Abstract: The device includes anti-cone stops projecting outward from at least two coaxial rings that can rotate about the rotor axis on the top face of the hub. Flyweights are each mechanically joined to one of the rings by a mechanism for driving the latter in rotation from the "ground" position, in which each anti-cone stop is facing an upper bearing shoe of the corresponding blade, to the "flight" position, in which the anti-cone stops are retracted against elastic mechanisms returning them to the "ground" position.

Abstract: A hingeless rotor including a rotor mast driven in rotation about an axis of the rotor, a hub secured in terms of rotation to the mast, and at least two blades, each of which is, firstly, joined to the hub by a root attachment part comprising at least one arm which can twist about a longitudinal pitch-change axis of the blade and, secondly, equipped with a cuff which is rigid in torsion, surrounding the at least one twistable arm, and the radially external part of the cuff, with respect to the rotor axis is secured in terms of torsion to the blade and to the twistable arm about the pitch-change axis, while the radially internal part of the cuff surrounds, without contact, the at least one twistable arm and exhibits a pitch lever projecting towards the outside of the cuff and joined to a pitch-control rod, wherein, for each blade, an intermediate pitch-control ring which is rigid in terms of torsion about the corresponding pitch-change axis, and which surrounds the corresponding at least one twistable arm is a

Abstract: The installation links a supply conductor to an electrical device for de-icing a blade using at least one cable with a first stretch linked to the supply conductor by a connector and to a second stretch with an overhead hook in the form of flattened half loop, itself linked to the device for de-icing the blade by a second connector fitted on the blade, possibly via a straight and flat third stretch and a second overhead hook. The first hook is of nonscreened structure, with an elongate part of substantially flattened rectangular transverse section and with a concavity pointing towards a device for retaining and articulating the blade on a hub.

Abstract: The installation for removing electrostatic charge and passing lightning current between a conductor of each blade of the rotor and a metallic part of the hub comprises at least one conductive member integral with the member for linking the blade to the hub in its angular deflections, and in electrical continuity with the conductor of the blade and held elastically in permanent contact with a conductive terminal integral with the hub and in electrical continuity therewith.

Abstract: A sail system for wind turbines of the vertical shaft type is disclosed. The sail system has a vertical rotating shaft, a plurality of support arms radially extending from an upper portion of the rotating shaft, and a sail pivoted to the tip of each support arm. The sail is provided with a longitudinal horizontal slit and is eccentrically pivoted to the tip of each support arm by means of a hinge. A holding rod is pivoted to an outside portion of the arm and penetrates the longitudinal slit of the sail. A spring is fitted over the holding rod between the spring stopper of the holding rod and the outer surface of the sail. The sail system not only prevents the sail from sagging due to the sail's weight, it also tightly pivots the sail to the arm regardless of the sail's configurations. The maximum turning angle of the sail relative to the arm is limited and adjusted by the spring.

Abstract: The device comprises, between two blades and their members linking them to the hub, three levers articulated by ball joints to the members and to the hub, the two levers pivoting on the third one about axes of pivoting parallel to each other and perpendicular to the common plane passing through the centres of the ball joints. At least one of the levers comprises at least one drag damper.

Abstract: A rotor hub for a rotary wing aircraft is described which allows the use of more than three blades on the rotor head while providing all of the required functional features. The rotor head is constructed using a central barrel to which is attached a plurality of blade attachment points on its exterior surface. The pitch arm actuating points are located inside of the hub barrel, extending from the outer surface into the hub barrel through arcuate slots in the barrel. The hub is particularly adapted for use with tilt rotor rotary wing aircraft and provides a negative Delta 3 blade pitch input in response to wind gusts and abrupt pilot control inputs.

Abstract: The device comprises anti-cone stops projecting outwards from a common ring that can rotate about the rotor axis on the top face of the hub and flyweights are each individually joined to the ring for driving the latter in rotation from the "ground" position, in which each anti-cone stop is facing an upper bearing shoe of the corresponding blade, to the "flight" position, in which the anti-cone stops are retracted, returning them to the "ground" position.

