| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | Damping device and aircraft rotor system incorporating it | US12398445 | 2009-03-05 | US08177202B2 | 2012-05-15 | Hervé Richer De Forges; Jean-Pierre Ciolczyk |
| The damping device is intended to form a drag-mode damper for a helicopter blade, and is incorporated in an aircraft rotor system. This damping device comprises: an external frame intended to be coupled to a first rotating element, and a radially internal element mounted coaxially to the frame and intended to be coupled to a second rotating element; at least one elastomer damper of annular cross section mounted fixedly to the frame and to the internal element; and a working chamber bounded by the frame and by the damper and communicating with a compensation chamber bounded by a highly deformable flexible member mounted coaxially to the internal element. The working chamber is formed at a first end of the device and communicates with the compensation chamber via a porous structure surmounting an end opening of the flexible member, which member is mounted in the internal element. | ||||||
| 142 | Helicopter aircraft vehicle rotor damper | US12203288 | 2008-09-03 | US08167561B2 | 2012-05-01 | Peter Jones |
| A helicopter rotor damper system including a torsional damper with a damper centering bearing providing a damper center of rotation axis, a first elastomeric torsional damper with a first elastomeric torsional damper torsional elastomer bonded between a first elastomeric torsional damper first torsional damper nonelastomeric bonding surface and a first elastomeric torsional damper second torsional damper nonelastomeric bonding surface, and a second elastomeric torsional damper with a second elastomeric torsional damper torsional elastomer bonded between a second elastomeric torsional damper first torsional damper nonelastomeric bonding surface and a second elastomeric torsional damper second torsional damper nonelastomeric bonding surface. The helicopter rotor damper system includes a damper link linked with the torsional damper, with the torsional damper and the damper link connected between a helicopter blade and a helicopter rotor with the elastomeric torsional damper nonelastomeric bonding surfaces relatively rotating. | ||||||
| 143 | System and method of damping a 1P motion | US12015149 | 2008-01-16 | US08038394B2 | 2011-10-18 | Brandon L. Stille; William A. Welsh; Timothy Fred Lauder |
| A rotor system includes a multiple of rotor blade yokes mounted to a rotor hub. A lead/lag damper is mounted to each of the rotor blade yokes and to a damper hub. An actuator system is operable to shift a damper hub axis of rotation relative the rotor axis of rotation to minimize 1P damper motions. A method of minimizing 1P damper motions within a rotor system includes shifting the damper hub axis of rotation relative the rotor axis of rotation to oscillate an inner connector of each lead/lag damper in phase with a 1P blade motion to minimize the 1P motion of the damper. | ||||||
| 144 | Lead-Lag Damper for Rotor Hubs | US12866920 | 2008-02-12 | US20110027083A1 | 2011-02-03 | Frank B. Stamps; James L. Braswell; David A. Haynie; Mithat Yuce |
| A lead-lag damper for a rotor assembly has a body mounted to either an inboard portion of a blade assembly or a fixed portion of the rotor assembly. A piston carried within the body is configured to allow for relative motion between the body and the piston. The piston defines opposing chambers within the body, the chambers being in fluid communication through a fluid passage. A link connects the piston to the other of the inboard portion of the blade assembly and the fixed portion of the rotor assembly, and the link engages a central portion of the piston. The piston acts on fluid in the chambers during relative motion between the piston and the body and causes fluid flow between the chambers through the fluid passage. Flow through the passage acts to damp lead-lag motion of the blade assembly relative to the fixed portion of the rotor assembly. | ||||||
| 145 | Elastomeric bearing with heatable shims | US11505725 | 2006-08-17 | US07686584B2 | 2010-03-30 | David N. Schmaling |
| An electrically heatable elastomeric bearing provides a multiple of elastomeric material layers and a multiple of shim layers. At least one of the multiple of shim layers includes an electrically heatable shim layer. | ||||||
