Abstract: A vertical axis wind machine having a mechanism of apertures and flaps to reduce return blade wind drag. The aperture and flap vertical axis wind machine has improved rotational speed and torque in relation to existing vertical axis wind machines. The aperture and flap vertical axis wind machine is also quieter, has fewer moving parts, requires no feathering controls to operate in high wind speeds, and can be operated independent of wind direction.

Abstract: A control system for a rotorcraft is disclosed. The control system includes a stepped mixing linkage, such that a selected amount of right-left lateral cyclic output is generated for certain amounts of forward-aft cyclic input. The stepped mixing linkage includes two supporting links and a floating link pivotally coupled between the two supporting links. The ratio of the lengths of the two supporting links to the length of the floating link is small, thereby generating a selected lateral sinusoidal output, a selected rotation of the sinusoidal output, and a selected ramped output in response to each forward-aft pilot input command.

Abstract: Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass.

Abstract: The present method is characterized by providing the rotor blade with a tab 3, which can advance and retreat with respect to rear of rotating direction of the rotor blade between a position where the tab protrudes from a trailing edge of the rotor blade and a position where the tab does not, and providing an actuator 4, which advances and retreats the tab 3, and operating the actuator 4 so that the tab advances and retreats in response to rotating timing of the rotor blade 2, when reducing the BVI noise of the rotor blade of a helicopter. Thus, the BVI noise of a helicopter can be reduced effectively.

Abstract: A turbine blade assembly has a plurality of blades mounted on a central rotor. Each of the blades has a proximal section and a variable pitch section. A number of stays extend in groups from the central rotor to converge and terminate on an associated one of the blades. The stays each have a proximal end spaced from the blades.

Abstract: The present invention discloses systems and methods for the performance enhancement of rotary wing aircraft through reduced torque, noise and vibration. In one embodiment, a system includes a sail having an aerodynamic shape positioned proximate to a tip of the rotor blade. An actuator may be configured to rotate the sail relative to the blade tip. a A control system receives information from a rotorcraft system and commands the actuator to rotate the sail to a predetermined favorable rotor blade operating condition. In another embodiment, a method includes configuring the rotorcraft in a selected flight condition, communicating input signals to a control system operable to position sails coupled to tips of blades of a rotor assembly, processing the input signals according to a constraint condition to generate sail positional information, and transferring the sail positional information to the sail.

Abstract: A tilt-rotor compound VTOL aircraft has a multiple-flow thrust generator(s) comprising a gas-powered tip-jet driven rotor(s) having a thrust-augmentation ratio of at least two; that tilts about the aircraft's pitch axis wherein the rotor's plane of rotation is substantially horizontal for VTOL operations and the rotor's plane of rotation is substantially vertical forward flight operations. A relatively small fixed-wing sustains the aircraft during forward flight. Compressed exhaust gas from the fan-jet engine(s) is ducted to a manifold having valves which control power to the multiple-flow thrust generator(s) and to the jet exhaust nozzle(s) as supplemental thrust for forward propulsion and yaw control. The manifold also serves to distribute compressed gas to the dead engine side of the aircraft in the event of a dead engine emergency, and to reaction jets for attitude control during VTOL operations.

Abstract: A rotating wing aircraft has a rotating fuselage and wings. The aircraft is configured to rotate with the air passing over the wings because of the rotation providing the lift needed to keep the aircraft aloft. The wings have rudders coupled to them, such as at the tips of the wings, to provide force for laterally moving the aircraft. The aircraft may be able to remain airborne by hovering for a long period of time, on the order of days. Power for the aircraft may be provided by a central diesel electric generator, which provides power for electric motors that turn propellers that are on the wings. The aircraft may be used for any of a variety of applications, such as for surveillance, communications, or as a radar platform.

Abstract: A rotor blade assembly provides a pitch control assembly to pitch the rotor blade about a rotor blade pitch axis. The pitch control assembly includes a trailing edge flap and a trailing edge servo flap that extend from the trailing edge of the rotor blade. The trailing edge flap is offset in the span wise direction relative to the trailing edge flap. The trailing edge servo flap is located upon a trailing edge servo flap arm linked to the trailing edge flap. To pitch the rotor blade, the trailing edge servo flap is pitched in a direction opposite the desired pitch direction of the trailing edge flap.

Abstract: A rotor blade assembly system includes a trim tab assembly which utilizes relatively thick resilient members bonded between a trim tab and the two trim tab doublers. Spanwise segmenting of the tab and the use of thick resilient member isolates the trim tab from normal strain. Because the trim tab is made of aluminum, the tab can be readily adjusted the field using a conventional tool.