Abstract: Windmill (10) having a plurality of hydrodynamic, folding blades (12, 14, 16 and 18) secured to a hub (64). The blades are propelled by wind current such that the windmill rotates about a central axis of a shaft (20) on which a hub (64) is journalled. Each folding blade extends radially from the hub and includes a lower blade portion (24) attached to the hub and an upper blade portion (22) pivotally attached to the lower blade portion. The lower blade portion includes a hydrodynamic surface extending from a first edge(43) and terminating at a trailing edge (42). The upper blade portion is hydrodynamically contoured so as to form a nose cone (44). An apex of the nose cone forms a leading edge (40) of the upper blade portion that is opposite a trailing edge (41).

Abstract: A mounting assembly (50) for mechanically interconnecting a helicopter rotor blade (12) to a rotor hub assembly (10) and for mechanically interconnecting the rotor blade (12) to a damper assembly (52) and a pitch control input assembly (54). The rotor hub assembly (10) includes a hub plate (16) having a hub plate aperture (22) for mounting a rotor assembly yoke (24). The rotor assembly yoke (24) includes upper and lower radially extending arms (28a, 28b) which are disposed above and below the hub plate (16) and which include a set of mounting apertures (29) formed through the proximal end thereof. The mounting assembly (50) includes upper and lower clevis arms (60a, 60b) formed at the root end (56) of the rotor blade (12), a horn/damper fitting (64) interposed between the upper and lower clevis arms (60a, 60b), and upper and lower spacer plates (90a, 90b) disposed between the clevis arms (60a, 60b) and the radially extending arms (28a, 28b) of the rotor assembly yoke (24).

Abstract: For each blade, the cuff which is rigid in torsion, surrounding the corresponding rotor attachment twistable arm, bears two opposed pitch levers each articulated to one respectively of two intermediate connecting rods which are moreover articulated to one and the same transmission lever on either side of a pivoting link by means of which this lever pivots on a pivot secured to the rotor mast. The transmission lever is additionally articulated to the pitch-control rod at a point which is offset with respect to its pivoting link. A crossmember is articulated to the connecting rods and interacts with an assembly having a drag damper, this assembly itself being articulated to a fixed point secured in terms of rotation to the rotor mast.

Abstract: A controllable pitch propeller for application principally to sailboats employing electric auxiliary power. The design addresses a highly efficient approach to performing four basic functions desirable on sailing vessels that have electrical, or internal combustion, auxiliary power and onboard electrical systems typically employing batteries. The design employs no external nor remote actuator means; instead, blade position (nominal pitch) is inherently "controlled" by the direction of shaft rotation and whether the propeller is acting as a propulsor or a turbine. The four basic functions, or configurations, performed by the design are 1) forward propulsion, 2) reverse propulsion, 3) efficient power generation as a turbine, and 4) feathering for no-power minimum drag. The propeller includes a cambered blade configured with a cross section that would purposely act efficiently with fluid inflow impinging on either edge, depending upon the function being performed.

Abstract: This invention provides a variable pitch marine propeller which is replaceable onto the drive shaft of a marine engine and which provides an exhaust channel through the propeller. To improve and increase the flow of exhaust gas through the propeller the propeller is provided with a blade shank having a cross-sectional area perpendicular to the direction of exhaust gas flow which is less than the cross-sectional area parallel to such flow in the region of the shank arm attachment. There are also provided, within the interior of the propeller, internal surfaces formed within the blade arm adjacent the shank and defining at least one channel to allow exhaust gases to flow through the arm and counterweight assembly. In addition, the propeller is formed such that the connecting region between the blade arm and the counterweight on each blade has a reduced radial width, smaller than that of the counterweight mass along an axis parallel to the drive shaft axis and parallel to the flow of exhaust gases.

Abstract: The invention relates to a fluid device for providing high load carrying capacity in an one direction and which provides a high level of damping along a substantially perpendicular direction. This is achieved by a device which includes an inner member and an outer member and a flexible section causing a connection therebetween, said flexible section exhibiting a substantially higher stiffness along one axis, a fluid cavity formed within said device, a piston attached to one of said inner member and said outer member, said piston being substantially surrounded by, and submersed in said fluid. In one embodiment, the piston includes a piston area A.sub.p which is substantially greater than 1/2 the fluid cavity area A.sub.c. Movement of the piston within the fluid cavity causes a damping force comprising a throttling component as well as a viscous shear component. Means are disclosed for substantially increasing the viscous shear component and throttling component including novel piston concepts.