| 146 | BLADE FOR REDUCING THE DRAG MOVEMENTS OF SAID BLADE, AND A METHOD OF REDUCING SUCH A DRAG MOVEMENT | US12490798 | 2009-06-24 | US20090324406A1 | 2009-12-31 | Thomas MANFREDOTTI; Paul CRANGA; Julien GUITTON |
| A blade (10) extending longitudinally from a root (11) of the blade (10) to a free end (12) of the blade (10), the blade (10) having a resonator (13) incorporated therein to reduce the drag movements (F1, F2) of the blade (10), the resonator (13) being provided with a solid and movable heavy element (30) and with resilient retaining element (20) secured to the heavy element (30) and to the blade (10). Furthermore, the resonator (13) includes guide element (40) in which the heavy element (30) is capable of oscillating (F1′, F2′) longitudinally, the guide element (40) being arranged in a longitudinal direction (D1) of the blade. | ||||||
| 147 | TO ROTORCRAFT ROTORS FITTED WITH INTER-BLADE DAMPERS | US11965786 | 2007-12-28 | US20080159862A1 | 2008-07-03 | Frederic BEROUL |
| The present invention relates to an improvement to rotorcraft rotors (1) fitted with inter-blade drag dampers (15) such that for each blade (4), the two joints (16) connecting said blade (4) to two inter-blade drag dampers (15) are disposed on either side of the pitch variation axis (101) of said blade, at least one of the two joints (16) being offset to above the plane P containing the pitch variation axis (101) and the vertical flapping axis (102). | ||||||
| 148 | FLUID-ELASTOMERIC DAMPER ASSEMBLY INCLUDING INTERNAL PUMPING MECHANISM | US11837892 | 2007-08-13 | US20070273075A1 | 2007-11-29 | Donald Russell |
| A fluid-elastomeric damper assembly operable for damping relative motion between a first structure and a second structure including a housing structure grounded to the first structure and a plurality of elastomer seals coupled to the housing structure, the housing structure and the plurality of elastomer seals defining a fluid-elastomeric chamber operable for containing a fluid. The fluid-elastomeric damper assembly also including one or more piston structures disposed within the housing structure and the fluid-elastomeric chamber, the one or more piston structures grounded to the first structure and driven by the second structure, and the one or more piston structures each including a first fluid chamber and a second fluid chamber in communication via an orifice, the first substantially fluid-filled chamber and the second substantially fluid-filled chamber also in communication with the fluid-elastomeric chamber through a fluid backfiller. The relative motion is operable for pumping the fluid through the orifice. | ||||||
| 149 | Fluid-elastomeric damper assembly including internal pumping mechanism | US11061066 | 2005-02-18 | US07270321B2 | 2007-09-18 | Donald D. Russell |
| A fluid-elastomeric damper assembly operable for damping relative motion between a first structure and a second structure including a housing structure grounded to the first structure and a plurality of elastomer seals coupled to the housing structure, the housing structure and the plurality of elastomer seals defining a fluid-elastomeric chamber operable for containing a fluid. The fluid-elastomeric damper assembly also including one or more piston structures disposed within the housing structure and the fluid-elastomeric chamber, the one or more piston structures grounded to the first structure and driven by the second structure, and the one or more piston structures each including a first fluid chamber and a second fluid chamber in communication via an orifice, the first substantially fluid-filled chamber and the second substantially fluid-filled chamber also in communication with the fluid-elastomeric chamber through a fluid backfiller. The relative motion is operable for pumping the fluid through the orifice. | ||||||
| 150 | Rotorcraft rotor with blades hinged in flap and in lag | US11523614 | 2006-09-20 | US20070071602A1 | 2007-03-29 | Frederic Beroul |
| The invention relates to a rotorcraft rotor comprising a hub and at least two blades hinged relative to the hub about respective pitch axes and about respective flap axes, and about respective lag axes; each blade is secured to a respective pitch lever; the rotor includes a respective pitch control rod connected to each pitch lever by a first ball joint, and a common lag damper system centered substantially on the axis of rotation of the rotor and connected to each of the blades; the damper system is secured to a respective lateral projection from each blade via a respective second ball joint that is sufficiently close to the first ball joint connecting the pitch rod to the pitch lever for the lag damper system to be relatively insensitive to flap oscillations of the hinged blades. | ||||||
