| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 416134000 | Nonmetallic resilient mounting | 44 |
| 20090317253 | Cylinder for varying the pitch angle of the blades of a horizontal axis windmill, and method of manufacture of the same - A cylindrical body arranged between a shaft body and a blade of a horizontal axis wind turbine is constituted of a cylindrical barrel portion, a first flange portion fixed to a first end of the barrel portion so that the blade is connected thereto, and a second flange portion fixed to a second end of the barrel portion and connected to the shaft body. The barrel portion is constituted of a cylindrically formed rubber stock and a plurality of filamentary bodies embedded in the rubber stock and arranged in a state inclined by a prescribed angle with respect to a direction parallel to an axial direction. When tensile force F develops in the barrel portion due to centrifugal force resulting from rotation of the blade, both opening ends of the barrel portion twistedly rotate due to actions of the filamentary bodies. Thus, it follows that the pitch angle of the blade connected to the first flange portion automatically varies with a wind speed. | 12-24-2009 |
| 20100040469 | VARIABLE-PITCH PROPELLER - Variable-pitch propeller ( | 02-18-2010 |
| 20130004313 | DAMPER FOR AN INTEGRALLY BLADED ROTOR - A Rotor includes a disk having a rim with an axial face, the rim defines a circumferential groove. A damper engaged with the rim at both the axial face and the circumferential groove. | 01-03-2013 |
| 20130336789 | WIND TURBINE BLADE COMPRISING ROOT END BULKHEAD - A wind turbine blade ( | 12-19-2013 |
| 20140205455 | SHOCK ABSORBER FOR PROPELLER UNIT, PROPELLER UNIT, AND VESSEL PROPULSION APPARATUS - A damper is disposed between an outer peripheral surface of a bushing and an inner peripheral surface of an inner hub. The damper includes a first portion facing a rib of the bushing, a second portion facing a rib of the inner hub, and a connection portion by which the first portion and the second portion are connected to each other. In a state in which a rotational force has not been applied between the bushing and the inner hub, the damper includes a cross-sectional shape that defines a deformation-absorbing space positioned between the first portion and the second portion. The deformation-absorbing space is deformed such that the first portion approaches the second portion in a state in which the rib of the bushing and the rib of the inner hub have moved relatively by application of a rotational force between the bushing and the inner hub. | 07-24-2014 |
| 20160152329 | Folding Proprotor Gimbal Lock and Blade Lock Mechanism | 06-02-2016 |
| 20080253891 | Swash Plate Anti-Torque Mechanism - An anti-torque mechanism which permits a full range of swashplate assembly motion. The anti-torque mechanism generally includes an anti-torque shaft and a compound bearing mounted thereto to provide five-degrees-of-freedom (spherical-linear-elastomeric) so as to permit a swashplate attachment point to move axially in response to pitch input; pivot in response to swashplate tilt; and move in/out in the radial direction. | 10-16-2008 |
| 20080304967 | Actuation system, helicopter using the same, and controlling method therefor - An actuation system includes a pump assembly configured to form a pump chamber; an actuator having first and second chambers and a movable member and configured to convert pressures applied to the first and second chambers into a movement of the movable member; and a valve section. A controller controls the valve section to open a first flow path between the pump chamber and the first chamber and close a second flow path between the pump chamber with the second chamber, during a discharge period during which the pump chamber is pressurized, in a first mode; to close the first flow path and open the second flow path during an intake period during which the pump chamber is depressurized, in the first mode; to close the first flow path and open the second flow path during the discharge period in a second mode; and to open the first flow path and close the second flow path during the intake period in the second mode. | 12-11-2008 |
| 20090060742 | Rotor Head for a Twin-Rotor Helicopter - A rotor head includes a hub and two joint members. The hub has opposite tubular end portions, each formed with a socket that extends inwardly from an end face thereof along a tube axis and that has inner and outer socket sections. Each of the joint members includes a link and a vibration absorbing component. The link has a hub coupling segment retained rotatably in the inner socket section of a respective socket, an intermediate segment extending from the hub coupling segment and disposed movably in the outer socket section of the respective socket, and a blade coupling segment extending from the intermediate segment and outwardly of the outer socket section. The vibration absorbing component is mounted on the intermediate segment, and is disposed in the outer socket section. | 03-05-2009 |
