Abstract: Embodiments are directed to a rotor hub assembly comprising a yoke configured to attach rotor blades thereto, a single Hooke's joint configured to attach to, and transmit forces between, a mast and the yoke, and a spherical bearing coupled between the yoke and the mast. Two pillow blocks couple the single Hooke's joint to the yoke. An adapter sleeve is attached to the pillow blocks and is positioned to surround the spherical bearing. The adapter sleeve extends between the single Hooke's joint and the mast. A hub lock extension is attached to the yoke. The hub lock extension is configured to receive a hub lock that prevents gimballing of the yoke when engaged.

Abstract: A rotor assembly for use in an aircraft comprising has a rotor hub, a spinner structure comprising a spinner opening, and a rotor blade received through the spinner opening. The rotor blade has a rotor root located proximate to the rotor hub. The rotor assembly also has a motive fairing face that at least partially rests along the rotor hub.

Abstract: A rotorcraft includes a main rotor system coupled to a mast and a rotor assembly. The rotor assembly includes a yoke comprising a rotor coupling, a first damper mount attached to the rotor coupling, a rotor extension configured to couple to the rotor coupling and comprising a second damper mount, a damper coupled to the first and second damper mounts, and a fairing enclosing the damper and the yoke.

Abstract: The present invention provides a new system that allows a safer operation of a moving object. The present invention provides a moving object operation system (1) including: a moving object (11); a plurality of operation signal transmitters (12A, 12B) for the moving object; and a synchronization unit (13). The moving object (11) includes: a signal receipt unit (111) that receives operation signals from the operation signal transmitters (12A, 12B). The operation signal transmitters (12A, 12B) include signal transmission units (121A, 121B) that transmit the operation signals to the moving object (11), respectively. The synchronization unit (13) is a unit that synchronizes the operation signal transmitters (12A, 12B).

Abstract: A rotor assembly for an aircraft is operable to generate a variable thrust vector. The rotor assembly includes a mast that is rotatable about a mast axis. A ball joint is positioned about and non rotatable with the mast. A tilt control assembly is positioned on and has a tilting degree of freedom relative to the ball joint. The tilt control assembly is non rotatable with the mast. A rotor hub is rotatably coupled to the tilt control assembly. The rotor hub is rotatable with the mast in a rotational plane and tiltable with the tilt control assembly. The rotor hub includes a plurality of grips each coupled to a rotor blade. Actuation of the tilt control assembly changes the rotational plane of the rotor hub relative to the mast axis, thereby generating the variable thrust vector.

Abstract: Embodiments are directed to obtaining data from a plurality of sensors located on a rotorcraft, wherein a first plurality of the sensors is associated with a hub of the rotorcraft and a second plurality of the sensors is associated with blades of the rotorcraft, processing the data to isolate blade dynamics using the data from the sensors associated with the blade from rotorcraft maneuvering dynamics using the data from the sensors associated with the hub, obtaining at least one parameter associated with the blade dynamics based on the processing, and analyzing the at least one parameter to control at least one of the rotorcraft and the blades.

Abstract: A mechanism in a teetering rotor head that has an actuating shaft with a carrier, in a hollow spindle, in a hollow central tower, with teetering sidewalls and with rotor blade anchor blocks bolted between them, and with blade root anchor bolts that turn with the blades, connected by 4 short straight levers and 2 sliding plates that work together to turn the bolts and twist the blades, changing the pitch.

Abstract: A wind turbine variable is controlled by detecting air flow conditions in front of the leading edge of the blade. One or more Laser Doppler Anemometers are mounted on or incorporated into the blade to determine air flow velocity in the region in front of the leading edge of the blade. The measured flow conditions may be used to control the position of a control surface such as a trailing edge flap or the rotor speed. The LDAs may comprise lasers of different frequencies to enable more than one component of flow velocity to be measured.

Abstract: A rotor system includes a lead stop mounted to a spindle and a lead stop plate mounted to a rotor hub arm, the lead stop operable to contact the lead stop plate over a lead angle range.

Abstract: A rotor system has a rotor, an axis of rotation about which the rotor may be rotated, a linkage system having a first adjustable length portion and a second adjustable length portion, wherein the second adjustable length portion is configured to provide a relatively finer adjustment of an overall effective length of the linkage system as compared to the first adjustable length portion and wherein the rotor is configured to rotate about the axis in response to changing the overall effective length of the linkage system.

