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公开(公告)号：CA2203012A1
公开(公告)日：1996-04-25
申请号：CA2203012
申请日：1995-10-10
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , SCHMALING DAVID N , MINER FREDERICK J
Abstract: A mounting assembly (100) is provided for securing a helicopter snubber bearing (70) to a bearingless rotor assembly (10) which includes a flexbeam connector (22) mounted to a torque drive hub member (18). The mounting assembly (100) includes a retainer fixture (102) for mounting a retainer (104) which engages an inner bearing race portion (88) of the snubber bearing (70). The retainer fixture (102) is mounted to the flexbeam connector (22) and includes an inboard end portion (112), a restraint portion (114) extending radially outboard thereof, and a seat portion (116) disposed therebetween. The retainer (104) is disposed in register with, and is compliantly bonded to, the seat portion (116) of the retainer fixture (102), and furthermore abuts the restraint portion (114) which provides redundant retention therefor. Furthermore, the seat portion (116) of the retainer fixture (102) is reduced in width dimension to reduce flap and pitch induced shear stresses.
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公开(公告)号：DE68914567T2
公开(公告)日：1994-07-21
申请号：DE68914567
申请日：1989-09-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , SCHMALING DAVID N
Abstract: A hybrid metal composite rotor hub retention plate (1) having high strength and reduced weight. The retention plate (1) comprises a metallic perimeter support structure (4) and a plurality of metallic spokes (9) that extend inwardly from the perimeter structure (4) to a hub (12). The perimeter structure (4), hub (12) and spokes (9)define at least three holes(13). The perimeter structure (4) and spokes (9) have upper and lower surfaces (15, 18). Fiber reinforced resin matrix composite (6) capable of reacting to bending loads, in-plane shear and axial loads is bonded to the upper and lower surfaces (15,18). The hybrid metal composite rotor hub retention plate (1) is made by forming the metal structure (4) and using the metal stucture (4) as a mold for the fiber reinforced resin matrix composite (6).
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公开(公告)号：DE3878084T2
公开(公告)日：1993-05-19
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：IT1185049B
公开(公告)日：1987-10-28
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：DE3465452D1
公开(公告)日：1987-09-24
申请号：DE3465452
申请日：1984-03-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： WEHNERT GEORGE JOSEPH , BYRNES FRANCIS E , OGLE PETER CHASE
Abstract: A helicopter hub main retention plate is described made up of graphite and glass fiber reinforced epoxy resin. The graphite fiber reinforcement is in-plane isotropically laid continuous graphite fibers and the glass fiber reinforcement comprises segments of fiberglass continuously and circumferentially wound round the areas of retention. Such materials and configuration provide crack resistance, damage tolerance, and integrity inspectability to the retention plate.
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Patent Agency Ranking
公开(公告)号：DE3521877A1
公开(公告)日：1986-01-02
申请号：DE3521877
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：AU4127996A
公开(公告)日：1996-12-24
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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公开(公告)号：ES2089568T3
公开(公告)日：1996-10-01
申请号：ES92920438
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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公开(公告)号：DE3521877C2
公开(公告)日：1996-07-11
申请号：DE3521877
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：DE69115565T2
公开(公告)日：1996-05-02
申请号：DE69115565
申请日：1991-05-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , SCHAMLING DAVID N
Abstract: The flexbeam helicopter rotor has an improved connection between the flexbeam (20) and the hub (12) of the connecting pin variety but in which the high tensile fibers of the flexbeam (20) do not wrap around the connecting pin (22), wherein the blade centrifugal loads and the blade lead-lag loads are reacted by the connecting pin (22) at a station where it passes through drilled holes (58) in the flexbeam inner end, and wherein the blade flapping motion imposed loads are reacted through two load paths in the flexbeam-to-hub connection, the first load path being created by a prying reaction between the flexbeam (20) and the hub connecting flanges (16, 18), and the second load path being created by the differential bending reaction between the flexbeam (20) at the station of the drilled holes (58) and the connecting pins (22). Further, there are means (42, 44) to decouple the loads and decrease the maximum load in at least one of the load paths created by the aforementioned prying reaction and the aforementioned bending reaction so that they are substantially spaced along the flexbeam axis of rotation (34) from each other to thereby permit the use of a minimum thickness flexbeam (20), and gain the attended advantage of reduced rotor weight and size, and which flexbeam-to-hub connection has the additional advantage of a reduced flapping hinge effecting offset, or flapping axis, from the prior art type of connection.
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