| 20090162201 | UNIFORM FATIGUE LIFE SPHERICAL ELASTOMERIC BEARING - An elastomeric spherical bearing includes a multiple of elastomeric layers with an essentially equivalent fatigue life. | 06-25-2009 |
| 20090175725 | LOW MAINTENANCE STIFF IN PLANE GIMBALED ROTOR HEAD - A stiff in-plane gimbaled rotor head for a rotorcraft, such as a helicopter, includes a vertically extending rotor shaft, a center hub disposed on the rotor shaft for conjoint rotation therewith, and an outer hub surrounding the center hub and coupled thereto through a spherical gimbal bearing for conjoint rotation therewith, and such that the outer hub is also capable of an angular range of gimbaling movement relative to the center hub. A plurality of rotor blades, which may include three or more blades, is coupled to the rotor shaft through the inner and outer hubs by a constant velocity joint that enables the blades to be rotated in a common plane about the axis of the rotor shaft while controlling the respective pitches of the blades and such that any other relative in-plane and out-of-plane movements of the blades during rotation is prevented. | 07-09-2009 |
| 20100034654 | Sculptured Throat Spool - A sculpted throat spool of a tension-torsion strap assembly is disclosed. Using the sculpted throat spool minimizes the stress riser typically present at the edge of the spool when a tension-torsion strap is articulated. | 02-11-2010 |
| 20100092294 | HELICOPTER ANTITORQUE TAIL ROTOR - A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has two opposite surfaces extending between the leading edge and the trailing edge, and a root portion extending from a radially inner first end, with respect to a rotation axis of the blade, towards a second end opposite the first end; and the root portion, when sectioned in a plane perpendicular to the leading edge and trailing edge, has a profile asymmetrical with respect to a chord joining the leading edge and trailing edge. | 04-15-2010 |
| 20100124501 | MULTIPLE FUNCTION INTERFACE FITTING - An apparatus may comprise a housing, a first member, and a second member. The housing may have a first end, a second end, a first side, a second side, an opening located in the first end, and a passage extending from the opening. The first member may extend from the first side. The first member may have a first channel in communication with the passage and the channel has a first center axis. The second member may extend from the first side. The second member may have a second channel in communication with the passage and the second channel has a second center axis substantially aligned with the center axis of the channel in the first member. | 05-20-2010 |
| 20100196161 | ROTOR HEAD OF REMOTELY-CONTROLLED HELICOPTER AND REMOTELY-CONTROLLED HELICOPTER - When an R/C helicopter of a single rotor type is configured to have a small size and light weight to be used indoors, a flying operation thereof can be stabilized and operability can be improved. | 08-05-2010 |
| 20100247312 | BLADE PROVIDED WITH A DRAG DAMPER, AND A ROTOR PROVIDED WITH SUCH A BLADE - The present invention relates to a rotorcraft blade ( | 09-30-2010 |
| 20100278648 | TENSION-TORQUE-TRANSMISSION ELEMENT FOR A FENESTRON BLADE AND METHOD FOR PRODUCING IT - A tension-torque-transmission element ( | 11-04-2010 |
| 20100278649 | ROTOR WING WITH INTEGRATED TENSION-TORQUE-TRANSMISSION ELEMENT AND METHOD FOR ITS PRODUCTION - A rotor wing in a fibre-reinforced composite design including fibre layers, in particular for a tail rotor of a rotary wing aircraft, with a rotor blade ( | 11-04-2010 |
| 20120201678 | FLEXBEAM ROTOR - A rotor hub assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extend through the rotor hub, with each end of each flex beam operably connectible to a rotor blade. One or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A rotor assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extending through the rotor hub and one or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A plurality of rotor blades are operably connected to the ends of the one or more flex beams. | 08-09-2012 |
| 20130034442 | LEAD LAG DAMPER FOR HELICOPTER ROTOR UNIT - A lead lag damper ( | 02-07-2013 |
| 20130034443 | PLANAR FLEXBEAM UNIT - A planar flexbeam unit ( | 02-07-2013 |
| 20130084183 | DUAL SERIES DAMPER SYSTEM - A dual series damper includes a fluid damper portion and a elastomeric damper portion. The fluid damper portion includes a first housing, a first connection member, and a piston coupled to the first connection member. The piston divides an interior of the first housing into a first fluid chamber and a second fluid chamber. The piston has a fluid passage in the piston, the fluid passage being configured to provide fluid communication between the first fluid chamber and the second fluid chamber. The elastomeric damper portion includes a second housing, a second connection member coupled to the second housing, and an elastomer between the first housing and the second housing. When a lead/lag force is introduced to the dual series damper, the fluid damper portion behaves rigidly so that the elastomeric damper portion dampens the lead/lag oscillation. | 04-04-2013 |