Abstract: A multi-element rotor blade includes an individually controllable main element and fixed aerodynamic surface in an aerodynamically efficient location relative to the main element. The main element is controlled to locate the fixed aerodynamic surface in a position to increase lift and/or reduce drag upon the main element at various azimuthal positions during rotation.

Abstract: A multi-element rotor blade includes a main element and an active slat movable relative to the main element. The slat rotates and translates relative to the main element from a base position. The base position provides a compromise between minimum coefficient of drag CD and maximum coefficient of lift CLmax. In the advancing blade, since the airspeed thereof is significantly greater than the retreating blade, the slat is positively rotated from the base position to minimizes drag at low angles of attack. In the retreating blade, since the airspeed thereof is significantly lower than the advancing blade, the slat is negatively rotated and translated to maximize the coefficient of lift CLmax.

Abstract: Turbine for flowing fluid, especially a turbine having a vertical power output shaft and formed with several wings projecting radially out from the power output shaft, which wings are rotatable over an angle of about 90° about horizontal shafts extending closely adjacent and along the trailing edge of the wing as seen in the flow direction, so that the wings, in an operative, first position, are positioned at right angle to the flowing fluid and in a second, non-operative position, are located horizontally or nearly horizontally and on plane with the flowing fluid. Each wing is formed with a fin portion for catching, at a very early stage of an operation cycle, flow medium passing by and to thereby initiate a pressing down of the wing to a portion at right angle to the flow medium for, as far as possible, maintaining the flow medium against the wing during the active moving path thereof.

Abstract: The present invention shows an oscillating wing system like lifting surface featuring a symmetrical profile mounted free to rotate over a fixation point located ahead neutral point and self-trimming at angle of attack in the flow by adjustment of a trailing edge elevon, and whose the system is actuated by linear lateral or vertical movement allowing to produce electrical energy with the wind flow or water flow of a deep river or at flood/ebb tide.

Abstract: Rotary wing aircraft with electric pitch control. According to the invention, each blade (5.i) of the wing comprises a plurality of flaps (6.i) which are able to control the pitch of said blade and are aligned along the span of the latter, said flaps being individually controlled in orientation from a flight control device (17). Elimination of mechanical and hydromechanical members for controlling the rotor of such an aircraft, without loss of reliability.

Abstract: A hub mounted actuation system for providing control of a portion of a rotor blade, such as a flap, on a rotorcraft. The rotor blade is attached to a rotor shaft that rotates with respect to an airframe. The hub mounted actuation system includes a stationary support mounted to the airframe and a rotary support attached to the rotor shaft for concomitant rotation therewith. At least one hub actuator rotates in combination with the rotor blade and includes a piston which is slidable within a housing. The piston and housing define a pressure chamber within the actuator which contains a fluid to be pressurized. A displacement control device is disposed between the stationary support and the rotary support for controlling movement of the piston within the housing. A linkage connects the hub actuator to the portion of the blade to be controlled. The linkage is adapted to displace the blade portion as a function of the movement of the piston within the housing.

Abstract: The invention is related to air flight vehicles, such as vertical take-off and landing (VTOL) airplanes, helicopters and covercraft. The goal of this invention is to create an air rotor designed so that while after vertical take off or cover regime, one can be stopped, fixed in a specific position and hidden into the fuselage (gondola) thus eliminating of air resistance when the rotor is not in working state. On landing this rotor can be extended out, brought into rotation and used for creation of lift force and vertical landing. The indicated goal is achieved by means of the rotor made as single blade (uniblade). The author solved the problem of force and moment balance of single blade. The center of gravity of the counterweight is located below the horizontal plane, and the blade has the horizontal sway axle, that crosses the vertical rotor rotation axis. The author offer this rotor on single axis, on co-axis, and on different exiles.

Abstract: A flap actuation system for a helicopter rotor blade. The rotor blade includes a root end, a tip end, a trailing edge and a flap hinged to at least a portion of the trailing edge about a pivot axis. The flap actuation system includes at least one supply line mounted within the rotor blade and extending outward from the root end. The supply line is adapted to channel pressurized fluid. At least one actuator fluidly connected to the supply line. The actuator includes a displacement member and a head member. The head member is engaged with the flap and is adapted to pivot the flap about its pivot axis when pressurized fluid is conveyed through the supply line. In one embodiment of the invention there are two supply lines, each extending outward from the root end and is adapted to channel pressurized fluid. There is at least one actuator fluidly connected to each supply line.

Abstract: An actuation system for pivoting a flap on a helicopter rotor blade to reduce the interaction of the blade with the preceding blade vortex. The actuation system includes a fluid supply which is connected to first and second fluid supply lines. The fluid supply lines convey flows of pressurized fluid from the fluid supply to an actuator. The actuator includes a housing mounted within the rotor blade and having a channel formed in it. A butterfly shaft is pivotally mounted within the channel and has laterally extending arms which separate the channel into four lobes. A first port connects the first fluid supply line with two diametrically opposed lobes in the channel. A second port connects the second fluid supply line with the other two diametrically opposed lobes in the channel. A torque coupling is attached to the butterfly shaft and engaged with the flap such that rotation of the torque coupling produces concomitant rotation of the flap.

