Class / Patent application number | Description | Number of patent applications / Date published |
244060000 | Transmission of power | 22 |
20080217469 | ROTORCRAFT AIR CONDITIONER SYSTEM - The invention relates to a method of controlling an air conditioner in a rotorcraft that also includes a cooler for cooling transmission lubricant, in which the temperature of the lubricant is monitored and the capacity of the air conditioner is decreased in the event of the lubricant temperature reaching or exceeding a determined value. | 09-11-2008 |
20080315035 | VARIABLE SPEED GEARBOX WITH AN INDEPENDENTLY VARIABLE SPEED TAIL ROTOR SYSTEM FOR A ROTARY WING AIRCRAFT - A gearbox of a rotary-wing aircraft includes at least one variable speed system which optimizes the main rotor speed for different flight regimes such as a hover flight profile and a high speed cruise flight profile for any rotary wing aircraft while maintaining an independently variable tail rotor speed. | 12-25-2008 |
20090057481 | Dual-Power Transmission Device for a Twin-Rotor Helicopter - A dual-power transmission device includes: a first output shaft secured rotatably in a housing and having a first rotor coupling portion extending outwardly of the housing; a second output shaft disposed to surround the first rotor coupling portion, secured rotatably in the housing, and having a second rotor coupling portion extending outwardly of the housing; first and second bevel gears mounted respectively on the first and second output shafts; first, second and third thrust bearings for positioning the first and second bevel gears in the housing; and first and second input units respectively coupled to first and second power sources and each meshing with the first and second bevel gears. | 03-05-2009 |
20090057482 | Transmission Device for a Twin-Rotor Helicopter - A transmission device includes: a transmission shaft having first and second shaft sections and a gear mounting portion; a first tube sleeved rotatably on the first shaft section, and including a tube body and an annular portion; a second tube sleeved on the second shaft section; a plurality of first planetary bevel gears mounted rotatably on the gear mounting portion; a plurality of second planetary bevel gears mounted rotatably on the annular portion; a transmission gear disposed rotatably on the tube body and meshing with the first and second planetary bevel gears; a first output bevel gear disposed rotatably on the second tube and meshing with the first planetary bevel gears; and a second output bevel gear disposed rotatably on the tube body of the first tube and meshing with the second planetary bevel gears. | 03-05-2009 |
20090072081 | Helicopter transmission - There is described a transmission for a helicopter, the transmission having a movable transmission member; a casing housing the movable member; lubricated supporting means for supporting the movable member inside the casing and for rotation about an axis; and feed means for feeding a lubricating fluid to the supporting means; the transmission also has storage means permitting gradual release of the lubricating fluid, and which are connected fluidically to the feed means and to the supporting means to permit lubrication of the supporting means in the event of breakdown of the feed means; and the storage means are angularly integral with the movable member and located radially inwards of the supporting means to feed the lubricating fluid centrifugally to the supporting means. | 03-19-2009 |
20090146001 | Power transmission system for an aircraft - A power transmission system for an aircraft is disclosed. A driving motor having a driving axle is provided inside an aircraft. The driving axle has a gear part and a wheel part. They drive a gear disk and a belt, respectively, to rotate the rotor and the tail rotor. The invention simplifies the power transmission structure of the aircraft. | 06-11-2009 |
20090212156 | AIRCRAFT ENGINE SYSTEM WITH GEARBOX UNIT - An engine system for an aircraft includes an engine and a gearbox. The engine is mounted in a nacelle region of the aircraft. The gearbox is coupled to the engine, and is mounted in a fuselage region of the aircraft. The fuselage region is separated from the fuselage region by a structure. | 08-27-2009 |
20100038473 | Aircraft Propeller Device, Method for Driving an Aircraft Propeller, Use of a Bearing for an Aircraft Propeller Drive and Use of an Electric Machine - To improve the damping of vibrations in aircraft propeller drives, the invention discloses an aircraft propeller drive comprising a propeller, a motor and a drive train between the propeller and the motor. The drive train of the aircraft propeller drive has a torsional vibration damper. | 02-18-2010 |
20100127119 | ROTORCRAFT ENGINE AND ROTOR SPEED SYNCHRONIZATION - Systems and methods are provided in which an electrical control system independently effects acceleration of both driven and driving elements of a clutch to engage each other. In preferred embodiments the clutch is not a friction clutch, but a dog clutch, and forms part of a drive drain of a rotorcraft. A second clutch can be used, along with a mechanical interlock to prevent simultaneous engagement of the clutches. Speeds of the driven and driving elements can be sensed, and altered using at least one of a rotor, a brake, a generator, an electric motor, and a combustion motor. In rotorcraft embodiments, the gearbox can have a neutral condition in which no power is transmitted from the engine to the rotor | 05-27-2010 |
20100294880 | ENGINE-PROPELLER DRIVE SYSTEM - Engine-propeller driving system comprising a device to transmit the power generated by an engine ( | 11-25-2010 |
20100314492 | Multiple Drive-Path Transmission with Torque-Splitting Differential Mechanism - A transmission for a rotary-wing aircraft has a differential torque-splitting mechanism associated with an input shaft. The differential has a drive disk coaxial with the shaft and integral in rotation with the shaft, a first driven member coaxial with the shaft and generally adjacent the drive disk, and a second driven member coaxial with the shaft and generally adjacent the drive disk. At least one pin engages each of the drive disk, the first driven member, and the second driven member. The first driven member is configured to drive a first transfer gear, and the second driven member is configured to drive a second transfer gear for supplying torque to a bull gear associated with a rotor mast. | 12-16-2010 |