Abstract: A hybrid fluid and elastomer damper. A damper, which may be utilized as a lead-lag damper for a helicopter rotor application, reduces vibratory motion transmitted axially, torsionally and angularly between a pair of components such as a rotor and a blade by hysteresis of the elastomer and throttling and shearing of the fluid through a narrow annular passageway. The hybrid damper captures the best features of both the elastomer and fluid dampers while avoiding many of the disadvantages of each.

Abstract: The invention relates to an antivibration device comprising two rigid strength members that are parallel and perpendicular to a first axis Z, and at least one laminated element interposed between the two strength members, said laminated element being made up of alternating layers of a rigid material and of elastomer which are disposed perpendicularly to the first axis, said laminated element enabling the two strength members to move relative to each other along a second axis Y that is perpendicular to the first axis. According to the invention, the device further includes a hydraulic damper which presents at least two leakproof cavities that are deformable and that are interconnected by means of a narrow channel, the two leakproof cavities and the narrow channel being filled with a liquid, each leakproof cavity being defined, at least in part, by a deformable wall which is fixed to both of the strength members and which permits them to move relative to each other parallel to the second axis.

Abstract: A pitch adjustment assembly (100) for a bearingless rotor assembly (20) which includes a torque tube member (36) enveloping a flexbeam connector (22), which torque tube member (36) defines a geometric center (120) and is operative to impart pitch motion to the rotor blade assembly (20).

Abstract: A rotor head for a rotary wing aircraft having a plurality of rotor blades, such that each blade is coupled to the hub by an attachment assembly. The attachment assembly includes a thrust bearing device attached to the hub for allowing angular oscillations, and drag damping device coupled between the blade and the hub for damping movements of drag caused by rotation of the rotor head. The drag damping device has visco-elastic elements which are pivotable with respect to each other about a common axis. The damping device is also disposed to pivot in a flapping direction of the blade through a pivot joint.

Abstract: A hollow rotor hub is provided at the top of the rotor shaft for a multi-bladed helicopter. The blades being mounted to the rotor hub on spherical elastomeric bearings which provide for coincident rotor blade hinges for blade pitch, flap and lead-lag motions. The invention discloses a lead-lag damper contained in a housing at the center of the hollow rotor hub. The damper consists of a series of damping plates, each plate being connected to one of the rotor blades. The damping plates are separated from each other and from the damper housing by elastomeric layers bonded to the plates and to the housing. Lead-lag damping is provided by the shear in the elastomeric layers. The damper may be fastened to the air frame in a conventional manner, it may be mounted on a spindle for rotation about the rotor axis independent of rotor shaft rotation or may be free-floating and attached only to the rotor blades and not to the rotor shaft.

Abstract: A self-adjusting variable-pitch propeller has a drive shaft rotatable about a shaft axis in a predetermined forward rotational sense, a hub carried on the drive shaft and limitedly rotatable relative thereto about the shaft axis both in the forward rotational sense and in an opposite backward rotational sense, and a spring operatively braced between the hub and the shaft for rotationally urging the hub on the shaft in the forward rotational sense. A plurality of blades projecting radially from the hub are each rotatable about a respective blade axis generally perpendicular to the shaft axis. Respective rods extending axially in the hub each have an inner end at a respective one of the blades and an outer end. Respective linkages connecting the inner ends of the rods to the respective blades angular displace the blades about the respective axes on relative displacement of the rods and hub.

Abstract: A rotor hub is provided for coupling a wind turbine rotor blade and a shaft. The hub has a yoke with a body which is connected to the shaft, and extension portions which are connected to teeter bearing blocks, each of which has an aperture. The blocks are connected to a saddle which envelops the rotor blade by one or two shafts which pass through the apertures in the bearing blocks. The saddle and blade are separated by a rubber interface which provides for distribution of stress over a larger portion of the blade. Two teeter control mechanisms, which may include hydraulic pistons and springs, are connected to the rotor blade and to the yoke at extension portions. These control mechanisms provide end-of-stroke damping, braking, and stiffness based on the teeter angle and speed of the blade.

