Abstract: A fan component and a fan lamp assembly, wherein the fan component includes a blade mounting disc and a plurality of fan blades, one side of the blade mounting disc away from the fan blades is provided with planetary gears synchronously rotating with corresponding fan blades and a solar gear capable of rotating relative to the blade mounting disc, a peripheral surface of the solar gear is provided with first spring mounting structures, the blade mounting disc is provided with a second spring mounting structures, a return tension spring is connected between each pair of the first spring mounting structures and the second spring mounting structures, and each return tension spring is arranged on a circumferential outside of the solar gear.

Abstract: An active folding wind turbine capable of resisting severe typhoons is provided. Each wind turbine blade includes an upper blade part and a lower blade part that are hinged to each other by a hinge device. A motor transmission system is installed in the lower blade part, is connected to the hinge device in a transmission manner, and can drive the upper blade part to rotate relative to the lower blade part through the hinge device, so that the wind turbine blade is bent. When the upper blade part rotates to an end of a travel, a blade tip of the upper blade part is propped against an upper end of the lower blade part of an adjacent wind turbine blade. A winch is built in an upper portion of the lower blade part of the wind turbine blade, and is provided with a cable.

Abstract: A vertical lift rotor propulsor assembly comprises a boom having a casing with a casing profile and a first propeller blade having a blade profile that corresponds substantially to at least a portion of the casing profile of the casing of the boom. A drive mechanism is at least partially housed within the boom and at the first propeller blade is rotatably mounted to the drive mechanism to be driven thereby. The drive mechanism is to operationally move the first propeller blade between a stowed position in which the first propeller blade is substantially flush with the casing of the boom, and a deployed position in which the first propeller blade is extended a determined distance from the casing of the boom.

Abstract: A rotor blade attachment assembly for use with a rotor hub to which a rotor blade assembly is connected includes a hub extender having an inboard end and an outboard end. The inboard end of the hub extender is configured to form a connection with the rotor hub. A blade fold axis about which the rotor blade rotates relative to the rotor hub is defined at the connection. An inboard bearing is mounted within an interior of the hub extender adjacent the inboard end and an outboard hearing is mounted within the interior of the hub extender adjacent the outboard end. A tension torsion strap is operably coupled to the inboard bearing and the outboard bearing.

Abstract: A mechanism for folding a rotor blade that is rotatably coupled to a blade cuff about a blade-fold axis between an extended position and a folded position. The mechanism includes a swash plate configured to translate relative to a mast, a pitch link rotatably coupled to the swash plate, a pitch horn rotatably coupled to the pitch link, a crank coupled to the pitch horn, and a link rotatably coupled to the crank and rotatably coupled to the rotor blade. The pitch horn and the crank being configured to commonly rotate relative to the blade cuff about a crank axis in response to translation of the swash plate, wherein the crank axis passes through the blade cuff.

Abstract: An aerial vehicle is described herein. The aerial vehicle includes a lift mechanism that includes a rotor blade assembly coupled to a motor assembly. The rotor blade assembly includes a plurality of rotor blades that are pivotably coupled to a rotor blade clamping mechanism. The rotor blade clamping mechanism includes an upper paddle clamp that is coupled to a lower paddle clamp. The upper paddle clamp includes a center protrusion and a plurality of blade support protrusions extending outwardly from the lower outer surface. The center protrusion includes a center shaft aperture sized and shaped to receive a motor shaft therein. Each blade support protrusion is sized and shaped to be inserted through a corresponding positioning aperture of a corresponding rotor blade. The lower paddle clamp includes a central recess to receive the center protrusion therein and a plurality of blade recesses to receive a corresponding blade support protrusion therein.

Abstract: A folding rotor blade assembly includes a blade fold support and a blade-fold actuator system coupled to the blade fold support. The blade-fold actuator system includes a motor, a tab configured to selectively prevent rotation of a blade tang of a rotor blade, and a cam connected to the blade fold support and coupled to the motor, the cam configured to move the tab between a locked position that prevents rotation of the blade tang and an unlocked position that permits rotation of the blade tang.

