| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Rotorcraft rotor fitted with lead-lag dampers housed in sleeves connecting blades to a hub of the rotor | US13937660 | 2013-07-09 | US09284051B2 | 2016-03-15 | Andre Amari; Jacques Gaffiero |
| A rotorcraft rotor fitted with a device for damping lead-lag oscillations of the blades (2) of the rotor. The blades (2) are hinge-mounted on a rotary hub (1) of the rotor via respective sleeves (3). The damper device comprises a set of dampers (6), each individually housed in a respective one of said sleeves (3) and deformable between two fastening points (8, 9), one with the sleeve and the other with an engagement member (7) for engaging the hub (1) via a linkage (10). For each of the sleeve (3), the damper (6) housed by a given sleeve (3) is in hinged engagement with the linkage (10) via a lever arm (11) hinged to the sleeve (3). | ||||||
| 122 | ROTOR BLADE COUPLING DEVICE OF A ROTOR HEAD FOR A ROTARY-WING AIRCRAFT | US14837386 | 2015-08-27 | US20160059959A1 | 2016-03-03 | Martin STUCKI; Mario CAMINADA; Patrick Reginald MOSER |
| In a rotor blade coupling device for coupling with a rotor mast so as to create a rotor head of a rotary-wing aircraft, in particular a gyroplane or a helicopter, encompassing a rotor head central piece, at least two rotor blade holders fastened to the rotor head central piece for accommodating at least two rotor blades lying in a rotor plane, as well as at least one joining means between adjacent rotor blade holders, a simplified structural design is to be achieved for the rotor blade coupling device, and the rotor blade coupling device is to enable an agile control. This is achieved by virtue that the rotor blade coupling device as the joining means encompasses at least one closed ring. The ring is arranged so as to cross all rotor blade holders at least at one respective joining location, and at least indirectly join together all rotor blade holders. | ||||||
| 123 | VIBRATION ABSORBING DEVICE FOR FLEXBEAMS | US14844873 | 2015-09-03 | US20160052648A1 | 2016-02-25 | Joshua Mancher; Lewis L. Kristie; Marcus D. Cappelli |
| A replacement vibration absorbing device for replacing a wear wrap on a flexbeam includes a sleeve having a plurality of layers of vibration absorbing material, wherein an edge of the sleeve is cut so that the sleeve may be installed around a generally central portion of a flexbeam. | ||||||
| 124 | System and method of harvesting power with a rotor hub damper | US13358046 | 2012-01-25 | US09260185B2 | 2016-02-16 | Charles Eric Covington; Mithat Yuce; David A. Popelka; Frank B. Stamps |
| The system and method of the present application relate to a lead/lag damper for a rotorcraft. The lead/lag damper is configured to harvest power from the lead/lag oscillatory motions of rotor blades with an electromagnetic linear motor/generator. Further, the lead/lag damper is configured to treat the lead/lag motions with the electromagnetic linear motor/generator. The system and method is well suited for use in the field of aircraft, in particular, helicopters and other rotary wing aircraft. | ||||||
| 125 | Temperature adaptive fluid damping system | US13697029 | 2011-02-24 | US09188190B2 | 2015-11-17 | Jeffrey Bosworth; Frank B. Stamps |
| A temperature adaptive fluid damping system is provided. One embodiment of the temperature adaptive fluid damping system comprises two fluid chambers, a piston in fluid communication with the fluid chambers, and a fluid path between the fluid chambers. An elastomeric retaining element adjacent to the fluid path is constrained to deform substantially perpendicular to the fluid path, so that the retaining element is operable to vary the cross-sectional area of the fluid path inversely to a change in temperature. | ||||||
| 126 | Rotor damper and tail rotor with such a rotor damper | US13375964 | 2009-06-02 | US09073636B2 | 2015-07-07 | Per-Erik Cardell; Tommy Johansson; Johan Lindroth; Kjell Stenbom |
| A rotor damper for a tail rotor of a helicopter. A main body of a resilient material is to be arranged between a drive shaft for the tail rotor and a hub on which rotor blades for the tail rotor are coupled. A flange is connected to the main body of the rotor damper. The flange includes an abutment surface for abutting an outer surface of the hub. A tail rotor including the rotor damper. | ||||||