Abstract: The blade includes at least one trailing edge swivelling air flow control flap, swivelling on the blade around an axis directed substantially along the span of the blade and the control flap, the swivelling of the control flap being controlled by an actuator gear mounted on the blade and including an actuator. The actuator includes a first rotating motor, the rotational speed of which corresponds to a frequency of swivelling of the control flap, and a second rotating motor which moves relative to each other two eccentrics mounted in series around the shaft of the first motor, the second motor rotating with one of the eccentrics, and a ring freely rotating around the eccentrics is driven in movements transmitted by a flexible arm transmission to the control flap. The frequency and amplitude controls of the swivelling of the air flow control flap are thus separated.

Abstract: The invention provides for a cycloidal propeller, in strictly rudder operation, accessory apparatuses that mesh with a gear drive connected to a shaft of the respective wing. The invention accomplishes relatively small actuation movements of the accessory apparatuses, sufficient to achieve a large pivoting movement of the wings, so that the wings can be adjusted over large angles without impediment. Therefore, wings having normal profiles may be utilized.

Abstract: A method and apparatus for controlling the blowing of compressed air from an aerodynamic structure such as an aircraft wing or helicopter rotor blade and thus controlling the aerodynamic properties of the wing comprises a narrow slot (13) in the upper surface (15) of the structure near its trailing edge (14). Inside the wing (12) is a chamber (23) that is connected to the narrow slot (13) in the wing surface (15). The chamber (23) houses a compressed air conduit (16) for supplying and holding compressed air. A passageway (25) connects the conduit (16) to the slot (13) in the upper surface (15) of the wing (12). The lower wall (27) of the passage (25) has a slit (32) allowing a shutter (31) to move selectively into the passage (25) and obstruct the flow of compressed air through the passageway (25). The shutter (31) is attached to a smart material actuator comprising a piezoelectrical bender (29). When a control voltage is applied to the bender (29), the bender (29) will bend.

Abstract: An actuating device can change a position of an active member that remains in substantially the same position in the absence of a force of a predetermined magnitude on the active member. The actuating device comprises a shape-memory alloy actuating member for exerting a force when actuated by changing the temperature thereof, which shape-memory alloy actuating member has a portion for connection to the active member for exerting thereon a force having a magnitude at least as large as the predetermined magnitude for moving the active member to a desired position. Actuation circuitry is provided for actuating the shape-memory alloy actuating member by changing the temperature thereof only for the time necessary to move the active member to the desired position.

Abstract: A rotor blade made of fiber-reinforced synthetic resin has a profile which, at least in the region of the blade tip is designed so as to be twistable by actuators about the rotor blade longitudinal axis. The torsion skin of the rotor blade in the region of the blade tip is designed anisotropically in the sense of a tension/torsion coupling and a controllable actuator, which acts in a longitudinal direction of the rotor blade upon the rotor blade tip, is disposed in the rotor blade spar. To achieve anisotropy, the torsion skin is a uni-directional winding having a winding angle of less than 45.degree. relative to the rotor blade longitudinal axis. The winding angle is dependent upon the force-to-displacement ratio of the actuator and may lie between 18.degree. and 40.degree.. In the region of the blade tip, the anisotropic torsion skin is disposed resting loosely on the rotor blade spar.

Abstract: An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The flap may be actuated in any conventional way, and is scheduled to be actuated to a deflected position during rotation of the rotor blade through predetermined regions of the rotor azimuth, and is further scheduled to be actuated to a retracted position through the remaining regions of the rotor azimuth. Through the careful azimuth-dependent deployment and retraction of the flap over the rotor disk, blade tip vortices which are the primary source for BVI noise are (a) made weaker and (b) pushed farther away from the rotor disk (that is, larger blade-vortex separation distances are achieved).

Abstract: A turbine has an upright shaft defining and rotatable about a vertical main axis, a support plate fixed to the shaft, a plurality of upright vanes pivotal on the support plate about respective vane axes offset from and generally parallel to the main axis, and a control plate rotatable adjacent the support plate about a vertical control axis. The control plate can be displaced relative to the support plate in an adjustment direction perpendicular to the axes. Respective formations on the vanes form grooves extending radially of the respective vane axes and open toward the control plate and respective link pins on the control plate are engaged in the grooves. Respective ring gears are provided on the control and main plates, centered on the respective axes, of the same diameter, and directed toward each other.

