Class / Patent application number | Description | Number of patent applications / Date published |
244170270 | Lifting rotor supports, e.g., pylons | 13 |
20090321556 | Helicopter with an improved vibration control device - A helicopter having a rotor, a fuselage connected to the rotor by connecting means, and a control device for controlling vibration of the fuselage; the control device including generating means for generating signals associated with vibration of the fuselage, and actuating means for producing a force on the fuselage associated with the signals to reduce vibration; and the actuating means being carried by the connecting means. | 12-31-2009 |
20100090055 | Vibration-Attenuating Hard-Mounted Pylon - A preferred embodiment of a pylon has six pylon mounting links for mounting the pylon to an airframe. Each link is considered “near-rigid” and has a spherical-bearing rod-end on both ends such that the link can only transmit axial loads. At least one of the links has a mass carried within the link and selectively moveable by an actuating means along the axis of the link in an oscillatory manner for attenuating vibrations traveling axially through the link. The actuating means may be an electromechanical, hydraulic, pneumatic, or piezoelectric system. By mounting each link in a selected orientation relative to the other links, the actuating means may be operated in a manner that attenuates axial vibration that would otherwise be transmitted through the link and into the airframe. | 04-15-2010 |
20100096492 | Helicopter - A helicopter having a rotor, a fuselage, and a transmission connected functionally to the rotor; the helicopter has a supporting body supporting at least the transmission, and connecting means having a first connecting member and at least one second connecting member connected to the supporting body and the fuselage respectively; and the connecting means have elastic means interposed between the first and second connecting member. | 04-22-2010 |
20100264258 | MAGNETIC DE-ROTATION SYSTEM FOR A SHAFT FAIRING SYSTEM - A magnetic de-rotation system includes an inner ring which supports an eddy current ring and at least one inner ring magnet and an outer ring which supports at least one outer ring magnet, attraction between the at least one inner ring magnet and the at least one outer ring magnet produces a stable rotational position for a fairing. | 10-21-2010 |
20110147512 | ROTOR CARRIER STRUCTURE, A FLYING MACHINE PROVIDED WITH SUCH A CARRIER STRUCTURE, AND A METHOD OF AVOIDING UNSTABLE COUPLING BETWEEN RESONANT VIBRATION MODES - The invention provides a carrier structure ( | 06-23-2011 |
20120006934 | METHOD AND A ROTARY WING AIRCRAFT THAT ARE OPTIMIZED SO AS TO MINIMIZE THE CONSEQUENCES FOR THE OCCUPANTS OF SAID AIRCRAFT OF AN OFF-SPECIFICATION EMERGENCY LANDING - A method of minimizing the consequences for the occupants of a rotary wing aircraft ( | 01-12-2012 |
20120104157 | ROTOR DRIVEN AUXILIARY POWER APPARATUS AND METHOD - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. | 05-03-2012 |
20120292434 | Six Degrees Of Freedom Vibration Suppression - A vibration suppression system for a rotorcraft having an airframe, a main gear box, a rotor, a hub, and a rotor head, said system comprising a hub mounted vibration suppressor (HMVS) mounted on the rotor head to reduce in-plane loads that the rotor exerts on the hub; and a plurality of active vibration control (AVC) actuators grouped in an overhead of the airframe beneath and proximate to the main gear box, to reduce residual loads. | 11-22-2012 |
20120298794 | AIRCRAFT PROVIDED WITH A DEVICE FOR REDUCING VIBRATION, AND A METHOD THEREFOR - An aircraft ( | 11-29-2012 |
20130037653 | ROTORCRAFT EMPENNAGE MOUNTING SYSTEM - An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. A bulkhead is positioned rearwardly from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof. | 02-14-2013 |
20130105621 | PYLON MOUNTING SYSTEM WITH VIBRATION ISOLATION | 05-02-2013 |
20150298818 | ROTOR INDEX SENSOR SYSTEM - An aircraft is provided and includes an airframe having main, pylon and tail sections, a rotor disposed at one of the pylon and tail sections and rotatable about a rotational axis to drive the airframe and a primary gearbox disposed within the main section of the airframe and a secondary gearbox disposed within one of the pylon and tail sections. The primary gearbox includes an outer housing rotationally fixed relative to the airframe and a driveshaft extending through the outer housing and coupled to the secondary gearbox to thereby drive rotation of the rotor relative to the airframe via the secondary gearbox. The aircraft further including a sensing system affixed to the outer housing and the driveshaft and configured to sense rotational characteristics of the driveshaft. | 10-22-2015 |
20150314865 | CONVERTIBLE AIRCRAFT PROVIDED WITH TWO DUCTED ROTORS AT THE WING TIPS AND WITH A HORIZONTAL FAN IN THE FUSELAGE - The invention relates to a convertible aircraft comprising a fuselage (F), a pair of wings (A | 11-05-2015 |