| 151 | Rotor system vibration absorber | US10474860 | 2002-04-19 | US07153094B2 | 2006-12-26 | Cecil E. Covington, deceased |
| A rotor system vibration absorber for use with a helicopter of other rotorcraft is disclosed in which spring forces are provided by a plurality of elongated rods arranged in a selected pattern. The rods are coupled at one end to a fixed base that is coupled to a rotor hub, and at the other end to a tuning weight. | ||||||
| 152 | Method of controlling vibration damping in a helicopter, and apparatus implementing the method | US11069987 | 2005-03-03 | US20060056973A1 | 2006-03-16 | Elio Zoppitelli |
| The present invention relates to a method of controlling a drag damper for a helicopter blade under all operating configurations of the helicopter, the method consisting in: a) measuring the elongation of the damper; b) amplifying the measured signal and filtering out noise; c) isolating the natural response of the blade corresponding to the drag movement of the blade from the forced response imposed by a rotor driving the blades; and d) analyzing in real time the natural response and adjusting the damping as a function of the analysis. | ||||||
| 153 | Flexbeam damper assembly having transition shim clamp device | US10342716 | 2003-01-15 | US06827553B2 | 2004-12-07 | Peter J. Jones; Eric J. Seitter |
| A damper assembly including a spherical elastomer bearing member, wherein the spherical elastomer bearing member is operable for accommodating relative motion and/or vibration, and a flat elastomer bearing member, wherein the flat elastomer bearing member is operable for accommodating relative motion and/or vibration. The damper assembly also including a substantially rigid transition shim disposed between the spherical elastomer bearing member and the flat elastomer bearing member, wherein the substantially rigid transition shim is operable for coupling the spherical elastomer bearing member to the flat elastomer bearing member. The damper assembly further including a tension member attached to the substantially rigid transition shim, wherein the tension member is operable for precompressing the spherical elastomer bearing member and increasing the cocking stiffness of the damper assembly. | ||||||
| 154 | Dual piston drag damper for rotary-wing aircraft rotor | US10356898 | 2003-02-03 | US20030146343A1 | 2003-08-07 | Elio Zoppitelli; Philippe Legendre |
| A drag damper for use on a rotary wing aircraft rotor comprises a body defining two variable volume chambers linked by a piston. The chambers are filled with fluid and are connected by a restriction port (35) and by a channel (32) of larger cross-section than the restriction port. A secondary piston slidable and pressure-tight piston is fitted in the channel and loaded by an elastic bias (34). The equivalent mass of this secondary piston (33) and of the fluid which it displaces, and the stiffness of the elastic bias (34) are such that the secondary piston is resonant in the channel (32) at the rotation frequency of the rotor, to filter the dynamic component at this frequency of stresses applied to the damper (20). Furthermore at the natural drag frequency of the corresponding blade, the elastic bias substantially blocks the secondary piston (33) in its channel (32), and the flow of fluid between the chambers (29, 30) of the damper (20) takes place mainly via the restriction port (35) calibrated to provide substantial damping at this frequency. | ||||||
| 155 | Fluid inertia drag damper for rotary wing aircraft rotor | US10186830 | 2002-07-01 | US20030012650A1 | 2003-01-16 | David Ferullo |
| A drag damper for use on a rotary-wing aircraft rotor comprises a body defining two variable volume chambers linked by a piston. The chambers filled with fluid in the damper are connected by a restrictor port in the piston or between the latter and the body, and via a channel of great length and small cross-section compared with the cross-section of the body, in which elastic means bear against and load the piston-rod assembly towards a neutral position, the anti-resonance frequency of the damper being matched substantially to the nominal rotation frequency of the rotor, and the restrictor port providing effective damping at the natural frequency (nullnull) of the blades in drag, differing by construction from the rotor frequency (null). | ||||||