Abstract: A hydraulic blade speed control apparatus and method. The apparatus includes a rotor assembly comprising a shaft; a first blade assembly pivotably attached to the shaft at a first initial position; a second blade assembly pivotably attached to the shaft assembly at a second initial position opposite to the first initial position; and a hydraulic movement mechanism. An initial angle of 180 degrees exists between the first blade assembly with said respect to the second blade assembly. The rotor assembly is configured to rotate the first blade assembly and the second blade assembly in a first direction and a second direction opposite to the first direction. The hydraulic movement mechanism is configured to pivotably move the first blade assembly in different angular positions with respect to the rotor assembly and the second blade assembly.

Abstract: A torque coupling (13) for a rotor head (11) of a rotary-wing aircraft has upper and lower plates (29, 31) configured for rotation with a rotor mast (19). Drive links (33) pivotally connected to the upper and lower plates (29, 31) pivot about a pivot axis generally parallel to and radially offset from an axis of rotation of the plates. Each link (33) is engaged with adjacent drive links (33) to form a continuous ring of links, such that motion of one link (33) about its pivot axis causes motion in an opposite direction of each adjacent link (33) about its pivot axis. Drive elements (25) connect the drive links (33) to an assembly configured to receive rotor blades. The drive elements (25) may be components of a universal joint, a multiple trailing-link configuration, a pad-bearing configuration, or another type of articulating assembly.

Abstract: A rotor blade for a bearingless rotor of a rotorcraft includes a flapwise-flexible and lead-lag-flexible rotor blade attachment region, an inner rotor blade segment, and an outer rotor blade segment. The inner rotor blade segment includes a blade root region and an aerodynamically effective rotor blade profile having a front profile region and a rear profile region relative to a blade depth direction. The front profile region includes a spar disposed in the blade root region and extending in the blade radius direction, the front profile region and spar embodied as a torsionally flexible hollow body in a region of the inner rotor blade segment, and the rear profile region being torsionally stiff. The front profile region and the rear profile are separated by a separation distance in the inner rotor blade segment. The torsional flexibility of the front profile region and the separation distance decreases with increasing blade radius in the inner rotor blade segment.

Abstract: A rotorcraft, such a helicopter or a tiltrotor aircraft, includes a light emitting device configured to provide light at a tip of a rotor blade. The light emitting device includes a light emitting diode arranged on the rotor blade, and a power source, wherein the power source is configured to power the light emitting diode due to a movement of the rotor blade. The power source may include a piezo-electric material configured to create a voltage due to movements of the rotor blade or an electrical generator including a stationary magnet assembly and a moveable coil assembly arranged on a shaft that rotates the rotor blade.

Abstract: A rotor assembly having a rotor hub, a plurality of yokes, and a plurality of swing arms is provided. The yoke depending from the rotor hub. Each swing arm is movably positioned on the rotor hub for rotation between an unlocked position and a locked position. The yokes are freely movable about a pitch axis and a lead/lag axis when the swing arms are in the unlocked position and the yokes are locked in a predetermined pitch position and a predetermined lead/lag position when the swing arms are in the locked position.

Abstract: A main rotor is provided for use in a rotary winged model aircraft. The main rotor includes a rotor hub assembly rotatable about a vertical axis and at least two main rotor blades. Each of the main rotor blades extends in a radial direction from the rotor hub assembly. The main rotor blades each include a tip end positioned to lie in spaced-apart relation to the rotor hub assembly and a root end coupled to the rotor hub assembly for pivotable folding movement from an initial horizontal position perpendicular to the vertical axis about a horizontal axis through a desired folding angle of about 90.degree.. Forces transmitted to the rotor hub by the rotor blade during a crash-landing of a rotary winged model aircraft including the main rotor are minimized due to movement of the rotor blades through the desired folding angle.

Abstract: This invention relates to helicopter rotors having three or more blades and of the type having a hollow rotor drive shaft and a control column positioned within the hollow shaft arranged to support a spider assembly at its upper end through which control movements are transmitted to the rotor. In the present invention, the inner ends of at least two of the arms of the spider are retained in fixed relationship and the outer end of each arm is connected to its respective feathering hinge through a vertical pivot located on an axis at an operational radius not greater than a radius of a point about which blade lead/lag movements occur. This arrangement serves to establish a virtual floating fulcrum about which the control column is tilted during operation to impart control movements, and thereby eliminates the complicated mechanical support means that are a feature of prior rotors of this type.