Abstract: A method of blade fold for a tiltrotor aircraft includes configuring the tiltrotor aircraft in a flight ready position with a rotor system in an inverted-Y position, unlocking a first rotor blade of the rotor system to permit the first rotor blade to pivot relative to a yoke of the rotor system, restraining the first rotor blade to allow the first rotor blade to pivot relative to the yoke as the yoke is rotated, rotating the rotor system in a first direction so that the first rotor blade pivots closer to a second rotor blade, rotating the rotor system in a second direction to orient the rotor system into a modified inverted-Y position, unlocking a third rotor blade to allow the third rotor blade to pivot relative to the yoke as the yoke is rotated, and rotating the rotor system in the second direction so that the third rotor blade pivots closer to the second rotor blade.

Abstract: A rotor blade locking assembly for locking a rotor blade in a deployed position. The rotor blade locking assembly comprises a locking mechanism configured to be coupled to a blade grip. The locking mechanism comprises a latch and an actuator configured to cause the latch to move between an unlocked position and a locked position. The assembly comprises a locking plate configured to be coupled to the rotor blade. The locking plate comprises a bearing surface configured to bear against a contact surface of the latch, when the latch is in the locked position.

Abstract: A folding rotor blade assembly for an aircraft a yoke, an inboard beam coupled to the yoke, an inboard centrifugal force bearing coupled to the inboard beam, a grip coupled to the inboard beam, an outboard bearing housing coupled to the grip, and a rotor blade pivotally coupled to the grip by a blade fold bolt that is positioned outboard of the outboard bearing housing.

Abstract: A rotor blade rotated about a rotor hub is provided including a first section configured to mount to the rotor hub. The first section includes a spindle and an inboard torque tube surrounding a portion of the spindle. A second section of the rotor blade includes a flexbeam and an outboard torque tube attached to and surrounding the flexbeam. An inboard end of the flexbeam is rotatable coupled to a first end of the spindle. The second section is configured to rotate about a blade axis between an aligned position and a rotated position. A transitional brace configured to surround a portion of the rotor blade adjacent the coupled flexbeam and spindle is movable between a first position and a second position. When in the first position, the transitional brace limits movement of the second section about the blade axis.

Abstract: A linkage assembly configured for use on a rotor blade having a first section and a second section, the second section being configured to rotate about a blade fold axis between an aligned position and a rotated position relative to the first section is provided. The linkage assembly includes a bracket having a first portion rotatably coupled to the first section about the blade fold axis and a second portion mounted to the second section. A spacer assembly is positioned between the bracket and an adjacent wall of the second section. The overall thickness of the spacer assembly is adjustable to control a distance between the second section and the bracket to adjust the rotated position.

Abstract: A hybrid VTOL/high speed aircraft may comprise systems and functions for in flight configuration changes from high lift helicopter or VTOL mode to fixed or swing-wing high speed aircraft mode to accommodate a variety of functions or missions.

Abstract: An apparatus for chordwise folding and locking of rotor systems includes a grip assembly and a harness disposed at least partially within and coupled to the grip assembly. A rotor blade is rotatably coupled to the grip assembly and the harness. The rotor blade has a radially extended orientation and a stowed orientation. A linkage assembly has a first end, a second end and a pivot joint therebetween. The first end of the linkage assembly is rotatably coupled to the harness and the second end of the linkage assembly is rotatably coupled to the rotor blade. A first lock assembly selectively secures the rotor blade to the grip assembly and the harness when the rotor blade is in the radially extended orientation. A second lock assembly selectively secures the rotor blade relative to the harness when the rotor blade is in the stowed orientation.

Abstract: A pin configured for use in a rotor blade movable between an aligned position and a folded position and having a rotor blade airfoil contour is provided including a cylindrical body configured to couple a first section and a second section of the rotor blade when the rotor blade is in the aligned position. A handle is mounted to an end of the cylindrical body and has an airfoil contour complementary to the rotor blade airfoil contour. The handle is movable between an open position and a closed position. When the handle is in the closed position, the handle is flush with an adjacent portion of the rotor blade. When the handle is in the open position, the handle is accessible to pull the cylindrical body from the first and second section s of the rotor blade.

