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公开(公告)号：GB2164618A
公开(公告)日：1986-03-26
申请号：GB8521934
申请日：1985-09-04
Applicant: UNITED TECHNOLOGIES CORP
Inventor： REAVELY RICHARD T , SCHMALING DAVID N
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公开(公告)号：CA2223684A1
公开(公告)日：1996-12-12
申请号：CA2223684
申请日：1995-06-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHMALING DAVID N , BYRNES FRANCIS E
Abstract: A hybrid composite flexbeam (10) for a soft inplane bearingless main rotor assembly (100) has eight spanwise regions: a hub attachment region (12); a first tapered region (14); a second tapered region (16); an inboard transition region (18); a pitch region having a cruciform configuration (20); an outboard transition region (22); a tapered outboard transition region (24); and a main rotor blade, torque tube attachment region (26). The pitch region (20) is formed from unidirectional fiberglass plies, a 50/50 admixture of unidirectional fiberglass and graphite plies, and unidirectional graphite plies. Unidirectional fiberglass and graphite plies of varying lengths are interleaved in the second inboard tapered region (16). Fiberglass and graphite cross plies of varying lengths are interleaved in the first inboard tapered region (14). Fiberglass and graphite cross plies and unidirectional fiberglass plies of varying length are interleaved in the outboard tapered region (24). The distributed arrangement of ply endings cause kick loads (97) in the hybrid flexbeam (10) to be distributed across the ply buildups.
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公开(公告)号：DE68914567D1
公开(公告)日：1994-05-19
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：CA1325628C
公开(公告)日：1993-12-28
申请号：CA608604
申请日：1989-08-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , SCHMALING DAVID N
Abstract: Hybrid Helicopter Rotor Hub Retention Plate A hybrid metal composite rotor hub retention plate having high strength and reduced weight. The retention plate comprises a metallic perimeter support structure and a plurality of metallic spokes that extend inwardly from the perimeter structure to a hub. The perimeter structure, hub and spokes define at least three holes. The perimeter structure and spokes have upper and lower surfaces. fiber reinforced resin matrix composite capable of reacting to bending loads, in-plane shear and axial loads is bonded to the upper and lower surfaces. The hybrid metal composite rotor hub retention plate is made by forming the metal structure and using the metal structure as a mold for the fiber reinforced resin matrix composite.
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公开(公告)号：CA2052910A1
公开(公告)日：1992-04-24
申请号：CA2052910
申请日：1991-10-03
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHMALING DAVID N , BYRNES FRANCIS E
Abstract: An improved clevis joint capable of withstanding substantial pivotal motion between its joined members and loading along its axis. An improved clevis joint wherein the parts joined thereby are pivotally connected by two sets of elastomeric bearings which are free to rotate about the joint axis and which envelope and support a free floating centering pin from the joined members so that during motion between the joined members, said elastomeric bearing sets share the rotary motion due to the rotating of the connecting pin. S-4348 - 16
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Patent Agency Ranking
公开(公告)号：CA2042532A1
公开(公告)日：1991-12-01
申请号：CA2042532
申请日：1991-05-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BYRNES FRANCIS E , SCHMALING DAVID N
Abstract: A flexbeam helicopter rotor having an improved connection between the flexbeam and the hub of the con- necting pin variety but in which the high tensile fi- bers of the flexbeam do not wrap around the connecting pin, wherein the blade centrifugal loads and the blade lead-lag loads axe reacted by the connecting pin at a station where it passes through drilled holes in the flexbeam inner end, and wherein the blade flapping mo- tion 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 and the hub connecting flanges, and the second load path being created by the differential bending reaction between the flexbeam at the station of the drilled holes and the connecting bolts. Further, there are means 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 from each other to thereby permit the use of a minimum thickness flexbeam, 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 ef- fecting offset, or flapping axis, from the prior art type of connection.
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公开(公告)号：AU602403B2
公开(公告)日：1990-10-11
申请号：AU1607388
申请日：1988-05-10
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHMALING DAVID N
Abstract: The two-step composite joint has improved strength to withstand both axial and bending loads and comprises two articles (3;6) each comprising a filler layer (15; 30) disposed between first and second composite layers (12,18;24,27). An end section (39) of the first article's first composite layer (12) is disposed external to, overlapping and bonded to an end section (42) of the second article's first composite layer (24) to form a first overlap (45). An end section (54) of the second article's second composite layer (27) is disposed internal to, overlapping and bonded to an end section (51) of the first article's second composite layer (18) to form a second overlap (57). The first overlap (45) is displaced across the thickness and along the length of the joint (9) from the second overlap (57). Loads are transferred across the joint (9) from first layer (12) to first layer (24) and from second layer (18) to second layer (27).
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公开(公告)号：IT1185707B
公开(公告)日：1987-11-12
申请号：IT2211785
申请日：1985-09-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： REAVELY RICHARD T , SCHMALING DAVID N
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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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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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