| 127 | MOTION CONTROLLED HELICOPTER AND ROTATION RATE SWITCHED FLUID LEAD LAG DAMPER | US14389847 | 2013-04-05 | US20150093245A1 | 2015-04-02 | Zachary Fuhrer; Mark Jolly; Conor M. Marr |
| A method for controlling helicopter ground resonance and air resonance motions as well as centrifugal force switching dampers are disclosed. A helicopter lead-lag damper (30) has a first ground resonance motion damping rate stage (FDR) and a second air resonance motion damping rate stage (SDR). The damper (30) includes a centrifugal force switch (52). The damper (30) is oriented relative to the rotary wing rotation axis (26) and helicopter blade (24). An in-flight rotation rate of the centrifugal force switching damper (30) actuates the centrifugal force switch (52) with the damper switching from the first ground resonance motion damping rate stage (FDR) to the second air resonance motion damping rate stage (SDR). | ||||||
| 128 | RETRACTABLE COMPOSITE ROTOR BLADE ASSEMBLY | US14506595 | 2014-10-03 | US20150086365A1 | 2015-03-26 | ESTEBAN A. CARABALLOSO |
| A retractable rotor blade assembly includes a rotor hub assembly having a rotor hub wall, a pitch disc mounted to the rotor hub wall for undergoing rotation about a longitudinal axis, and retractable rotor blades configured to be extended and retracted relative to the rotor hub assembly. Each of the rotor blades has an interlink assembly, a blade base, and a damper for dampening movement of the interlink assembly during extension and retraction of the rotor blade. The interlink assembly includes a plurality of interconnected link base subassemblies each configured to be translated along a span of the rotor blade such that each subsequent link base subassembly becomes stacked one atop the other while remaining connected to a next link base subassembly. The blade base is interconnected between the pitch disc of the rotor hub assembly and one of the interconnected link base subassemblies. | ||||||
| 129 | Dual spring rate damper | US13461414 | 2012-05-01 | US08857581B2 | 2014-10-14 | Frank B. Stamps; Michael R. Smith; Christopher M. Bothwell; Lawrence M. Corso; James L. Braswell, Jr.; David A. Popelka; Ernst C. Schellhase; Charles L. Hollimon; Thomas J. Newman; Bryan Baskin; Thomas C. Campbell; Daniel B. Robertson |
| A rotor hub and method to dampen a force exerted on a rotor hub by a rotor blade during flight. The rotor hub including a central member rotatably coupled to a rotor mast, a blade grip rigidly attached to a blade and movably coupled to the central member, and an adjustable damper operably associated with the blade grip. The method includes damping the force exerted on the rotor hub with the adjustable damper and selectively adjusting the adjustable damper between a first spring rate and a second spring rate. | ||||||
| 130 | System and Method for Linkage Length Adjustment | US14136814 | 2013-12-20 | US20140178199A1 | 2014-06-26 | Mark A. Wiinikka |
| A rotor system has a rotor, an axis of rotation about which the rotor may be rotated, a linkage system having a first adjustable length portion and a second adjustable length portion, wherein the second adjustable length portion is configured to provide a relatively finer adjustment of an overall effective length of the linkage system as compared to the first adjustable length portion and wherein the rotor is configured to rotate about the axis in response to changing the overall effective length of the linkage system. | ||||||
| 131 | MAGNETORHEOLOGICAL FLUID ELASTIC LAG DAMPER FOR HELICOPTER ROTORS | US13630421 | 2012-09-28 | US20140090937A1 | 2014-04-03 | Norman Mark Wereley; Wei Hu; Curt Steven Kothera; Peter Che-Hung Chen |