Abstract: A hybrid VTOL/high speed aircraft may comprise systems and functions for in flight configuration changes from high lift helicopter or VTOL mode to fixed or swing-wing high speed aircraft mode to accommodate a variety of functions or missions.

Abstract: A blade attachment (1, 20) for a bearingless main rotor of a helicopter with an airfoil blade (2), a flexbeam (3, 21) including a flexbeam body (16, 17) and a flexbeam head (13) at an end of the flexbeam body (16, 17). A control cuff (4, 22) encloses and extends along at least a predominant portion of the flexbeam (3, 21). A separable junction arrangement between the flexbeam head (13), the control cuff (4, 22) and the root end of the airfoil blade (2) is mechanical with removable fasteners. The removable fasteners comprise a main bolt (7) and at least one supporting bolt (8).

Abstract: A device (20) for folding a blade (5), the device comprising a fitting (30) and a cuff (50) connected to said fitting (30). The fitting (30) has at least one horizontal pin axis (31) perpendicular to a radial direction (AX2) and a clevis (35) axially offset relative to the horizontal pin axis (31) in the radial direction (AX2). The cuff (50) has an insert (51) inserted in said clevis (35), a vertical pin (70) passing through said clevis (35) and said insert (51). The cuff (50) includes at least one horizontal fastener pin axis (55) axially offset relative to said insert (51) along the radial direction (AX2), at least one lateral arm (80) connects said horizontal pin axis (31) to said fastener pin axis (55).

Abstract: An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.

Abstract: A Magnus rotor comprising a support that is arranged inside the Magnus rotor, a rotor that rotates about the support during operation of the Magnus rotor, a bearing that supports the rotor on the support, and a shaft that penetrates the bearing and is connected to the rotor above the bearing.

Abstract: An aerodynamic blade attachment (1) for a bearingless rotor, particularly a main rotor, of a helicopter, comprising: an airfoil blade (2) having a tip end and a root end and having a pitch axis from said tip end to said root end; a flexbeam (3); a control cuff (4, 22) enclosing and extending along said flexbeam (3) and a separable junction arrangement between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Said junction arrangement is mechanical between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Removable fasteners (5, 6) connect said root end of said airfoil blade (2) and said control cuff (4) with said flexbeam (3). Said junction arrangement comprises fairing means (10, 27, 28, 31, 32 and 39) encompass the removable fasteners (5, 6) and said flexbeam (3).

Abstract: Each propulsion unit of the drone comprises a propeller (20) and a rotary-cage synchronous electric motor whose stator is connected to the drone body. The propulsion unit in of the gearless type, the rotor of the motor being rotationally integral with the propeller hub (24). The rotor is integral with an upper flange (56) extending in a radial plane with respect to the axis of rotation. Reversible means are provided for the fast coupling of the propeller to the rotor, implementing studs (62) with an enlarged head (66) formed on the flange, which cooperate with homologous curvilinear buttonholes (32) formed on the hub. The switching from the decoupled position to the locked position is operated by relative rotation of the propeller hub with respect to the flange by a fraction of a turn, in an opposite direction with respect to the direction of rotation of the motor.

Abstract: A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.

Abstract: A portable blower includes a casing (2) having an intake port (6) and a discharge port (7); an air passage (8) provided inside the casing (2) and connecting between the intake port (6) and the discharge port (7); a blower fan (17) arranged inside the air passage (8); a filter (16) arranged at the intake port (6); and a lid portion (3) openably fitted to the casing (2), the lid portion (3), when open, exposing the intake port (6) and, when closed, covering the intake port (6). When open, the lid portion (3) supports the casing (2) to let it stand on a table top. As the blower fan (17) is operated, outside air is introduced through the intake port (6) into the air passage (8) so as to be sent out through the discharge port (7).

Abstract: An impeller for a pump is disclosed herein. The impeller can include a hub having a fixed end and a free end. The impeller can also have a plurality of blades supported by the hub. Each blade can have a fixed end coupled to the hub and a free end. The impeller can have a stored configuration and a deployed configuration, the blades in the deployed configuration extending away from the hub, and the blades in the stored configuration being compressed against the hub.