| 20130121828 | Rotor Hub Bearing System - The bearing system is configured for treating and reacting dynamic loading within a rotor hub of rotorcraft. The bearing system includes an outer member having a plurality of alternating outer elastomeric layers and shim layers. The outer member has an inboard surface configured for bonding to an inboard bearing support, and the outer member has an outboard surface configured for bonding to an outboard bearing support. The bearing system has an inner member bonded to an interior surface of the outer member. The inner member can include a rigid inner core, as well as a plurality of elastomeric layers and shim layers configured to react torsional movements of the rotor blade. | 05-16-2013 |
| 20130224022 | HELICOPTER BLADE RETENTION COMPOSITE YOKE - A rotary wing aircraft yoke is provided including an arcuate medial portion. A pair of arms extends from the medial portion and each terminates in a distal end. The yoke is made from multiple plies of glass and graphite fibers of varying orientations. The number of graphite plies increases along each arm from adjacent the medial portion to the distal end. | 08-29-2013 |
| 20140112785 | SEPARABLE BLADE ATTACHMENT FOR A BEARINGLESS ROTOR OF A HELICOPTER - The invention relates to a separable blade attachment ( | 04-24-2014 |
| 20140241884 | ROTARY WING AIRCRAFT PITCH BEAM ATTACHMENT WITH ANTI-ROTATION PLATE DESIGN - A retaining assembly for a tail rotor system is provided including a washer having a plurality of splines. The washer is configured to couple to an adjacent pitch change shaft. A retaining nut includes a self-locking feature and a flange arranged at a first end. The retaining nut is configured to threadably couple to the pitch change shaft such that the flange is in contact with the washer. The flange includes a plurality of first holes configured to at least partially align between the splines of the washer. A lock plate includes a body and a plurality of tabs extending generally perpendicularly from the body. The lock plate is slidably positioned about the pitch change shaft adjacent the flange. The lock plate is operably coupled to the retaining nut and the washer to limit rotational movement thereof relative to the pitch change shaft. | 08-28-2014 |
| 20140241885 | PARTLY CRUCIFORM FLEXBEAM AND METHOD OF MANUFACTURING SUCH A FLEXBEAM - A partly cruciform flexbeam ( | 08-28-2014 |
| 20140255191 | Low Shear Modulus Transition Shim for Elastomeric Bearing Bonding in Torsional Applications - A bearing assembly comprises a bearing, a shim disposed within the bearing, and a component disposed within the shim. The shim comprises a first material, the component comprises a second material, and the first material has an elastic modulus value that is lower than an elastic modulus value of the second material. An apparatus comprises an elastomeric bearing, a fiberglass shim, and a steel spindle that is connected to the elastomeric bearing through the shim. A method for reducing strain in an adhesive layer that connects a bearing to a component comprises selecting a shim material having an elastic modulus value that is less than an elastic modulus value of the component and providing instructions to connect the component to the shim by placing the adhesive layer between an outer surface of the component and an inner surface of the shim. | 09-11-2014 |
| 20140271199 | High Flapping Yoke Hub Assembly Using a Cylindrical Elastomeric Attachment to Avoid Holes - An apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein a center portion of each longitudinal side portion comprises a build-up of material that is configured to accommodate a yoke hub clamp. Included is an apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions. Also included is a method of coupling aircraft blades comprising providing a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions. | 09-18-2014 |
| 20140271200 | Flexing Clevis Arrangement Bolted Joint Attachment For Flexible Rotor Hub With High Offset And High Flapping - A flexible joint assembly for providing flexure to a rotor blade comprising an upper hub plate and a lower hub plate configured to secure a rotor blade yoke via a bolted joint located radially outward of a mast; and an upper flexure assembly connected to the upper hub plate and a lower flexure assembly connected to the lower hub plate, wherein the upper flexure assembly and lower flexure assembly are configured to promote flapping of the rotor blade yoke about a flapping hinge located radially outward of the bolted joint. | 09-18-2014 |