Abstract: A snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors that is design optimized to facilitate utilization of a self-aligning bearing and for installation inboard of the corresponding flexbeam-to-rotor hub attachment joint, thereby enhancing accessibility and reducing maintenance costs. The rotor hub of the rotor assembly is design optimized for securing the snubber assembly in combination therewith and includes a plurality of arms, each arm forming an outboard clevis for attaching the rotor assembly flexbeam to the rotor hub. Inboard of the clevis, each rotor hub arm includes an outboard internal bulkhead having a bolt hole therethrough and an inboard internal bulkhead having a bolt hole therethrough. The inboard and outboard internal bulkheads in combination define a bearing cavity and an internal cavity for securing the snubber assembly in combination with the rotor hub.

Abstract: There is provided a self-actuating variable pitch marine propeller which incorporates two or more blades, each independently rotatable, relative to the propeller hub, between a first lower and a second higher pitch. The blades are preferably mechanically linked by coordinating devices and are caused to move preferably by a combination of centrifugal force effect resulting from inertial masses means and the hydrodynamic forces acting upon the blade hydrodynamic surface. The rotation of the blades relative to the propeller hub is restrained until the restraint is overcome by the forces acting to pivot the blades to the higher pitch position. Most preferably there is also provided a mechanical bias, such as a spring to hold the blades in the lower pitch position. Initially, the hydrodynamic force can also tend to hold in the blades in the lower pitch position, or to move the blades towards the higher pitch.

Abstract: The invention relates to an articulated rotor head for gyroplanes comprising a rigid central hub body (1), perpendicularly integrated with a drive shaft (2), each blade (3) being radially fixed to the hub body (1) by means of connecting and articulating components. These components each comprise:a spherical laminated elastomer stop (4) housed in the central hub body;a hollow sleeve (5) rigidly locked to the spherical laminated stop (4);an elastic return and drag damping brace (9) of the blade (3) arranged between the sleeve and the outer part of the rigid hub body (1) on a contiguous sleeve;a connecting and pitch articulation spindle (6) of the blade (3) connected to the foot of the blade (3) and a pitch lever (8) rigidly locked to the spindle (6) and which swivels about the pitch axis inside the sleeve (5) on two bearings, one of which at least forms a thrust stop (7) to transmit, from the spindle (6) in the sleeve (5), the thrust loads originating from the centrifugal forces on the blade (3).

Abstract: Gyrocraft rotor hub body (1) in which each blade (2) is linked to the body (1) by articulations and linking members the body includes two strong elements (7, 8) whose planes are substantially parallel to each other and perpendicular to the axis of the mast (3) of the rotor. The two elements (7, 8) are separated from each other by a space which is of sufficient size to permit the housing of the articulations which are advantageously embodied in the form of laminated spherical stops (5), one of the armatures (16) of which moves integrally with the (17) is fixed with respect to the two elements of the hub body and is arranged in the vicinity of the periphery of these elements so as to constitute a rigid bracing.

Abstract: A rotor head for a rotary wing aircraft rotor blades, such that each blade is coupled to the hub by an attachment assembly. The attachment assembly includes a thrust bearing attached to the hub for allowing angular oscillations, and drag damping device coupled between the blade and the hub for damping movements of drag caused by rotation of the rotor head. The drag damping device has hydro-elastic elements which are pivotable with respect to each other about a common axis. The damping device as also disposed to pivot in a flapping direction of the blade through a pivot joint.

Abstract: An undesirably long axial length of a ram air turbine may be reduced in a construction including a hub (110) mounted for rotation about a rotational axis (112), at least one turbine blade (114) rotatably mounted on the hub (110) for rotation between coarse and fine pitch positions about a blade pitch axis (116) which is different from the rotational axis (112) and a counterweight assembly (120) for each turbine blade (114) and mounted on the hub (110) for rotation between coarse and fine pitch positions about the blade pitch axis (116) in spaced relation to the rotational axis (114) and disposed when rotated about the rotational axis (112) to bias the turbine blade (114) towards its coarse pitch position. A limited lost motion connection (143, 144, 145, 146, 147, 148, 150) is located between the turbine blade (114) and the counterweight assembly (120).