Abstract: The invention relates to a fluid pump, in particular liquid pump, with a rotor, with a rotor shaft (11) and with at least one rotor blade for delivering the fluid, wherein the rotor with regard to its diameter may be changed between a first, compressed condition, and a second expanded condition, wherein the at least one rotor blade comprises at least two erection elements (12, 13, 14) which are distanced to one another along the longitudinal axis (18) of the rotor shaft (11) and which project away from the shaft in the expanded condition of the rotor, as well as at least two limp rib elements (25, 26, 27, 28, 29, 30) which run at a distance to one another from one erection element (12, 13, 14) at least up to a further erection element, wherein a limp membrane (10) is held between the rib elements, which is tautened in the expanded condition of the rotor.

Abstract: A rotating fan with a transmission mechanism and a blade deployment mechanism. In an energized state, an electromagnetic coil generates a magnetic force that causes a clutch plate to be in contact with a contact surface, thereby engaging a planetary gear system. In a de-energized state, the clutch plate is not in contact with the contact surface, thereby disengaging the planetary gear system. In a deployed configuration, a drive link activated by the planetary gear system rotates a blade link to cause a fan blade to pivot. The result is that the fan blade tip is farther from the motor shaft than the fan blade root. In a retracted configuration, the drive link rotates the blade link to cause the fan blade to pivot and retract. The result is that the fan blade tip is equidistant from the motor shaft as the fan blade root.

Abstract: A retractable rotor blade for a flying vehicle is configured to undergo extension and retraction movement and includes an interlink assembly, a helical ribbon assembly for reinforcing the interlink assembly, and a flexible and elastic sleeve configured to cover the interlink assembly and the helical ribbon assembly in the extended and retracted states of the rotor blade. The interlink assembly has interconnected link base subassemblies each configured to be translated along a span of the rotor blade such that each subsequent link base subassembly becomes stacked one atop the other while remaining connected to a next link base subassembly. Each of the link base subassemblies has a damper configured to dampen movement of the interlink assembly during extension and retraction of the rotor blade.

Abstract: There is provided a combined ceiling fan and light fitting (10) having blades (1-4) that when the ceiling fan is not in use retract and are stowed above an enclosure (12) containing a light emitting device and that when the fan is in use are extended under centrifugal force. The blades are formed in such a way as to both stow compactly above the enclosure and provide reasonable aerodynamic performance. Each blade partially overlies a neighbouring blade when in its stowed position and the blades are so formed as to permit such stacking while limiting the overall height of the assemblage of stowed blades.

Abstract: A combined ceiling fan and light fitting (fan/light) having folding fan blades is provided. The fan light has a blade support arranged to be rotated by an electric motor, with blades being secured to the blade support, a root end of each blade being pivotable between folded and operative positions about a blade pivot axis fixed in the blade support. In one aspect of the invention, an improved mechanism is provided for synchronizing movement of the blades. This uses a sun gear mounted to the blade support and arranged to mesh with planet gears that rotate about the blade pivot axes. In addition improvements are provided to blades and blade mounting arrangements that balance compact folding of the blades and good air moving effectiveness.

Abstract: There is provided a combined ceiling fan and light fitting (10) having blades (1-4) that when the ceiling fan is not in use retract and are stowed above an enclosure (12) containing a light emitting device and that when the fan is in use are extended under centrifugal force. The blades are formed in such a way as to both stow compactly above the enclosure and provide reasonable aerodynamic performance. Each blade partially overlies a neighboring blade when in its stowed position and the blades are so formed as to permit such stacking while limiting the overall height of the assemblage of stowed blades.

Abstract: A hydraulic system for a ram air turbine includes a hydraulic pump having a high pressure fluid outlet port, a housing, a pivot post arranged to pass through the housing and defining a mechanical pivot relative to the housing about an axis, a transfer tube positioned between the high pressure fluid outlet port of the hydraulic pump and a port in the housing for the high pressure fluid outlet path, and seal elements positioned at or near opposite ends of the transfer tube. A fluid inlet path and a high pressure fluid outlet path pass through the housing and the pivot post. The transfer tube has a crowned end.

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 disclosed ram air turbine assembly includes a movable support structure that is prevented from moving to a stowed position by a stow abort mechanism that prevents movement to the stowed position when the turbine is not in a desired orientation.