| 20140271201 | Jam-Tolerant Linear Control Motor for Hydraulic Actuator Valve - According to one embodiment, a linear control motor includes a first permanent magnet, a coil, a first magnetic material, a shaft, and a first non-magnetic material. The first non-magnetic material is disposed between at least one of the movable components and at least one of the static components and operable to prevent physical contact between at least one of the movable components and at least one of the static components. | 09-18-2014 |
| 20140377067 | ROTOR SYSTEM OF A ROTARY WING AIRCRAFT - A rotor system of a rotary wing aircraft, e.g. a helicopter with a rotor mast, a rotor hub ( | 12-25-2014 |
| 20140377068 | ROTOR BLADE CONTROL DEVICE - Rotor blade control device for a helicopter, consisting of a swash plate disk, the swash plate disk consisting of a non-rotating part of the swash plate disk, which is stationary stationarily coupled to the helicopter, a rotating part of the swash plate disk, at least three actuators which are arranged around a rotor shaft axis of the helicopter, a coupling element between actuator and the non-rotating part of the swash plate disk. The coupling element can be adjusted in its tilt, in order to change the position of the crosspoint at the non-rotating part of the swash plate disk alongside the rotor shaft axis by means of the actuator through a control shaft, in order to adjust the rotor blades. Here, the coupling element is made up in a rigid way, and the actuators are arranged onto the stationary component being able to pivot around a respective swivel axis. Further, the first crosspoint has a radial distance to the swivel axis, whereby the control axis and the swivel axis are arranged in such a way toward each other, that the radial distance of the first crosspoint to rotor shaft axis changes with the swivel movement of actuator around swivel axis. | 12-25-2014 |
| 20150104314 | ADAPTIVELY-TWISTABLE BLADE, AND AN AIRCRAFT INCLUDING SUCH A BLADE | 04-16-2015 |
| 20150125300 | ROTOR HUB FOR A ROTORCRAFT - A drive mechanism for a rotary aircraft includes an outer drive member having a plurality of drive trunnions extending therefrom; a middle drive member resiliently coupled to the outer drive member; and an inner drive member resiliently coupled to the middle drive member. | 05-07-2015 |
| 20150139800 | HELICOPTER TRANSMISSION MOUNT SYSTEM - A restraint system for a transmission in an aircraft can include a first strut having a first fluid chamber, a first piston resiliently coupled to a first housing with a first elastomeric member. The restraint system can include a second strut having second fluid chamber, a second piston resiliently coupled to a second housing with a second elastomeric member. The restraint system can include a fluid line between the first fluid chamber and the second fluid chamber. The first strut and the second strut collectively provide not only torque restraint, but also torque measurement and fore/aft vibration isolation. | 05-21-2015 |
| 20150147177 | ROTORCRAFT TOP FAIRING HAVING A PROFILE IN THE SHAPE OF A TRUNCATED DROP OF WATER THAT IS PROVIDED WITH A HUMP OF UNEVEN SURFACE - A rotorcraft provided on top with a fairing ( | 05-28-2015 |
| 20150298801 | STIFF INPLANE ELASTROMERIC ROTOR HEAD - An aircraft rotor head is provided and includes a rotor hub including a central portion and radial arms extending outwardly from the central portion, blade retention yokes, each blade retention poke being pivotably coupled to a corresponding one of the radial arms at one end and to a corresponding blade at another end and a lag restraint star rotatable about and translatable along the central portion. The lag restraint star is coupled to each of the blade retention yokes to facilitate uniform blade lead/lag and uniform blade coning. | 10-22-2015 |
| 20150336662 | ROTOR BLADE COUPLING DEVICE AND ROTOR HEAD - A rotor blade coupling device ( | 11-26-2015 |
| 20150344133 | FLEXBEAM UNIT WITH AT LEAST ONE TWISTED FLEXBEAM ELEMENT - A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of the multi-blade rotor, at least one of the predetermined number of torsion elements comprising at least one flexbeam element having an associated longitudinal direction, the at least one flexbeam element comprising at least one twisted area in which the at least one flexbeam element is twisted in the associated longitudinal direction. | 12-03-2015 |
| 20160152328 | Rotor Hub Bearing System | 06-02-2016 |
| 20160159474 | BAR OF COMPOSITE MATRIX MATERIAL - In a rotary wing aircraft a bar ( | 06-09-2016 |
| 20160200433 | ROTORCRAFT ROTOR COMPRISING A HUB MADE OF COMPOSITE MATERIALS OBTAINED FROM CARBON FIBER FABRIC DUSTED IN A THERMOPLASTIC RESIN | 07-14-2016 |
| 20160200434 | ROTOR HEAD FOR A VERTICAL TAKEOFF AND LANDING AIRCRAFT | 07-14-2016 |