Abstract: Gyrocraft rotor head including a hub connected to each blade (2) of the rotor by a linking member which is integral with the blade (2) and which is linked to the hub body by a laminated spherical stop. Each blade (2) is fitted with an assembly (20) for elastic recall in drag with incorporated damping, one of whose extremities (22) is linked to the member linking the blade to the hub body. The linking member is constituted by an intermediate sleeve (11) comprising one part in the form of a ring (12) and one part fitted with at least one double clevis (14), the intermediate sleeve (11) being a single integral assembly of which the ring (12) surrounds the laminated spherical stop with which it is integrated and of which the double clevis or clevises interact with the structure for integration of the blade (2).

Abstract: There is provided a self-actuating variable pitch marine propeller which incorporates two or more blades, each independently rotatable, relative to the propeller hub, between a first lower and a second higher pitch. The blades are preferably mechanically linked by coordinating means and are caused to move preferably by a combination of centrifugal force effect resulting from inertial mass means and the hydrodynamic forces acting upon the blade hydrodynamic surface. The rotation of the blades relative to the propeller hub is limited primarily as to speed of rotation by restricted viscous fluid flow damping means operably connected to the blades. In one preferred embodiment, the viscous flow means further acts as an initial restraint against all motion by closing off the viscous flow orifice until a certain minimum propeller rotational speed is achieved.

Abstract: A bearingless hub structure for a rotary-wing aircraft is provided, the structure including a hub body adapted to be securely connected to a rotor mast, a plurality of flexible beam members provided integrally with the hub body to extend radially outwardly, a pitch housing encircling each of the flexible beam members, and having a radially outward end portion which is rigid with a radially inward end portion of a rotor blade, a spherical bearing positioned adjacent to a radially inward end portion of the flexible beam member for supporting the pitch housing, a lead-lag damper positioned between the flexible beam member and the pitch housing, and the flexible beam members each having a flexible plate portion which is of a low bending rigidity in a flapping direction, a flexible portion provided radially outwardly of the flexible plate portion having a low bending rigidity in the lead-lag direction, and a twist-flex portion provided radially outwardly of the flexible portion.

Abstract: A marine propeller includes a hub rotatable about a longitudinal axis and having a plurality of blades extending radially outwardly therefrom and pivotable about respective radial pivot axes between a low pitch position and a high pitch position. Each blade has a hydrodynamic force characteristic which shifts the location of the resultant hydrodynamic force on the blade in a direction aiding up-pitching of the blade, and increasing the up-pitching pivot moment with decreasing angles of attack. A counteractive hydrodynamic force generating area is provided on the negative pressure backside surface of the blade and shifts the location of the resultant hydrodynamic force on the frontside surface forwardly with decreasing angle of attack.

Abstract: The hydraulic damper according to the invention has at least one restricted communication passage (47) between its two working chambers (8, 9) whose cross section is controlled by a viscous restriction valve (51) positioned via a control pressure of a fluid of a control damper with at least one secondary chamber (41, 42) delimited in a secondary cylinder (39) by a control piston (40), which cylinder and control piston are integrally attached, one to the main body (1), the other to the damping piston (4) of the damper, such that the damping law of the control fluid positioning said valve (51) is linked to the relative displacements of the main body (1) and damping piston (4).Application to the equipping of elastic-return struts with integral damping, in particular for helicopter rotors and blades. FIG. 2.

Abstract: A wind turbine assembly including a rotor body having mounted thereon a plurality of rotor blades. Each of the rotor blades may be joined at an inner extremity to a blade stem projection extending interiorly into the rotor body and secured to the rotor body by a torsional-spaced and axial-shock damping connection. The blade stem projection may also be secured within the rotor body in a manner allowing limited rotation of the blade stem projection relative to the rotor body, corresponding to a selective range of pitch of the associated rotor blade, with a system for rotating a blade stem projections of each of the rotor blades by corresponding degrees of rotation to provide a predetermined pitch of the rotor blades. Also disclosed are pitch-damping tower designs, and an integrated design wherein the tower is pitch- and yaw-damped.