Abstract: A retractable rotor blade for a flying vehicle includes an interlink assembly having interconnected link base subassemblies, a helical ribbon assembly reinforcing the interlink assembly, and a flexible and elastic sleeve that covers the interlink and helical ribbon assemblies in extended and retracted states of the rotor blade. Each link base subassembly has a damper for dampening movement of the interlink assembly during extension and retraction of the rotor blade, a pair of retractable links by which the link base subassembly is interconnected with another of the link base subassemblies, a link hub, and a pair of locking arms housed in the link hub for locking the rotor blade in the extended state. The helical ribbon assembly has sequentially overlapped ribbons helically wound around the interlink assembly. The flexible and elastic sleeve has a flexible and elastic skin and elastic ribs for imparting rigidity to the flexible and elastic skin.

Abstract: A rotating fan with a transmission mechanism and a blade deployment mechanism. In an energized state, an electromagnetic coil generates a magnetic force that causes a clutch plate to be in contact with a contact surface, thereby engaging a planetary gear system. In a de-energized state, the clutch plate is not in contact with the contact surface, thereby disengaging the planetary gear system. In a deployed configuration, a drive link activated by the planetary gear system rotates a blade link to cause a fan blade to pivot. The result is that the fan blade tip is farther from the motor shaft than the fan blade root. In a retracted configuration, the drive link rotates the blade link to cause the fan blade to pivot and retract. The result is that the fan blade tip is equidistant from the motor shaft as the fan blade root.

Abstract: An embodiment of Vertical Axis Wind Turbine (VAWT) concept with vanes coupled to central shaft thorough supports that are connected in such a way that vanes can be moved closer or further away from the central shaft of the wind turbine. The rotational speed of the wind turbine can be regulated by adjusting the distance of the vanes. Additionally, the turbine can be put into storm protection mode by bringing the vanes right next to the central shaft where the profile of the wind turbine is reduced to minimum.

Abstract: A combined ceiling fan and light fitting (fan/light) (1) having folding fan blades (12) is provided. The fan light (1) has a blade support (13) arranged to be rotated by an electric motor (6), with blades (12) being secured to the blade support (13), a root end of each blade (12) being pivotable between folded and operative positions about a blade pivot axis-(14) fixed in the blade support (13). In one aspect of the invention, an improved mechanism is provided for synchronizing movement of the blades. This uses a sun gear (16) mounted to the blade support and arranged to mesh with planet gears (17) that rotate about the blade pivot axes (14). In addition improvements are provided to blades (12, 33, 60) and blade mounting arrangements that balance compact folding of the blades (12, 33, 60) and good air moving effectiveness.

Abstract: A fan device having simultaneously foldable blades includes a rotatable driving unit. A plurality of supporting frames extend outwardly from the driving unit, each supporting frame has a pivot mounted on one end thereof. A plurality of shells are respectively mounted on the supporting frames, each shell has a center hole defined therein. A plurality of blades are respectively disposed on the shells. Each blade has an assembling portion disposed thereon. Each assembling portion has a through hole defined therein. A plurality of coupling rods respectively positioned between every two adjacent shells. When the driving unit rotates, the shells synchronously rotate and driving the coupling rods to be moved for simultaneously driving the blades to retractably fold/unfold.

Abstract: A blade system and method of use for a wind turbine to produce electrical power. The system has a vertical rotor shaft coupled to an anchor pad and supports a horizontal blade arm. A blade assembly having a rotatable flap is coupled to the blade arm. The flap captures the wind which causes the rotor shaft to rotate and generates electrical power from an electrical generator.

Abstract: A disc rotor blade retraction system includes a main blade spar incorporating a hydraulic cylinder and having a screw thread, A ball screw is concentrically carried within the main blade spar and is operably connected to a ball nut which has an outboard end connected to an intermediate spar with a hydraulic piston received for reciprocation in the hydraulic cylinder. A first geared actuator engages the ball screw and a second geared actuator engages the main blade spar screw thread. A hydraulic fluid accumulator providing pressurized hydraulic fluid is connected to an outboard end of the hydraulic cylinder and a controller actuates the first and second geared actuators.