| 416134000 | Aircraft rotors | 38 |
| 20090317253 | Cylinder for varying the pitch angle of the blades of a horizontal axis windmill, and method of manufacture of the same - A cylindrical body arranged between a shaft body and a blade of a horizontal axis wind turbine is constituted of a cylindrical barrel portion, a first flange portion fixed to a first end of the barrel portion so that the blade is connected thereto, and a second flange portion fixed to a second end of the barrel portion and connected to the shaft body. The barrel portion is constituted of a cylindrically formed rubber stock and a plurality of filamentary bodies embedded in the rubber stock and arranged in a state inclined by a prescribed angle with respect to a direction parallel to an axial direction. When tensile force F develops in the barrel portion due to centrifugal force resulting from rotation of the blade, both opening ends of the barrel portion twistedly rotate due to actions of the filamentary bodies. Thus, it follows that the pitch angle of the blade connected to the first flange portion automatically varies with a wind speed. | 12-24-2009 |
| 20100040469 | VARIABLE-PITCH PROPELLER - Variable-pitch propeller ( | 02-18-2010 |
| 20130004313 | DAMPER FOR AN INTEGRALLY BLADED ROTOR - A Rotor includes a disk having a rim with an axial face, the rim defines a circumferential groove. A damper engaged with the rim at both the axial face and the circumferential groove. | 01-03-2013 |
| 20130336789 | WIND TURBINE BLADE COMPRISING ROOT END BULKHEAD - A wind turbine blade ( | 12-19-2013 |
| 20140205455 | SHOCK ABSORBER FOR PROPELLER UNIT, PROPELLER UNIT, AND VESSEL PROPULSION APPARATUS - A damper is disposed between an outer peripheral surface of a bushing and an inner peripheral surface of an inner hub. The damper includes a first portion facing a rib of the bushing, a second portion facing a rib of the inner hub, and a connection portion by which the first portion and the second portion are connected to each other. In a state in which a rotational force has not been applied between the bushing and the inner hub, the damper includes a cross-sectional shape that defines a deformation-absorbing space positioned between the first portion and the second portion. The deformation-absorbing space is deformed such that the first portion approaches the second portion in a state in which the rib of the bushing and the rib of the inner hub have moved relatively by application of a rotational force between the bushing and the inner hub. | 07-24-2014 |
| 20160152329 | Folding Proprotor Gimbal Lock and Blade Lock Mechanism | 06-02-2016 |
| 20080253891 | Swash Plate Anti-Torque Mechanism - An anti-torque mechanism which permits a full range of swashplate assembly motion. The anti-torque mechanism generally includes an anti-torque shaft and a compound bearing mounted thereto to provide five-degrees-of-freedom (spherical-linear-elastomeric) so as to permit a swashplate attachment point to move axially in response to pitch input; pivot in response to swashplate tilt; and move in/out in the radial direction. | 10-16-2008 |
| 20080304967 | Actuation system, helicopter using the same, and controlling method therefor - An actuation system includes a pump assembly configured to form a pump chamber; an actuator having first and second chambers and a movable member and configured to convert pressures applied to the first and second chambers into a movement of the movable member; and a valve section. A controller controls the valve section to open a first flow path between the pump chamber and the first chamber and close a second flow path between the pump chamber with the second chamber, during a discharge period during which the pump chamber is pressurized, in a first mode; to close the first flow path and open the second flow path during an intake period during which the pump chamber is depressurized, in the first mode; to close the first flow path and open the second flow path during the discharge period in a second mode; and to open the first flow path and close the second flow path during the intake period in the second mode. | 12-11-2008 |
| 20090060742 | Rotor Head for a Twin-Rotor Helicopter - A rotor head includes a hub and two joint members. The hub has opposite tubular end portions, each formed with a socket that extends inwardly from an end face thereof along a tube axis and that has inner and outer socket sections. Each of the joint members includes a link and a vibration absorbing component. The link has a hub coupling segment retained rotatably in the inner socket section of a respective socket, an intermediate segment extending from the hub coupling segment and disposed movably in the outer socket section of the respective socket, and a blade coupling segment extending from the intermediate segment and outwardly of the outer socket section. The vibration absorbing component is mounted on the intermediate segment, and is disposed in the outer socket section. | 03-05-2009 |
