Class / Patent application number | Description | Number of patent applications / Date published |
416148000 | Tiltable carrier (e.g., hub, etc.) | 12 |
20080267778 | Torque Coupling for Rotary-Wing Aircraft - A torque coupling ( | 10-30-2008 |
20080304969 | BUILT-IN SWING MECHANISM OF ROTARY FAN - The present invention provides an improved built-in swing mechanism of a rotary fan. The mechanism includes a ball-and-socket support frame, arranged onto front wall of the main casing corresponding to the axle center of a drive motor and provided with a spherical supporting surface and a through-hole. A spherical abut seat is fastened at a front end of the drive motor is provided with a spherical abut surface that couples with the spherical supporting surface. A punch hole is placed at the center of spherical abut surface for the penetration of the axle center. A crank linkage element is assembled between rear end of the drive motor and the rear wall of the main casing. The first end of the crank linkage element can be driven to enable the oscillation of the second end. The second end is assembled at a rotary pivot corresponding to the main casing. | 12-11-2008 |
20090269200 | Rotor Hub Systems and Methods - A rotorcraft is equipped with a rotor hub of large diameter in order to accommodate high loads from a hingeless rotor. In preferred embodiments, a rotorcraft has a rotor disposed on a mast with blades attached to a hub by means of a feather bearing that receives a shank of a blade. The hub is attached to non-rotating structure such as a tilting nacelle by means of a hub bearing. This facilitates the transfer of moments generated on the rotor to the airframe. The hub and feather bearings can be sized and arranged such that a feather bearing on a hub is disposed within an imaginary cylinder centered at a rotational axis of the hub and having a diameter no greater 1.2 times an inner diameter of the hub bearing. This can result in a large diameter hub and hub bearing capable of withstanding very large bending moments. | 10-29-2009 |
20110293427 | ROTOR BLADE CAMBER ADJUSTMENT - A rotor for a rotary wing aircraft is provided, which includes a hub and a number of rotor blades. Each rotor blade includes an elongate central body that has a leading edge and a flap along the leading edge. The body is pivotally connected to the hub, to pivot about a longitudinal pivot axis, and the flap is pivotally attached to the body. The rotor blade includes a leading camber adjustment mechanism that pivots the flap downwards relative to the body when the body is pivoted in a direction in which its leading edge is lifted. Similarly, the rotor blade has a trailing flap and a trailing camber adjustment mechanism that pivots the trailing flap downwards relative to the body when the body is pivoted in a direction in which its trailing edge is lifted. | 12-01-2011 |
20120183401 | MAIN ROTOR ARRANGEMENT OF AN UAV-HELICOPTER - A main rotor arrangement for an UAV-helicopter. A rotor mast defines a vertical axis of rotation. A hub is for attachment of rotor blades. The hub is mounted to the rotor mast in a tiltable way so as to reduce loads acting on the rotor blades during operation of the UAV-helicopter. A damping assembly is configured to damp the tilting of the hub. | 07-19-2012 |
20120230824 | ROTOR ASSEMBLY - A rotor assembly for helicopter vehicles for stabilizing the aircraft and thus providing an easy way of controlling pitch and roll of the aircraft by respectively associated magnetic actuators. The rotor assembly comprises a rotor with two flexible rotor blades, a rotor head rotationally coupled to the rotor shaft, a rotating swash plate, with at least three fly bars extending therefrom. The swash plate is rotationally coupled to the rotor shaft and adjusted to tilt in all directions relative to a plane perpendicular to the rotor shaft. The rotor head is hinged to the rotor shaft in one direction so that the rotor head and the rotor blades jointly are not able to tilt around their transversal axis. The coupling between the rotating swash plate and the rotor head provide synchronized tilt movements between the rotor head and the rotating swash plate around the longitudinal axis of the rotor head. | 09-13-2012 |
20120288372 | TEETER-RESTRAINT DEVICE FOR WIND TURBINES - A wind turbine system includes a shaft, a rotor for driving the shaft, and a first fluidic teeter control assembly. The rotor includes a first blade engaged to the shaft by a hub, and has a degree of freedom to pivot relative to the shaft. A first teeter angle is defined between an instantaneous position of the first blade and a time-averaged plane of rotation of the first blade. The first fluidic teeter control assembly is engaged between the rotor and the shaft for providing a first dynamic teeter restraining force as a function of the first teeter angle and a fluidic resistance. The first dynamic restraining force is relatively low when the first teeter angle is within a first teeter operation range, and the first dynamic restraining force is higher when the first teeter angle is outside that range. | 11-15-2012 |
20130224025 | Offset Stacked Yoke Hub for Tiltrotor Aircraft - A tiltrotor rotor hub comprises first and second configurations of yokes arranged in two parallel and axially offset planes, each having an equal number of two or more yokes substantially equally spaced about a mast, wherein a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke. Another tiltrotor rotor hub is selectively positionable for operation in helicopter/airplane/transition modes and comprises substantially parallel and axially offset first and second planes, each containing a plurality of blade yokes arranged about a central axis and a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke. Another tiltrotor rotor hub is coupled to a tiltrotor mast and comprises a stacked arrangement of blade yokes wherein a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke, and a plurality of mounting components coupling each yoke to the overlapping azimuthally adjacent yoke. | 08-29-2013 |
20140161614 | ROTATIONAL SUPPORT OF A WIND TURBINE BLADE - The invention resides in an assembly for rotationally supporting a wind turbine blade ( | 06-12-2014 |
20140271204 | Tiltrotor Control System With Two Rise/Fall Actuators - A rotor system for rotor aircraft comprises a rotor hub comprising a plurality of rotor blades, a rotatable rotor mast coupled to the rotor hub, a swashplate assembly comprising a non-rotating ring engaged with a rotatable ring, a plurality of pitch links mechanically coupling the rotatable ring to the plurality of rotor blades, and a swashplate actuator system. The rotatable ring is configured to rotate with the rotor mast, and the non-rotating ring is configured to engage and guide the rotatable ring. The pitch links are configured to control the pitch angle of each rotor blade. The swashplate actuator system consists of: a first actuator and a second actuator, where the first actuator and the second actuator are mechanically coupled to a stationary surface and the non-rotating ring. | 09-18-2014 |
20150050148 | ROTOR BLADE CONTROL DEVICE - A rotor blade control device for a helicopter, comprising a swash-ring, said swash-ring comprising a non-rotating component of the swash-ring, coupled in a non-rotatable manner to the helicopter, a rotating component of the swash-ring, at least three actuators disposed around a rotor shaft axis of the helicopter, a coupling means between the actuators and the non-rotating component of the swash-ring. The coupling means can be adjusted in terms of its pitch, for changing the position of a swash-ring coupling point on the non-rotating component of the swash-ring along the rotor shaft axis by the actuator, by means of a control shaft, in order to adjust the rotor blades. The coupling means has a pushing member, in addition to at least one lever non-rotatably connected to the control shaft, which is connected at a first end to the lever in a rotational joint, such that it can pivot about a pivotal axis, and is coupled at a second end to the non-rotating component of the swash-ring at a swash-ring coupling point, in a ball joint. | 02-19-2015 |
20160083077 | SINGLE BLADE PROPELLER WITH VARIABLE PITCH - An improved performance propeller employs a single propeller blade having an axis of rotation and a centripetal force about the axis. A pitch control unit is mounted opposite the single propeller blade and has a compensating centripetal force with respect to the single propeller blade about the axis.. | 03-24-2016 |