Abstract: An example rotating swashplate ring to rotor mast connection includes a polygon-shaped drive tube secured to the rotor mast and a gimbal joint connected between the rotating swashplate ring and the polygon-shaped drive tube, wherein the gimbal joint rotates with the rotor mast and can translate axially along the polygon-shaped drive tube.

Abstract: The present invention includes a rotor hub system, comprising: a teetering rotor hub disposed about a mast, the teetering rotor hub comprising: a first and a second yoke; each connected to a set of rotor blades, wherein the second set of rotor blades and the first set of rotor blades are disposed in a common plane, but the first and the second yoke do not come in contact.

Abstract: A pitch bearing assembly for a wind turbine having a stiffener is disclosed. The pitch bearing assembly may include an outer race and an inner race rotatable relative to the outer race. The inner race may define a mounting surface and an inner circumference. The mounting surface may extend generally perpendicular to the inner circumference. In addition, the stiffener may include a body and a mounting flange. The body may extend axially within a volume defined by the inner circumference of the inner race. Further, the mounting flange of the stiffener may be coupled to the mounting surface of the inner race.

Abstract: A wind turbine includes rotor blades pivotably mounted in a gondola such that the pitch of the blades is adjustable, and pitch adjustment mounted coaxially and pivotably on the rotor axle such that the pitch adjustment are rotatable relative to that axle. The gondola is furthermore connected via torsion positioning to the axle, such that it can rotate relative to the pitch adjustment to adjust the pitch of the rotor blades. The wind turbine may also include a cable for each rotor blade, which are each with one end connected to the blade and with their opposite end to the rotor axle, such that the blades are supported by the cables against movement in the radially outward direction.

Abstract: This disclosure is directed to a single blade propeller and systems, devices, and techniques pertaining to assisting in critical stages of flight (e.g., takeoff, landing, emergency situations, etc.) in vertical takeoff and landing (VTOL) aircraft. The single blade propeller may be incorporated into fixed and rotary wing VTOL aircraft as part of a first propulsion system. The first propulsion system may include one or more single blade propellers driven by electric motors, combustion engines, and/or hybrid engines. Each of the single blade propellers may include a lift-producing blade and a counterweight opposite the lift-producing blade. As each of the single blade propellers spins, it may produce lift in a direction approximately perpendicular to the horizon to effect vertical flight.

Abstract: The present application includes a blade-pitch control system for controlling a pitch angle of each of a plurality of blades on an aircraft rotor. A feedback lever associated with each blade is pivotally mounted to the rotating portion of a swashplate assembly. A pitch link connects an output arm of a lever to a pitch horn of a corresponding blade, and a feedback link connects the input arm of the lever to a yoke. Flapping motion of the yoke causes motion of the feedback link, and this motion causes corresponding rotation of the lever. Rotation of the lever causes motion of the pitch link, which changes the pitch angle of the attached blade. This provides for selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the blades.

Abstract: The present application includes a main rotor assembly for an aircraft. The rotor assembly has a main rotor mast configured for rotation about a mast axis and two yokes pivotally connected to the mast for rotation therewith about the mast axis. Each yoke is independently pivotable relative to the mast about at least one flap axis that is generally perpendicular to the mast axis. In at least one embodiment, a torque splitter connects the yokes and allows for limited rotation of the yokes relative to each other about the mast axis. Each yoke is configured for the attachment of rotor blades extending generally radially relative to the mast axis.

Abstract: 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.

Abstract: 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.

Abstract: A blade-pitch control system has a swashplate configured for continuous rotation with an associated rotor and mast, and at least one link connects the swashplate to each blade of the rotor. The swashplate provides for collective control of the pitch angle of the blades through selective rotation of the swashplate about a swashplate axis while the swashplate is rotating with the rotor and mast. The system can be configured to provide for cyclic control of the pitch angle of the blades through planar translation of the swashplate or through tilting of the swashplate about axes generally perpendicular to the swashplate axis.

Abstract: An omni-directional air flow device, for example, a fan or a vent associated with a fan, comprises a swivel control point providing almost a spherical range of motion of the air flow device so that air may flow in any direction. The omni-directional air flow device may comprise a user input device for receiving a program for controlling movement of the air flow device through a pre-determined path within the spherical range of motion and for controlling air flow velocity as the air flow device follows the pre-determined path. Moreover, the device may further comprise a controller and memory for storing data representing the pre-determined path and varying air flow velocities along the path. When provided with temperature and humidity sensors coupled to the processor, the processor may calculate a comfort index and adjust the pre-determined path or air flow velocity accordingly.