| 20090162201 | UNIFORM FATIGUE LIFE SPHERICAL ELASTOMERIC BEARING - An elastomeric spherical bearing includes a multiple of elastomeric layers with an essentially equivalent fatigue life. | 06-25-2009 |
| 20090175725 | LOW MAINTENANCE STIFF IN PLANE GIMBALED ROTOR HEAD - A stiff in-plane gimbaled rotor head for a rotorcraft, such as a helicopter, includes a vertically extending rotor shaft, a center hub disposed on the rotor shaft for conjoint rotation therewith, and an outer hub surrounding the center hub and coupled thereto through a spherical gimbal bearing for conjoint rotation therewith, and such that the outer hub is also capable of an angular range of gimbaling movement relative to the center hub. A plurality of rotor blades, which may include three or more blades, is coupled to the rotor shaft through the inner and outer hubs by a constant velocity joint that enables the blades to be rotated in a common plane about the axis of the rotor shaft while controlling the respective pitches of the blades and such that any other relative in-plane and out-of-plane movements of the blades during rotation is prevented. | 07-09-2009 |
| 20100034654 | Sculptured Throat Spool - A sculpted throat spool of a tension-torsion strap assembly is disclosed. Using the sculpted throat spool minimizes the stress riser typically present at the edge of the spool when a tension-torsion strap is articulated. | 02-11-2010 |
| 20100092294 | HELICOPTER ANTITORQUE TAIL ROTOR - A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has two opposite surfaces extending between the leading edge and the trailing edge, and a root portion extending from a radially inner first end, with respect to a rotation axis of the blade, towards a second end opposite the first end; and the root portion, when sectioned in a plane perpendicular to the leading edge and trailing edge, has a profile asymmetrical with respect to a chord joining the leading edge and trailing edge. | 04-15-2010 |
| 20100124501 | MULTIPLE FUNCTION INTERFACE FITTING - An apparatus may comprise a housing, a first member, and a second member. The housing may have a first end, a second end, a first side, a second side, an opening located in the first end, and a passage extending from the opening. The first member may extend from the first side. The first member may have a first channel in communication with the passage and the channel has a first center axis. The second member may extend from the first side. The second member may have a second channel in communication with the passage and the second channel has a second center axis substantially aligned with the center axis of the channel in the first member. | 05-20-2010 |
| 20100196161 | ROTOR HEAD OF REMOTELY-CONTROLLED HELICOPTER AND REMOTELY-CONTROLLED HELICOPTER - When an R/C helicopter of a single rotor type is configured to have a small size and light weight to be used indoors, a flying operation thereof can be stabilized and operability can be improved. | 08-05-2010 |
| 20100247312 | BLADE PROVIDED WITH A DRAG DAMPER, AND A ROTOR PROVIDED WITH SUCH A BLADE - The present invention relates to a rotorcraft blade ( | 09-30-2010 |
| 20100278648 | TENSION-TORQUE-TRANSMISSION ELEMENT FOR A FENESTRON BLADE AND METHOD FOR PRODUCING IT - A tension-torque-transmission element ( | 11-04-2010 |
| 20100278649 | ROTOR WING WITH INTEGRATED TENSION-TORQUE-TRANSMISSION ELEMENT AND METHOD FOR ITS PRODUCTION - A rotor wing in a fibre-reinforced composite design including fibre layers, in particular for a tail rotor of a rotary wing aircraft, with a rotor blade ( | 11-04-2010 |
| 20120201678 | FLEXBEAM ROTOR - A rotor hub assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extend through the rotor hub, with each end of each flex beam operably connectible to a rotor blade. One or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A rotor assembly for a helicopter includes a rotor hub operably connectible to a shaft of a helicopter. One or more flex beams extending through the rotor hub and one or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A plurality of rotor blades are operably connected to the ends of the one or more flex beams. | 08-09-2012 |
| 20130034442 | LEAD LAG DAMPER FOR HELICOPTER ROTOR UNIT - A lead lag damper ( | 02-07-2013 |
| 20130034443 | PLANAR FLEXBEAM UNIT - A planar flexbeam unit ( | 02-07-2013 |
| 20130084183 | DUAL SERIES DAMPER SYSTEM - A dual series damper includes a fluid damper portion and a elastomeric damper portion. The fluid damper portion includes a first housing, a first connection member, and a piston coupled to the first connection member. The piston divides an interior of the first housing into a first fluid chamber and a second fluid chamber. The piston has a fluid passage in the piston, the fluid passage being configured to provide fluid communication between the first fluid chamber and the second fluid chamber. The elastomeric damper portion includes a second housing, a second connection member coupled to the second housing, and an elastomer between the first housing and the second housing. When a lead/lag force is introduced to the dual series damper, the fluid damper portion behaves rigidly so that the elastomeric damper portion dampens the lead/lag oscillation. | 04-04-2013 |
