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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.
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公开(公告)号：DE69103244T2
公开(公告)日：1994-11-24
申请号：DE69103244
申请日：1991-10-10
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , KRAUSS ALBERT T , HIBYAN EDWARD S
IPC: B64C27/605
Abstract: The swashplate configuration eliminates the need for scissors linkages through the use of a centering member (24) capable of tilt and axial translation while driving torque to the rotating swashplate member through the use of elastomeric bearing assemblies each consisting of a first stack of flat laminates (34, 36) and a second stack of spherical laminates (38).
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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.
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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.
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公开(公告)号：CA2115166A1
公开(公告)日：1993-03-18
申请号：CA2115166
申请日：1992-08-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , CULLEN I LAWRENCE III
IPC: B64C27/48
Abstract: A composite torque tube for a bearingless main rotor (BMR) assembly that is optimally fabricated to meet torsional stiffness, fatigue strength, and buckling strength design constraints at minimal unit weight. The composite torque tube includes a strengthened inboard section for mechanically coupling the torque tube in combination with the hub structure of the BMR assembly, a strengthened outboard section for mechanically coupling the torque tube in combination with a corresponding main rotor blade, and an intermediate section that is operative to accommodate the pitch, flapwise, and/or edgewise loads acting on the BMR assembly during operation thereof. The intermediate section of the torque tube has a constant wall thickness and is formed from continuous filament windings having a predetermined fiber orientation within a broad range of about +/-18 DEG to about +/-40 DEG and/or a narrow range of about +/-26 DEG to about +/-35 DEG . The torque tube is preferably formed from continuous filament windings having an optimal fiber orientation of about +/-35 DEG to provide an intermediate section having a minimal torque tube wall thickness.
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Patent Agency Ranking
公开(公告)号：CA2036598A1
公开(公告)日：1991-10-07
申请号：CA2036598
申请日：1991-02-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , D ANNA FRANK P
Abstract: Flexbeam Helicopter Rotor With Improved Snubber-Vibration Damper Between the Torque Tube and the Flexible Spar Member A flexbeam helicopter rotor having an improved snubber-vibration damper for positioning the flexbeam spar relative to the torque tube, wherein the snubber-damper is an elastomeric bearing having a spherical and a flat portion, and whose laminates are continuous, selectively preloaded and of selected material to provide increased fatigue life, size reduction, reduced laminate stress concentration, and reduced critical design stress in the snubbervibration damper.
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公开(公告)号：DK276485A
公开(公告)日：1985-12-21
申请号：DK276485
申请日：1985-06-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , FERRIS DONALD L , HIBYAN EDWARD S , NOEHREN WILLIAM L , OGLE PETER C , OLSEN ERIC G
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公开(公告)号：IT8521200D0
公开(公告)日：1985-06-19
申请号：IT2120085
申请日：1985-06-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , FERRIS DONALD L , HIBYAN EDWARD S , NOEHREN WILLIAM L , OGLE PETER C , OLSEN ERIC G
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公开(公告)号：CA2149673C
公开(公告)日：1998-08-18
申请号：CA2149673
申请日：1993-10-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , CULLEN LAWRENCE I III
Abstract: A tubular elastomer damper (11) has a central shaft (12) disposed within a housing (13) and surrounded by an elastomer member (14). Uniform strain is provided across the elastomer disposed between the central shaft and the housing by either tapering the length of the elastomer from an inner bonding surface (15) to an outer bonding surface (16) such that the radius times the length at each point along the elastomer is equal or by providing a first elastomer layer (28) adjacent the shaft (26) having a high fatigue strain/lower damping ability, a second elastomer layer (29) adjacent the housing (27) having a low strain higher damping ability and intermediate elastomer layer (30) of moderate strain and damping therebetween such that from the inner to the outer radius of the elastomer member, uniform strain is achieved. B y providing uniform strain from the inner to the outer radius of the tubular elastomer damper,temperature increases due to localized hi gh strains are avoided which are detrimental to damper performance. Optionally, axial cooling passages are provided within the elastome r member to dissipate heat to assure operation within design parameters,thus extending the life of the tubular elastomer damper.
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公开(公告)号：AU686913B2
公开(公告)日：1998-02-12
申请号：AU4127996
申请日：1995-06-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHMALING DAVID N , BYRNES FRANCIS E
Abstract: A hybrid composite flexbeam for a soft inplane bearingless main rotor assembly has eight spanwise regions: a hub attachment region; a first tapered region; a second tapered region; an inboard transition region; a pitch region having a cruciform configuration; an outboard transition region; a tapered outboard transition region; and a main rotor blade, torque tube attachment region. The pitch region is formed from unidirectional fiberglass plies, a 50/50 admixture of unidirectional fiberglass and graphite plies, and unidirectional graphite plies, all of which extend from root to tip of the hybrid flexbeam. Unidirectional fiberglass and graphite plies of varying lengths are interleaved in the second inboard tapered region. Fiberglass and graphite cross plies of varying lengths are interleaved in the first inboard tapered region. Fiberglass and graphite cross plies and unidirectional fiberglass plies of varying length are interleaved in the outboard tapered region. The ends of the plies of varying length form distributed ply drop-off arrangements in the first and second inboard tapered regions and the outboard tapered regions. The distributed arrangement of ply endings cause kick loads in the hybrid flexbeam to be distributed across the ply buildups. Fiberglass edge caps having a U-shaped configuration may be disposed in combination with the leading and trailing edges of the hybrid flexbeam, starting at the limits of the pitch region and extending inboardly and outboardly therefrom, respectively.
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