Abstract: A hybrid wind machine includes a fan shaft to drive a fan, and an electrical motor/generator combination, coupled to the first shaft, so as to allow the electrical motor/generator to drive the fan shaft when the wind machine is operating in a wind generating mode. Further, the coupling of the electrical motor/generator combination to the fan shaft allows the fan shaft to drive the electrical motor/generator combination as an electrical generator when the wind machine is operating in a power generating mode.

Abstract: 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.

Abstract: The present invention relates to a fan, to a method, and to a device for assembling the fan. The fan has an axis of rotation, which is connected to a dog, wherein the dog is connected to a fan wheel, wherein the dog, in a first number of contact surfaces, is in contact with additional contact surfaces of the fan wheel, wherein the dog and/or the fan wheel have more than the first number of contact surfaces and/or additional contact surfaces, wherein at least two contact surfaces have different height positions with respect to a central axis of the dog and/or the fan wheel.

Abstract: A teeter mechanism for a multiple-bladed wind turbine includes a rotor shaft operable to rotate about a first axis. A spherical member is rotatable about the first axis along with the rotor shaft. A plurality of turbine blades is mounted to a rotor hub. The rotor hub rotationally drives the rotor shaft, and is operable to teeter about the spherical member such that the rotor hub rotates about the first axis in a first position and rotates about a second axis offset from the first axis in a second, teeter position.

Abstract: The invention resides in an assembly for rotationally supporting a wind turbine blade (110) relative to a wind turbine hub (120). The assembly comprises an intermediate ring (130) having an inner annular portion and an outer annular portion provided with means for attaching the turbine blade. The intermediate ring is rotatably mounted to the hub via a first bearing arrangement. According to the invention, the first bearing arrangement comprises a radial bearing (140) and a thrust bearing, whereby the inner annular portion is mounted to the hub via the radial bearing and the outer annular portion is mounted to the hub via the thrust bearing. The thrust bearing is a plain bearing comprising first and second sliding surfaces (151, 152) which are clamped to the hub between first and second clamping members (161, 162).

Abstract: A horizontal axis wind turbine with a ball-and-socket hub is disclosed. The hub provides for a second vertical axis, the hub axis, intersecting the center of the hub that enables a change in orientation of the rotor axis without changing the orientation of the main shaft axis. The cause for the rotation around the hub axis is an imbalance in torque applied by the blades across a wind shear axis due to a gradient in wind velocity. Rotation around the hub axis will continue until back-and-forth rotation of the blades is such that the torque is balanced across a wind shear axis and the rotor axis is set at an optimal angle. As changes in wind direction occur, the torque will become imbalanced, and the hub will rotate until a new optimal angle is achieved. The present turbine design allows for the hub to freely rotate ±20° around the hub axis and continuously maintain orientation of the rotor axis at an optimal angle.

Abstract: A ram air turbine (RAT) includes a movable turbine support structure that is prevented from moving to a stowed position by a stow abort mechanism when turbine blades are not locked in a desired position. The stow abort mechanism includes a pawl that is driven by a cam on a release lever. The release lever is movable in response to a position of a release pin that prevents rotation of a turbine drive shaft from a desired orientation that locks the turbine blades in a desired position required for stowage. Disengagement of the release pin causes the stow abort mechanism to maintain a position where the pawl blocks movement to the deployed position. Engagement of the release pin to prevent rotation results in movement of the pawl to a position that provides for movement to the stowed position.

Abstract: 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.

Abstract: Wind turbine rotor comprising a hub, a plurality of blades and at least one pitch system for rotating a blade substantially along its longitudinal axis, the pitch system comprising a motor, a drive pinion, a gear arranged to mesh with the drive pinion and a pitch bearing, the pitch bearing comprising an outer bearing ring connected to the hub, an inner bearing ring connected to a blade and, between these two bearing rings, one or more rows of rolling elements which allow both bearing rings to rotate relative to each other, wherein the inner bearing ring has an inner side, and wherein a reinforcement disc is radially fixed to the inner side of the inner bearing ring.

Abstract: A fan configured for integration with a structure having at least two support members is disclosed. The fan comprises a fan guard, a fan blade surrounded by the fan guard, and first and second mounting brackets. Each of the first and second mounting brackets is configured for connection to a respective one of the support members. The fan also comprises first and second connectors oppositely disposed on the fan guard and configured for connection to a respective one of first and second mounting brackets. The first and second connectors are adjustable with respect to the first and second mounting brackets, and the fan is configured to rotate between at least two struts. Rotation of the fan between the at least two struts is limited such that an opening defined by one of the struts and said fan guard does not exceed a predetermined size.