Abstract: A rotor yoke includes a blade attachment portion, a mast attachment portion, and an intermediate portion extending between the blade attachment portion and the mast attachment portion. The intermediate portion, the blade attachment portion, and the mast attachment portion define an optional inner edge, such that the inner edge, if present, defines an opening. The rotor yoke further includes a peripheral, outer edge extending about the blade attachment portion, the intermediate portion, and the mast attachment portion. At least one of the outer edge and the inner edge, if present, includes a reduced thickness portion exhibiting a thickness that is less than a thickness of an adjacent portion of the rotor yoke.

Abstract: An overhead fan system of a building comprises a ceiling fan underneath a nearby fire sprinkler head. The ceiling fan has particularly low fan solidity to minimize the fan obstructing the spray of water from the sprinkler head. To further reduce the obstruction, some example fans include fan blades that automatically retract in the event of a fire.

Abstract: A blade assembly for a ceiling fan includes a mounting arm, a bearing, a cover, a spiral spring, a blade, and three screws. The mounting arm has a plate. The plate has a boss. The boss has a split. The bearing is sleeved on the boss. The cover has a stub. The stub has a receiving recess for receiving the bearing. The cover has a through hole for passing the boss. The cover has three bosses. The spiral spring has one end sleeved on the boss of the cover and the other end engaged with the split. The blade has three mounting holes and corresponding to the boss of the cover. The three screws pass through the mounting holes and fasten with the bosses of the cover.

Abstract: A fan comprising: a housing unit; a retractable fan blade; and a means for driving the retractable fan blade from a retracted position within the housing unit to an extended position exterior to the housing unit.

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 blade assembly for a ceiling fan includes a mounting arm, a bearing, a cover, a spiral spring, a blade, and three screws. The mounting arm has a plate. The plate has a boss. The boss has a split. The bearing is sleeved on the boss. The cover has a stub. The stub has a receiving recess for receiving the bearing. The cover has a through hole for passing the boss. The cover has three bosses. The spiral spring has one end sleeved on the boss of the cover and the other end engaged with the split. The blade has three mounting holes and corresponding to the boss of the cover. The three screws pass through the mounting holes and fasten with the bosses of the cover.

Abstract: In the absence of centrifugal force produced during rotation of helicopter blades, damage may result if a blade is rotated upward by wind or other forces. Lock units removably appended between the rotor assembly and each blade pitch housing attached to a helicopter blade are usable to restrict upward rotation. A base portion of a lock unit may be configured to be held in position by a removable pin device. An extendible device extending from the base portion to a surface of a blade pitch housing can be adjusted to press the base portion back against a surface of the rotor assembly. The lock unit thereby restricts these surfaces of the blade pitch housing and rotor assembly from moving closer to each other and thereby restricts upward rotation of the blade pitch housing and its attached helicopter blade. The lock units are readily removable in preparation for returning a helicopter to active use.

Abstract: The invention relates to a rotorcraft rotor comprising a hub and at least two blades hinged relative to the hub about respective pitch axes and about respective flap axes, and about respective lag axes; each blade is secured to a respective pitch lever; the rotor includes a respective pitch control rod connected to each pitch lever by a first ball joint, and a common lag damper system centered substantially on the axis of rotation of the rotor and connected to each of the blades; the damper system is secured to a respective lateral projection from each blade via a respective second ball joint that is sufficiently close to the first ball joint connecting the pitch rod to the pitch lever for the lag damper system to be relatively insensitive to flap oscillations of the hinged blades.

Abstract: A variable pitch fan blade mechanism, particularly well suited for automotive applications, wherein the blade pitch is compliantly responsive to selective actuation of a linear actuator. A linear actuator is disposed in the fan shaft composed of an electric drive component drivingly engaged with a follower component, a set of fan blades resiliently attached to a head of the follower component, and a push assembly connected to the fan shaft composed of a push plate and a plurality of push rods, one push rod for each fan blade. Each push rod engages its respective fan blade adjacent an edge thereof. The fan blades are resiliently biased toward the push rods such that axial movement of the push rods in response to actuation of the linear actuator results in compliant changes of pitch of the blades.