| A MagnetoRheological Fluid Elastic (MRFE) lag damper system for adaptive lead-lag damping of helicopter main rotors. Embodiments include snubber dampers especially for hingeless helicopter rotors, and concentric bearing dampers. The snubber lag dampers include a flexible snubber body defining a cavity, a flexible or rigid interior (e.g., center) wall subdividing the cavity, and a flow valve in the interior wall or external to the cavity. The flexible snubber body may comprise elastomeric materials and metal rings stacked together to create a sealed MR fluid cavity. The shear deformation of the snubber body induces MR fluid flow through the valve, controlled by a magnetic field in the valve. An MRFE concentric bearing damper is also disclosed, comprising a pair of concentric tubes with elastomeric material injected and cured in an annular gap between the two tubes, and an MR fluid reservoir with piston-mounted MR valve housed inside the innermost tube. | ||||||
| 132 | Dual frequency damper for an aircraft | US13421991 | 2012-03-16 | US08622375B2 | 2014-01-07 | Jeffrey Bosworth; Mithat Yuce; Frank B. Stamps; Michael R. Smith |
| A dual frequency damper includes a liquid inertia vibration eliminator (LIVE) portion and a fluid damper portion. LIVE portion and fluid damper portion operate in series and function so that dual frequency damper is optimized in both stiffness and damping at multiple frequencies. LIVE portion acts as a frequency dependent switch to selectively cause low frequency oscillatory forces to be treated primarily by the high spring rate and high damping rate characteristics of the fluid damper portion, and also to select high frequency oscillatory forces to be primarily treated by the low spring rate and low damping rate characteristics of the LIVE unit portion. | ||||||
| 133 | DEVICE FOR MONITORING THE FLAPPING AND/OR LAG BEHAVIOR OF A BLADE OF A ROTORCRAFT ROTOR | US13792807 | 2013-03-11 | US20130243597A1 | 2013-09-19 | Christophe Perrin; Nicolas Imbert; Charles Chuc |
| The present invention relates to a rotorcraft rotor (1) having a plurality of blades (3) movably mounted on a hub (2) via blade roots (4) that are respectively associated therewith. The rotor (1) is fitted with an information capture appliance having at least one measurement assembly (E1) comprising a flexible bar (11) interposed in engagement at its respective ends between the hub (2) and a blade root (4) that is allocated thereto. A strain gauge (7, 8) formed of a SAW transducer is implanted on the bar (11) and generates information relative to the bending of the bar (11) following tilting orientations of the blade root (4) in flapping (B) and/or in lag (T). | ||||||
| 134 | VIBRATION ABSORBING DEVICE FOR FLEXBEAMS | US13408248 | 2012-02-29 | US20130224507A1 | 2013-08-29 | Joshua Mancher; Lewis L. Kristie; Marcus D. Cappelli |
| A replacement vibration absorbing device for replacing a wear wrap on a flexbeam includes a sleeve having a plurality of layers of vibration absorbing material, wherein an edge of the sleeve is cut so that the sleeve may be installed around a generally central portion of a flexbeam. | ||||||
| 135 | System and Method of Harvesting Power with a Rotor Hub Damper | US13358046 | 2012-01-25 | US20130189098A1 | 2013-07-25 | Charles Eric Covington; Mithat Yuce; David A. Popelka; Frank B. Stamps |
| The system and method of the present application relate to a lead/lag damper for a rotorcraft. The lead/lag damper is configured to harvest power from the lead/lag oscillatory motions of rotor blades with an electromagnetic linear motor/generator. Further, the lead/lag damper is configured to treat the lead/lag motions with the electromagnetic linear motor/generator. The system and method is well suited for use in the field of aircraft, in particular, helicopters and other rotary wing aircraft. | ||||||
| 136 | Magnetorheological fluid elastic lag damper for helicopter rotors | US12378275 | 2009-02-12 | US08413772B2 | 2013-04-09 | Norman Mark Wereley; Wei Hu; Curt Steven Kothera; Peter Che-Hung Chen; Grum Tamrat Ngatu |
| A MagnetoRheological Fluid Elastic (MRFE) lag damper system for adaptive lead-lag damping of helicopter main rotors. Embodiments include snubber dampers especially for hingeless helicopter rotors, and concentric bearing dampers. The snubber lag dampers include a flexible snubber body defining a cavity, a flexible or rigid interior (e.g., center) wall subdividing the cavity, and a flow valve in the interior wall or external to the cavity. The flexible snubber body may comprise elastomeric materials and metal rings stacked together to create a sealed MR fluid cavity. The shear deformation of the snubber body induces MR fluid flow through the valve, controlled by a magnetic field in the valve. An MRFE concentric bearing damper is also disclosed, comprising a pair of concentric tubes with elastomeric material injected and cured in an annular gap between the two tubes, and an MR fluid reservoir with piston-mounted MR valve housed inside the innermost tube. | ||||||