Abstract: A blade pitch control mechanism for a propeller assembly (10) includes an actuation shaft (24) having a spherical member (28) located at a propeller axis (22). A yoke (40) is located around the spherical member (28) and is rotatable thereon about a yoke tilt axis (62) substantially perpendicular to the propeller axis (22). The yoke (40) includes a plurality of propeller blade attachments (44), each receptive of a propeller blade (14). The plurality of blade attachments (44) are configured such that rotation of the yoke (40) about the yoke tilt axis (62) results in rotation of each propeller blade (14) about a blade pitch change axis (48).

Abstract: 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.

Abstract: A rotating control system includes a member having at least one clevis defined by a pair of clevis arms disposed in a clevis plane, the at least one clevis having an axis of symmetry disposed in the clevis plane midway between the pair of clevis arms, a shaft member pivotally coupled between the pair of clevis arms, the shaft member having a shaft axis, the shaft axis disposed axially along the shaft member, and an anti-rotation device for limiting a rotation of the shaft member about the shaft axis, the anti-rotation device having a plurality of flanges configured to couple to the clevis arms of the member, the flanges extending from a surface of a base member, the anti-rotation device having at least one restraining member that protrudes toward the shaft member for limiting the axial rotation of the shaft member.

Abstract: A wind turbine and methods for controlling wind turbine thrust are disclosed. In one embodiment, the method includes measuring a tilt angle of a wind turbine in a loaded position using a measuring device. The wind turbine includes a tower, a nacelle mounted on the tower, a rotor coupled to the nacelle, and a plurality of rotor blades coupled to the rotor. The method further includes comparing the tilt angle to a predetermined tilt angle for the wind turbine and, if the tilt angle exceeds the predetermined tilt angle, adjusting a pitch of at least one of the plurality of rotor blades such that the tilt angle is less than or equal to the predetermined tilt angle.

Abstract: 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.

Abstract: 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.

Abstract: A wind energy system is provided with said wind energy system including a hub pivotable about a rotation axis, a first bearing connected to said hub, a tapered adapter, a second bearing connected to said first bearing by said adapter, wherein said first and second bearings and said adapter are arranged such that the tilt angle of said rotation axis of said hub is adjustable. Further, a tilt adjustment system for a wind energy system and a method for operating a wind energy system is provided.

Abstract: 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.

Abstract: A rotor-hub for a rotary-wing aircraft is disclosed. The rotor-hub comprises a yoke comprising a plurality of yoke arms and a plurality of yoke straps, wherein the yoke arms are joined together by the yoke straps, and wherein a plurality of inner walls of the yoke define a central void space. A pitch horn is movably connected to the yoke and a portion of the pitch horn is located within the central void space. A connecting shell is fixedly attached to the yoke.

Abstract: 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.

Abstract: 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.

Abstract: A frame for supporting equipment arranged in a hub of a wind turbine is fixed to the hub at one end and flexibly connected to the hub at another end. The variation of the relative position between the hub and the frame caused by the deformation of the hub associated with a rotation of the wind turbine or the like is absorbed by the flexible connection. A wind turbine whose frame in the hub has high durability against the rotation can be provided.

Abstract: A turbine for use with a turbine generator, the turbine including at least one turbine blade for positioning in a flowpath, a hub mounting the at least one turbine blade, and a rotatable shaft in operational communication with the hub via a hinge assembly, an axis of the hub being independent of an axis of the shaft. The hinge assembly is disposed between the shaft and the hub and configured to adjust an angle therebetween. A controller assembly is configured to adjust at least one operational characteristic of the hinge assembly during turbine operation. In one embodiment the operational characteristic is a teeter angle of the hinge assembly. In one embodiment operational characteristic is a stiffness or damping force. Methods for using and controlling a fluid turbine are also disclosed.

Abstract: A system for providing variable pitch to a rotor blade of an aircraft engine includes a rotatable hub; at least one blade mounted on the rotatable hub; a gear mechanism operably connected to the rotatable hub; a timing ring rotatably and operably connected to the gear mechanism; and a pitch arm operably connecting the timing ring and the at least one blade mounted on the rotatable hub. In the operation of the system, the gear mechanism facilitates the rotation of the timing ring to vary the pitch of the at least one blade mounted on the rotatable hub.

Abstract: 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.

Abstract: A wind energy system is provided with said wind energy system including a hub pivotable about a rotation axis, a first bearing connected to said hub, a tapered adapter, a second bearing connected to said first bearing by said adapter, wherein said first and second bearings and said adapter are arranged such that the tilt angle of said rotation axis of said hub is adjustable. Further, a tilt adjustment system for a wind energy system and a method for operating a wind energy system is provided.

Abstract: A rotor hub assembly for a rotary-wing aircraft has a central member and a plurality of blade grips adapted for attaching rotor blades to the central member. The blade grips are pivotally attached to the central member and are capable of pivoting about a pivot axis generally normal to a plane of rotation of the blades. The pivoting allows for in-plane motion of the blades relative to the central member. A damper is operably connected to each blade grip for damping the in-plane motion of the associated blade, each damper being selectively switchable between at least two spring rates.