| 20130121828 | Rotor Hub Bearing System - The bearing system is configured for treating and reacting dynamic loading within a rotor hub of rotorcraft. The bearing system includes an outer member having a plurality of alternating outer elastomeric layers and shim layers. The outer member has an inboard surface configured for bonding to an inboard bearing support, and the outer member has an outboard surface configured for bonding to an outboard bearing support. The bearing system has an inner member bonded to an interior surface of the outer member. The inner member can include a rigid inner core, as well as a plurality of elastomeric layers and shim layers configured to react torsional movements of the rotor blade. | 05-16-2013 |
| 20130224022 | HELICOPTER BLADE RETENTION COMPOSITE YOKE - A rotary wing aircraft yoke is provided including an arcuate medial portion. A pair of arms extends from the medial portion and each terminates in a distal end. The yoke is made from multiple plies of glass and graphite fibers of varying orientations. The number of graphite plies increases along each arm from adjacent the medial portion to the distal end. | 08-29-2013 |
| 20140112785 | SEPARABLE BLADE ATTACHMENT FOR A BEARINGLESS ROTOR OF A HELICOPTER - The invention relates to a separable blade attachment ( | 04-24-2014 |
| 20140241884 | ROTARY WING AIRCRAFT PITCH BEAM ATTACHMENT WITH ANTI-ROTATION PLATE DESIGN - A retaining assembly for a tail rotor system is provided including a washer having a plurality of splines. The washer is configured to couple to an adjacent pitch change shaft. A retaining nut includes a self-locking feature and a flange arranged at a first end. The retaining nut is configured to threadably couple to the pitch change shaft such that the flange is in contact with the washer. The flange includes a plurality of first holes configured to at least partially align between the splines of the washer. A lock plate includes a body and a plurality of tabs extending generally perpendicularly from the body. The lock plate is slidably positioned about the pitch change shaft adjacent the flange. The lock plate is operably coupled to the retaining nut and the washer to limit rotational movement thereof relative to the pitch change shaft. | 08-28-2014 |
| 20140241885 | PARTLY CRUCIFORM FLEXBEAM AND METHOD OF MANUFACTURING SUCH A FLEXBEAM - A partly cruciform flexbeam ( | 08-28-2014 |
| 20140255191 | Low Shear Modulus Transition Shim for Elastomeric Bearing Bonding in Torsional Applications - A bearing assembly comprises a bearing, a shim disposed within the bearing, and a component disposed within the shim. The shim comprises a first material, the component comprises a second material, and the first material has an elastic modulus value that is lower than an elastic modulus value of the second material. An apparatus comprises an elastomeric bearing, a fiberglass shim, and a steel spindle that is connected to the elastomeric bearing through the shim. A method for reducing strain in an adhesive layer that connects a bearing to a component comprises selecting a shim material having an elastic modulus value that is less than an elastic modulus value of the component and providing instructions to connect the component to the shim by placing the adhesive layer between an outer surface of the component and an inner surface of the shim. | 09-11-2014 |
| 20140271199 | High Flapping Yoke Hub Assembly Using a Cylindrical Elastomeric Attachment to Avoid Holes - An apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein a center portion of each longitudinal side portion comprises a build-up of material that is configured to accommodate a yoke hub clamp. Included is an apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions. Also included is a method of coupling aircraft blades comprising providing a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions. | 09-18-2014 |
| 20140271200 | Flexing Clevis Arrangement Bolted Joint Attachment For Flexible Rotor Hub With High Offset And High Flapping - A flexible joint assembly for providing flexure to a rotor blade comprising an upper hub plate and a lower hub plate configured to secure a rotor blade yoke via a bolted joint located radially outward of a mast; and an upper flexure assembly connected to the upper hub plate and a lower flexure assembly connected to the lower hub plate, wherein the upper flexure assembly and lower flexure assembly are configured to promote flapping of the rotor blade yoke about a flapping hinge located radially outward of the bolted joint. | 09-18-2014 |