| 156 | Minimizing wind forces on helicopter blades | US09637370 | 2000-08-15 | US06398496B1 | 2002-06-04 | Teppo K. Jokinen |
| Helicopter blades each have a piston connected to it. The pistons are movable within a cylinder between innermost and outermost positions. The hydraulic fluid of each cylinder is connected to other cylinders by a hydraulic tube or through a manifold. A drive bar moving synchronously with the blades is connects to the cylinders. As the helicopter moves in flight the force of the wind against a blade causes a piston to move inwardly. This causes fluid to be expelled from the cylinder into the another cylinder by way of the hydraulic tube causing other piston to be moved outwardly. Meanwhile the other piston, because it is moving with the wind, is exerting an opposite effect on the other piston. The result is a tendency for the blades to approach an equilibrium condition with respect to the wind forces to minimize the shocks to the overall system. | ||||||
| 157 | Device for damping the drag of the blades of a rotor | US644846 | 1996-05-09 | US5636970A | 1997-06-10 | Nicolas Certain |
| The device comprises, between two blades and their members linking them to the hub, three levers articulated by ball joints to the members and to the hub, the two levers pivoting on the third one about axes of pivoting parallel to each other and perpendicular to the common plane passing through the centres of the ball joints. At least one of the levers comprises at least one drag damper. | ||||||
| 158 | Pitch-control devices for hingeless rotors | US539651 | 1995-10-05 | US5562415A | 1996-10-08 | Philippe M. R. Legendre; Thomas P. Manfredotti; Gilles D. Herpin |
| For each blade, the cuff which is rigid in torsion, surrounding the corresponding rotor attachment twistable arm, bears two opposed pitch levers each articulated to one respectively of two intermediate connecting rods which are moreover articulated to one and the same transmission lever on either side of a pivoting link by means of which this lever pivots on a pivot secured to the rotor mast. The transmission lever is additionally articulated to the pitch-control rod at a point which is offset with respect to its pivoting link. A crossmember is articulated to the connecting rods and interacts with an assembly having a drag damper, this assembly itself being articulated to a fixed point secured in terms of rotation to the rotor mast. | ||||||
| 159 | Tubular elastomer damper | US241456 | 1994-05-11 | US5449152A | 1995-09-12 | Francis E. Byrnes; Lawrence I. Cullen, III |
| A tubular elastomer damper has a central shaft disposed within a housing and surrounded by an elastomer member. 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 to an outer bonding surface such that the radius times the length at each point along the elastomer is equal or by providing a first elastomer layer adjacent the shaft having a high fatigue strain/lower damping ability, a second elastomer layer adjacent the housing having a low strain higher damping ability and an intermediate elastomer layer of moderate strain and damping therebetween such that from the inner to the outer radius of the elastomer member, uniform strain is achieved. By providing uniform strain from the inner to the outer radius of the tubular elastomer damper, temperature increases due to localized high strains are avoided which are detrimental to damper performance. Optionally, axial cooling passages are provided within the elastomer member to dissipate heat to assure operation within design parameters, thus extending the life of the tubular elastomer damper. | ||||||
| 160 | Rotor head for rotary wing aircraft | US40653 | 1993-03-31 | US5407325A | 1995-04-18 | Jacques A. Aubry |
| A rotor head for a rotary wing aircraft having a plurality of rotor blades, such that each blade is coupled to the hub by an attachment assembly. The attachment assembly includes a thrust bearing device attached to the hub for allowing angular oscillations, and drag damping device coupled between the blade and the hub for damping movements of drag caused by rotation of the rotor head. The drag damping device has visco-elastic elements which are pivotable with respect to each other about a common axis. The damping device is also disposed to pivot in a flapping direction of the blade through a pivot joint. | ||||||
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