Abstract: Methods and apparatus for continuing wind turbine operation when normal wind turbine motor control is unavailable due to overheating of one or more wind turbine control motors. Technical effects of the present invention include providing an effective control strategy continuing operation during over-heating of a wind turbine control motor, such as a pitch control motor and a yaw control motor.

Abstract: 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.

Abstract: A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading edge (202) of the main portion of the proprotor blade. The slot (215) is selectively shaped so the a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat (217) and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft (11) and civilian-type tiltrotor aircraft (111) with only minor variations to accommodate the different shapes of the proprotor blades.

Abstract: 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.

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: To provide a lightweight hub of a horizontal axis wind turbine with a balanced strength, the hub 1 related to the present invention comprises a reinforcement plate 4 coupled to the spherical shell 2 on the peripheral edge in the round region G inside the circular flange 3 used to secure a blade. In addition to being off-center at the point C side, an off-center opening 5, that contains the center B of the region G, is formed in the region G. The reinforcement plate 4 is formed at the remainder portion of the region G after removing the off-center opening 5. By means of an unequal arrangement of the reinforcement plate 4 and the opening 5 on the inside of the circular flange 3, severe imbalances due to the casting of the hub 1 are cancelled and a balanced strength is obtained, making it also easier to reduce the weight.

Abstract: A helicopter rotor transmission assembly for translating motion of a drive shaft driven by a helicopter engine into rotary motion of a helicopter rotor mast that carries rotor blades. The transmission assembly includes a fixed outer housing, an inner housing carried within the outer housing and adapted to rotate relative to the outer housing by the drive shaft, and a ball received in the inner housing so as to be rotatable relative to the inner housing about one axis, and constrained from rotation about the two orthogonal axes. The ball is adapted to receive the rotor mast so that the mast can be driven to both spin and tilt.

Abstract: A transmission gearbox (1) has a casing (2) that tilts around a tilting axis (B—B) via two bearings (19). Each of the bearings includes: a fixed part (20) having a sleeve (20a); and a trunnion (21a) which belongs to a pivoting part (21) and which pivots around the sleeve, the pivoting part being solidly connected to the casing (2). A shouldered wear ring (22) is disposed between the sleeve (20a) and the trunnion (21a) of each bearing (19). The invention is suitable for use in the pivot mounting of a power transmission gearbox (1) that is used to rotate the tilting rotor (14) of a convertible aircraft.

Abstract: A preferred embodiment of a rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft includes a gimbal mechanically coupled to the drive shaft so that the gimbal rotates with the drive shaft, and a hub pivotally coupled to the gimbal for receiving the rotor blades. The rotor head also includes an actuator mechanically coupled to the hub for causing the hub to pivot about the gimbal.

Abstract: A downstream wind turbine for converting wind energy into electrical energy. In a preferred embodiment the downstream wind turbine adapted to respond to high winds and gyroscopic precession. The downstream wind turbine comprises a support tower; a yaw bearing attached to the support tower; a support frame operably linked to the bearing; at least one swing arm with one end pivotally attached to the support frame; an elongated carry member pivotally attached to the other end of the swing arm; a wind driven energy conversion system balanced on and attached to the carry member so that the carry member is biased to maintain an approximately horizontal orientation with respect to the support frame and in response to wind proportionally swings downstream, and which responds to gyroscopic precession forces by tilting up or down; and a governor device for modifying at least one dynamic characteristic of the turbine.

Abstract: The invention is based on an axial fan with a hub region (4, 27) for connecting the axial fan with a driven shaft (20) of an electrical drive (21), whereby the axial fan is statically balanced by means of a balancing weight (26). A flexurally soft connection is formed in the hub region (4, 27) between the axial fan (1) and the driven shaft (20) of an electrical drive (21).

Abstract: This invention pertains to a horizontal axis wind turbine of down-wind design that tilts rather than teetering to overcome loads produced by gyroscopic precession. Gyroscopic precession occurs to the rotor as it is spinning when it turns to adjust to or follow a wind directional change. It is absolutely necessary to provide a means by which to overcome this phenomena as it can lead to structural failures due to it's extreme effects. Wind turbines that can not overcome these effects usually have an active yaw system that will turn them very slowly in order to not encounter the effects of the extreme loads produced by gyroscopic precession. This invention also provides a means by which to control the rotor speed based upon the using of the turbine's own weight as a basis for that control. These two functions work in unison and are immediate in their response to provide for a superior dynamic wind turbine design that will be more cost effective to produce as well as maintain.