Abstract: A propeller to be used in particular for sail boats comprises a hub (2) fitted to the end of a drive shaft (5) and carrying a bevel toothing (8) meshing with bevel pinions (9) provided at the ends of corresponding propeller blades (10) mounted in a rotatable manner about their own axes between two annular shell halves (11, 12) covering the hub (2); and an adjusting element (21) coupled through cylindrical mating toothings (19) to the inner shell half (12) and detachably fastened thereto, the adjusting element internally carrying a circular sector (24) to be engaged by a corresponding circular sector (23) projecting from the outer hub outline so as to determine the boundary orientation positions of the blades (10); the propeller pitch being adjustable by disengagement of the mating toothings (19) between the adjusting element (21) and shell half (12), rotation of the adjusting element through a given angle and further engagement between the mating toothings (19).

Abstract: A snubber set (30) for a helicopter rotor (10) is comprised of an inner race (44), an intermediate race (45), a preload plate (46), an inner portion (48) having alternating laminates of elastomer (52) and metal shims (54) which are spherically shaped, and an outer portion (50) having alternating laminates of elastomer (58) and metal shims (60) which are flat. The flat laminates (58) are comprised of a center portion (61) made from a high loss elastomer and a peripheral portion (62) made from a high shear strength elastomer.

Abstract: Wind-driven electric generator apparatus has a generator head supported on a tower for free-yaw movement and for free-pitch movement within predetermined limits. The generator head has a downwind rotor with a pair of elongated blades mounted on a hub that is rigidly attached to a rotor shaft driving an electric generator. The blades are flexible and have a coning angle therebetween that varies with wind velocity. The generator head is capable of aligning itself with the wind direction azimuthally and elevationally. A yaw brake prevents an excessive yaw rate. In most preferred embodiment, pitch movement and yaw movement beyond small angular ranges are regulated, and an electrohydraulic yaw drive system corrects gross azimuthal misalignment with respect to the wind direction.In a most preferred embodiment, pitch movement and yaw movement beyond small angular ranges are regulated, and an electrohydraulic yaw drive system corrects gross azimuthal misalignment with respect to the wind direction.

Abstract: A main helicopter rotor has a number of blades and drive shaft that supports, at its top end, a hub defined by a rocking toroidal body, the inner and outer edges of which are connected to the drive shaft via respective spherical elastomeric joints having a common center on the axis of the drive shaft. The toroidal body is fitted with and supports a rigid tubular body substantially coaxial with the drive shaft. Each blade is connected to the hub by a connecting element extending through both the tubular body and the toroidal body and connected respectively to the same by a first and second elastomeric bearing.

Abstract: A main helicopter rotor has a number of blades, and a drift shaft supporting at its top end, a hub consisting of a rigid annular body integral and coaxial with the drive shaft. An elastically deformable torodial body surrounds and is connected to the annular body for defining, with the same, a closed-section torodial assembly. Each blade is connected to the hub by a connecting element extending at least partially through the annular body and the torodial body, and connected respectively to the same by a first and second spherical elastomeric bearing.

Abstract: An aspirator fan is disclosed, which comprises a rotating shaft press-fitted in an impeller, a support member having an urging means and receiving one end of the rotating shaft for supporting the rotating shaft as a cantilever, and a shaft abutment member disposed in a casing and having a shaft abutment portion against which the opposite end of the rotating shaft is urged by the force of the resilient means. The aspirator fan is free of an alignment adjustment between the rotating shaft and bearings which is required in the casing of conventional aspirator fans. The shaft abutment member is structurally separated from the casing, so that even when the casing is deformed, a deformation of the casing has no effect on the rotation of the rotating shaft. The aspirator fan can, therefore, be operable with an improved reliability.

Abstract: The invention relates to a drag elastic-return and damping device (28) for a blade, and a rotor head including it.The device (28) comprises a connecting rod (30) connected to the blade and transmitting its drag movements to a rotary member (29) for elastic return with incorporated damping whose outer armature (32) it causes to rotate about a coaxial inner armature (31) in order to shear at least one thin collar (33) of a viscoelastic elastomer about its axis (B). The connecting rod (30) is coupled by way of rotational joints (43, 44) to a sleeve (15) for attaching the blade to the hub (1), and to a lever (34) of the outer armature (32). The member (29) is supported at the periphery of the hub (1), between two adjacent blades, or in the sleeve for attaching an adjacent blade such that the corresponding connecting rod is mounted as an inter-blade tie. On the rotor head, each blade is articulated with the hub (1) by a spherical laminated thrust block (5).