| 137 | Rotary wing aircraft rotary lead lag damper | US11754673 | 2007-05-29 | US08356977B2 | 2013-01-22 | Peter J. Jones; Zachary Fuhrer |
| The rotary damper for controlling helicopter motions includes an outer canister with an inner paddle wheel receiving cavity which receives an inner paddle wheel with upper and lower elastomeric tubular intermediate members between the inner paddle wheel and the outer canister. The canister and inner paddle wheel form neighboring variable volume chambers in liquid communication through liquid damping conduits. A clockwise rotation of the inner paddle wheel about the center of rotation axis relative to the outer canister pumps damper liquid from a second variable volume chamber through a first liquid conduit towards a first variable volume chamber, and a counterclockwise rotation of the paddle wheel relative to the outer canister pumps the damper liquid from the first variable volume chamber through the first liquid conduit towards the second variable volume chamber with the elastomeric tubular intermediate members providing for the relative rotation and containing the damper liquid in the damper. | ||||||
| 138 | ROTOR DAMPER DEVICE, AND AN ASSOCIATED ROTOR AND AIRCRAFT | US13440143 | 2012-04-05 | US20120269630A1 | 2012-10-25 | Elio Zoppitelli; Etienne Rampal |
| A damper device (10) for a rotor (2) having a rotary ring (11) and a plurality of levers (12), each lever (12) extending from a first end (12′) connected to said ring (11) by a first mechanical connection (20) to a second end (12″) suitable for being hinged to a blade (4). The damper device (10) includes non-rotary damper means (30) secured to non-rotary fastener means (40) and to a non-rotary member (51) of an interface (50), said interface (50) being interposed between said non-rotary damper means (30) and said ring (11) to convert a rotary movement of a blade (4) transmitted to a lever (12) into a movement in translation acting on said damper means (30). | ||||||
| 139 | Dual Spring Rate Damper | US13461414 | 2012-05-01 | US20120230823A1 | 2012-09-13 | Frank B. Stamps; Michael R. Smith; Christopher M. Bothwell; Lawrence M. Corso; James L. Braswell, JR.; David A. Popelka; Ernst C. Schellhase; Charles L. Hollimon; Thomas J. Newman; Bryan Baskin; Thomas C. Campbell; Daniel B. Robertson |
| A rotor hub and method to dampen a force exerted on a rotor hub by a rotor blade during flight. The rotor hub including a central member rotatably coupled to a rotor mast, a blade grip rigidly attached to a blade and movably coupled to the central member, and an adjustable damper operably associated with the blade grip. The method includes damping the force exerted on the rotor hub with the adjustable damper and selectively adjusting the adjustable damper between a first spring rate and a second spring rate. | ||||||
| 140 | LEAD-LAG DAMPER DEVICE | US13357897 | 2012-01-25 | US20120195760A1 | 2012-08-02 | Cédric Lopez; Benjamin Talon |
| Damper device for damping relative movements of two elements of a mechanical system. The damper device comprises a damping chamber filled with a hydraulic fluid, a rod (4) having a piston (3) movable in the damping chamber so as to define two hydraulic compartments (1, 2), at least one calibrated orifice (10) provided in the piston (3) for throttling the hydraulic fluid flowing from one hydraulic compartment (1, 2) to another hydraulic compartment, at least one compression peak-limiting valve (11) and a traction peak-limiting valve (12), throttling the hydraulic fluid flowing from one hydraulic compartment (1, 2) to another hydraulic compartment. The damper has additional hydraulic means that are active in compression and in traction when the piston (3) reaches the end of its stroke, so as to constitute a progressive hydraulic abutment damping the end-of-stroke jolts. | ||||||
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