20110108663 | PROPULSION DEVICE WITH A PLURALITY OF ENERGY CONVERTERS FOR AN AIRCRAFT - The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a first energy converter ( | 05-12-2011 |
20110220759 | POWER DISTRIBUTION SYSTEM - The invention relates to a power distribution system for an aircraft that comprises at least one engine, comprising at least one torque transmission means that is movably held and is connected to at least one shaft of the engine and extends from the shaft of the engine to an interior region of the aircraft fuselage, and at an end pointing away from the engine comprises at least one interface for introducing a torque. At the interface of the torque transmission means it is possible both to operate mechanical and to start the engine. Consequently in the aircraft it is possible to essentially do without converting mechanical energy to electrical energy and the subsequent use of electrical energy for generating mechanical power. This is particularly favourable in the case of twin-engine commercial aircraft that are used on short hauls. | 09-15-2011 |
20110309190 | LAYSHAFT GENERATOR - An apparatus is provided and includes a rotatable shaft on which a first bevel gearbox is disposed, a layshaft on which a second bevel gearbox is disposed, the first and second bevel gearboxes being coupled to transmit shaft rotation to the layshaft, an accessory gearbox to which the layshaft and one or more accessories are coupled and a generator operably disposed on the layshaft between the second bevel gearbox and the accessory gearbox. | 12-22-2011 |
20110315816 | Constant-Velocity Joint with Torque-Combining Differential - A constant-velocity drive system for an aircraft rotor has a gimbal mechanism and a differential torque-combining mechanism. The gimbal mechanism has gimbals driven in rotation by a rotor mast about a mast axis, the gimbals providing for gimballing relative to the mast about gimbal axes generally perpendicular to the mast axis. The differential torque-combining mechanism is connected to the gimbal mechanism and configured to be driven in rotation about the mast axis by the gimbal mechanism. The differential mechanism is capable of gimballing relative to the mast about the gimbal axes, the differential torque-combining mechanism having an output component attached to a yoke of the rotor for driving the yoke in rotation with the differential torque-combining mechanism. | 12-29-2011 |
20130126669 | ELECTRIC DRIVE DEVICE FOR AN AIRCRAFT - The invention relates to an electric drive ( | 05-23-2013 |
20140034781 | System and Method of Augmenting Power in a Rotorcraft - The present application relates to a regenerative or hybrid drive system for an aircraft. The drive system includes the use of a power augmentation device to selectively engage the drive system of an aircraft to store power. The power in the power augmentation device being configured to release a power burst to systems within the aircraft to perform critical flight maneuvers. | 02-06-2014 |
20140124618 | COUNTER ROTATING FACEGEAR GEARBOX - A gearbox assembly includes a first face gear driveable about a face gear axis in a first direction by at least one first pinion gear and a second face gear driveable about the face gear axis in a second direction opposite the first direction by at least one second pinion gear. A thrust bearing is located between the first face gear and the second face gear. The first face gear is configured to drive rotation of a first shaft in the first direction and the second face gear is configured to drive rotation of a second shaft in the second direction. Further disclosed is a power train for a rotary wing aircraft having a gearbox including a first face gear rotatable in a first direction and a second face gear rotatable in a second direction opposite the first direction. | 05-08-2014 |
20140252161 | DE-COUPLE GEARED TURBO-FAN ENGINE AND AIRCRAFT - A turbofan engine includes a core engine section including a compressor section feeding air to a combustor to generate high speed exhaust gases that drive a turbine section all disposed about an engine axis, a geartrain driven by the core engine section, a fan section driven by the geartrain about a fan axis spaced apart from the engine axis, and an accessory gearbox driven by the geartrain and mounted apart from the core engine section and the fan section. | 09-11-2014 |
20140263825 | Active Vibration Isolation System - An apparatus is disclosed includes an active vibration isolation system that includes a vibration isolator, a dual fluid pump in fluid communication with the vibration isolator and a hydraulic system, wherein the dual fluid pump is configured to segregate a tuning fluid from a hydraulic fluid and an electric-hydraulic servo valve in fluid communication with the dual fluid pump. | 09-18-2014 |
20150136901 | ROTOR HUB ELASTOMERIC BEARING - An apparatus comprising a drivelink comprising a housing including a socket, wherein the socket comprises a cross-sectional area, and a bearing cartridge disposed within the socket, wherein a cross-sectional area of the cartridge is less than the cross-sectional area of the socket. An apparatus comprising a drivelink comprising a housing having a socket, and a bearing cartridge positioned within the socket and comprising a first portion and a second portion, wherein the first portion is configured to undergo compression when a load is applied to the drivelink, and wherein the second portion is configured to not be in tension when the load is applied to the drivelink. | 05-21-2015 |
20160185460 | AIRCRAFT WITH COUNTER-ROTATING TURBOFAN ENGINES - An aircraft including a frame, a first turbofan engine coupled to the frame, and a second turbofan engine coupled to the frame is disclosed. The first turbofan engine includes a first turbine, a first fan coupled to the first turbine to be driven by rotation of the first turbine, and a first transmission coupled between the first turbine and the first fan to transmit rotation from the first turbine to the first fan. The second turbofan engine includes a second turbine, a second fan coupled to the second turbine to be driven by rotation of the second turbine, and a second transmission coupled between the second turbine and the second fan to transmit rotation from the second turbine to the second fan. | 06-30-2016 |