| 20140271201 | Jam-Tolerant Linear Control Motor for Hydraulic Actuator Valve - According to one embodiment, a linear control motor includes a first permanent magnet, a coil, a first magnetic material, a shaft, and a first non-magnetic material. The first non-magnetic material is disposed between at least one of the movable components and at least one of the static components and operable to prevent physical contact between at least one of the movable components and at least one of the static components. | 09-18-2014 |
| 20140377067 | ROTOR SYSTEM OF A ROTARY WING AIRCRAFT - A rotor system of a rotary wing aircraft, e.g. a helicopter with a rotor mast, a rotor hub ( | 12-25-2014 |
| 20140377068 | ROTOR BLADE CONTROL DEVICE - Rotor blade control device for a helicopter, consisting of a swash plate disk, the swash plate disk consisting of a non-rotating part of the swash plate disk, which is stationary stationarily coupled to the helicopter, a rotating part of the swash plate disk, at least three actuators which are arranged around a rotor shaft axis of the helicopter, a coupling element between actuator and the non-rotating part of the swash plate disk. The coupling element can be adjusted in its tilt, in order to change the position of the crosspoint at the non-rotating part of the swash plate disk alongside the rotor shaft axis by means of the actuator through a control shaft, in order to adjust the rotor blades. Here, the coupling element is made up in a rigid way, and the actuators are arranged onto the stationary component being able to pivot around a respective swivel axis. Further, the first crosspoint has a radial distance to the swivel axis, whereby the control axis and the swivel axis are arranged in such a way toward each other, that the radial distance of the first crosspoint to rotor shaft axis changes with the swivel movement of actuator around swivel axis. | 12-25-2014 |
| 20150104314 | ADAPTIVELY-TWISTABLE BLADE, AND AN AIRCRAFT INCLUDING SUCH A BLADE | 04-16-2015 |
| 20150125300 | ROTOR HUB FOR A ROTORCRAFT - A drive mechanism for a rotary aircraft includes an outer drive member having a plurality of drive trunnions extending therefrom; a middle drive member resiliently coupled to the outer drive member; and an inner drive member resiliently coupled to the middle drive member. | 05-07-2015 |
| 20150139800 | HELICOPTER TRANSMISSION MOUNT SYSTEM - A restraint system for a transmission in an aircraft can include a first strut having a first fluid chamber, a first piston resiliently coupled to a first housing with a first elastomeric member. The restraint system can include a second strut having second fluid chamber, a second piston resiliently coupled to a second housing with a second elastomeric member. The restraint system can include a fluid line between the first fluid chamber and the second fluid chamber. The first strut and the second strut collectively provide not only torque restraint, but also torque measurement and fore/aft vibration isolation. | 05-21-2015 |
| 20150147177 | ROTORCRAFT TOP FAIRING HAVING A PROFILE IN THE SHAPE OF A TRUNCATED DROP OF WATER THAT IS PROVIDED WITH A HUMP OF UNEVEN SURFACE - A rotorcraft provided on top with a fairing ( | 05-28-2015 |
| 20150298801 | STIFF INPLANE ELASTROMERIC ROTOR HEAD - An aircraft rotor head is provided and includes a rotor hub including a central portion and radial arms extending outwardly from the central portion, blade retention yokes, each blade retention poke being pivotably coupled to a corresponding one of the radial arms at one end and to a corresponding blade at another end and a lag restraint star rotatable about and translatable along the central portion. The lag restraint star is coupled to each of the blade retention yokes to facilitate uniform blade lead/lag and uniform blade coning. | 10-22-2015 |
| 20150336662 | ROTOR BLADE COUPLING DEVICE AND ROTOR HEAD - A rotor blade coupling device ( | 11-26-2015 |
| 20150344133 | FLEXBEAM UNIT WITH AT LEAST ONE TWISTED FLEXBEAM ELEMENT - A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of the multi-blade rotor, at least one of the predetermined number of torsion elements comprising at least one flexbeam element having an associated longitudinal direction, the at least one flexbeam element comprising at least one twisted area in which the at least one flexbeam element is twisted in the associated longitudinal direction. | 12-03-2015 |
| 20160152328 | Rotor Hub Bearing System | 06-02-2016 |
| 20160159474 | BAR OF COMPOSITE MATRIX MATERIAL - In a rotary wing aircraft a bar ( | 06-09-2016 |
| 20160200433 | ROTORCRAFT ROTOR COMPRISING A HUB MADE OF COMPOSITE MATERIALS OBTAINED FROM CARBON FIBER FABRIC DUSTED IN A THERMOPLASTIC RESIN | 07-14-2016 |
| 20160200434 | ROTOR HEAD FOR A VERTICAL TAKEOFF AND LANDING AIRCRAFT | 07-14-2016 |
