continuous fiberglass plies and the fiberglass plies of varying lengths. The ends of the fiberglass plies terminate in a distributed arrangement in the second tapered region to define the taper thereof. The remaining regions of the flexbeam are formed by interleaved combinations of the continuous fiberglass plies, the fiberglass plies of varying length, and the graphite cross plies of varying length. Ends of the graphite cross plies terminate in a distributed arrangement in the first tapered region to partially define the taper thereof. Ends of the fiberglass plies and the graphite cross plies terminate in a distributed arrangement in the tapered outboard transition region to define the taper thereof. The distributed arrangements of ply endings cause kick loads in the flexbeam to be distributed relatively uniformly into the ply buildups.

    14.
    发明专利
    未知

    公开(公告)号：FR2572358A1

    公开(公告)日：1986-05-02

    申请号：FR8510757

    申请日：1985-07-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CARTER DONALD R ,  KRAUSS TIMOTHY A ,  SEDLAK MATTHEW

    IPC: B64C27/46 ,  B64C27/32 ,  B64C27/467 ,  B64C27/72 ,  B64C27/22 ,  B64C21/04

    Abstract: A circulation control aircraft rotor blade having a spanwise Coanda surface 16 and a plurality of spanwise extending flexible composite material panels 18 cooperating with the surface to define slots for the discharge of compressed air from within the blade with each panel having first flexure means 60 associated with screw adjustments 36 for establishing a slot opening preload and second flexure means 62 associated with screw adjustments 38 for establishing a slot maximum opening.

    TORSIONALLY COMPLIANT HELICOPTER ROTOR BLADE WITH IMPROVED STABILITY AND PERFORMANCE CHARACTERISTICS
    16.
    发明专利
    TORSIONALLY COMPLIANT HELICOPTER ROTOR BLADE WITH IMPROVED STABILITY AND PERFORMANCE CHARACTERISTICS 未知

    公开(公告)号：CA1078357A

    公开(公告)日：1980-05-27

    申请号：CA270512

    申请日：1977-01-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KRAUSS TIMOTHY A

    IPC: B64C27/46 ,  B64C27/467 ,  B64C27/44

    Abstract: TORSIONALLY COMPLIANT HELICOPTER ROTOR BLADE WITH IMPROVED STABILITY AND PERFORMANCE CHARACTERISTICS A torsionally compliant helicopter rotor blade with maximum blade torsional flexibility at the blade tip portion and so shaped at the blade root portion that the locus of shear centers and the locus of centers of lift are substantially coincident, and so shaped at the tip portion so that the locus of shear centers is selectively forward of the locus of centers of lift to establish an aerodynamic restoring moment in response to blade tip torsional excursions, thereby improving blade torsional stability.

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