Abstract: A main helicopter rotor having a number of blades and wherein a drive shaft supports, at its top end, an annular hub integral with the drive shaft and in turn supporting, via a spherical elastomeric joint having its center on the axis of the drive shaft, and an elastic axial suspension, a toroidal body surrounding the drive shaft. Each blade is connected to the hub by a connecting element extending through both the hub and the toroidal body, and connected respectively to the same by a first and second spherical elastomeric bearing.

Abstract: A motor driven by a fluid motion, comprising a rotor with a vane whose surface varies according to the vane position relatively to the fluid flow direction. To create a thrust on the vane when the fluid moves quasi-parallel to the vane longitudinal axis, at least one side-panel is provided on the vane, generally perpendicular to the longitudinal axis thereof.

Abstract: A device of retractable stops for the blades of articulated rotors for giroplanes, which includes a stationary stop 20 with a finger 22 radially converging towards the exterior and externally radially protruding on the external spar 9 of the articulation means 7 of each blade on the hub 3, as well as a movable stop 21 with a receptacle 36 resiliently returned by a return device 45 in a position fit around the finger, but disengaged from the finger by centrifugal force when the rotation speed of the blades is higher than a set value. The invention therefore provides absolute stops in flapping and drag in the "ground" position and sharp stops in the flight position. One advantageous application is for helicopter rotors.

Abstract: A viscous damper for a helicopter rotor blade having a stator member and a rotor member each having a plurality of flanges of different diameter defining cylindrical internal and external shear surfaces, respectfully, and a shear gap therebetween, one stator member internal shear surface having two diameters, the shear gap distances between proportional to radius, and a coaxial rotor member comprising two discs having outer cylindrical shaped shear suraces forming a shear gap with adjacent stator member shear surfaces and one rotor disc being axially movable so that a variable portion of its shear surface is opposite both of the diameters of the stator member two-diameter internal shear surface.

Abstract: A propeller or fan blade is rotatably mounted to a blade retention pitch member by a pin radially outside of a spinner. By mounting the propeller blade for rotation about the axis of the pin, the blade response to a vibratory excitation in a first mode of vibration is modified such that the twisting motion of the blade is minimized. High speed stability of the blade is enhanced thereby. Moreover a damaged blade may be easily replaced.

Abstract: A flexible beam type helicopter rotor includes restraining means outboard of a snubber means and connected between the flexible beam and a torque tube to increase the stiffness of the rotor in the lead/lag plane as applied pitch is increased.

Abstract: The invention relates to a regulating device for maintaining constant the rotary speed in turbines of the type comprising a turbine hub and a number of turbine blades which are axially, but rotatably connected to the hub and have such a shape and are so aranged that each turbine blade in a flowing medium and by the action thereof is acted on by a torque about its longitudinal axis against the action of a spring device and acts on the turbine hub by a torque acting about the axis of rotation of the turbine.

Abstract: A flexbeam helicopter rotor having an improved snubber-vibration damper for positioning the flexbeam spar relative to the torque tube, wherein the snubber-damper is an elastomeric bearing having a spherical and a flat portion, and whose laminates are continuous, selectively preloaded and of selected material to provide increased fatigue life, size reduction, reduced laminate stress concentration, and reduced critical design stress in the snubber-vibration damper.

Abstract: A lightweight propulsion device for use with various types of lightweight boats and other small craft, including use with a swimmer is provided with a frame for mounting the propulsion device on the craft. A shaft rotatably supported on the frame carries a propeller, including flexible blades rotatably supported relative to the shaft on a hub. The blades are supported for rotation about an axis having a major radial component and stop means supported relative to the shaft limits movement of each blade in each direction from a plane through the shaft axis. A pair of cables are coupled to the shaft to turn the shaft and are positioned to be wrapped around the shaft in opposite directions. Sheaves on the shaft for each cable contain and direct the cables as they are alternately wrapped and unwrapped around the shaft.

Abstract: A hinged vane rotor generating power from rivers, streams, tides or wind. A cylindrical drum is supported sideways in a current by axles at the ends connected to pulleys which are in turn, connected to a generator(s), mill wheel, pump or other working device. The rotor is turned by a series of hinged vanes, each one opening to catch the current on one side of the drum and closing to avoid the current on the other side of the drum. A fluid directing component is incorporated to increase current against one side of the drum and reduce it against the other side.