Abstract: An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The flap may be actuated in any conventional way, and is scheduled to be actuated to a deflected position during rotation of the rotor blade through predetermined regions of the rotor azimuth, and is further scheduled to be actuated to a retracted position through the remaining regions of the rotor azimuth. Through the careful azimuth-dependent deployment and retraction of the flap over the rotor disk, blade tip vortices which are the primary source for BVI noise are (a) made weaker and (b) pushed farther away from the rotor disk (that is, larger blade-vortex separation distances are achieved).

Abstract: An advanced aileron configuration for wind turbine rotors featuring an aileron with a bottom surface that slopes upwardly at an angle toward the nose region of the aileron. The aileron rotates about a center of rotation which is located within the envelope of the aileron, but does not protrude substantially into the air flowing past the aileron while the aileron is deflected to angles within a control range of angles. This allows for strong positive control of the rotation of the rotor. When the aileron is rotated to angles within a shutdown range of deflection angles, lift-destroying, turbulence-producing cross-flow of air through a flow gap, and turbulence created by the aileron, create sufficient drag to stop rotation of the rotor assembly.The profile of the aileron further allows the center of rotation to be located within the envelope of the aileron, at or near the centers of pressure and mass of the aileron.

Abstract: A cross flow wind turbine comprising a rotor mounted for rotation about a vertical axis and a plurality of blade assemblies mounted on the rotor. Each blade assembly comprises a blade of aerofoil section mounted vertically for pivotal movement about a vertical shaft. The turbine also includes a device for measuring the direction of the apparent fluid velocity, a shaft encoder for measuring the blade angle and a control system to set the blade angle such that the lift component of the aerodynamic forces on the blade contributes positively to the driving torque on the rotor.

Abstract: In a helicopter having a main rotor with blades controlled in pitch by servo flaps the servo flaps are arranged in advance of the leading edges of the blade to provide increased lift efficiency of the rotor system. The signals for controlling the pitches of the blade are generated by a computer implemented means responsive to pilot command signals and flight parameter signals and are transmitted from the stationary structure of the helicopter to the rotating structure through a non-mechanical stationary-to-rotary interface. An active stabilization system is associated with each rotor blade to overcome the instability previously associated with leading edge servo flaps and to reduce the complexity of the control signals needed to be produced by the control signal generating means.

Abstract: A wind turbine has a rotor with at least one blade which has an aileron which is adjusted by an actuator. A hinge has two portions, one for mounting a stationary hinge arm to the blade, the other for coupling to the aileron actuator. Several types of hinges can be used, along with different actuators. The aileron is designed so that it has a constant chord with a number of identical sub-assemblies. The leading edge of the aileron has at least one curved portion so that the aileron does not vent over a certain range of angles, but vents if the position is outside the range. A cyclic actuator can be mounted to the aileron to adjust the position periodically. Generally, the aileron will be adjusted over a range related to the rotational position of the blade. A method for operating the cyclic assembly is also described.

Abstract: A helicopter comprises a pair of rotors each having a flap hinged to one of its edges, a seesaw rod swingably supported above the rotors, a pair of auxiliary wings fixed to opposite ends of the seesaw rod, and a pair of connecting rods each connecting one of the flaps with seesaw rod above it. When the lift produced by one of the rotors becomes larger than that produced by the other, the auxiliary wing located above the rotor producing the larger lift rises and turns up the flap of the rotor to reduce its flap effect and decrease the rotor lift, while the auxiliary wing located above the rotor producing the smaller lift lowers and turns down the flap of the rotor to increase its flap effect and raise its lift. As a result, the lifts of the two rotors are regulated.

Abstract: An articulated blade whose forward vane section is directly pitched by relative fluid flow upon it, and whose rear deflector section deflects the flow upon it. A control arm, through parallelogram linkage, maintains the deflector in parallel orientation with it, thus cambering the blade when it pitches. Fluid is deflected always in a direction controlled by orientation of the control arm. High lift-drag ratios are possible at high angles of attack. The blade can be used to extract power from the fluid, or for propulsion through a fluid.

Abstract: An airfoil camber control apparatus utilizes a cable of shape memory alloy affixed at its ends to a front interior portion of the airfoil. A tensioning system is connected to a rear interior portion of the airfoil and to the cable. When electrical current is applied to the cable to heat it, it returns to its remembered, shorter length, thereby applying tension to the tensioning system to alter the position of the rear portion of the airfoil relative to the front portion.

Abstract: A helicopter main rotor blade having built-in twist for improved hover performance is provided with a trailing-edge, short span slot near the tip end of the blade for upwardly directing a stream of pressurized air therefrom. The upward ejection of air from the slot untwists the blade, which will enhance the forward flight performance of the blade. A method of modulating the ejection of air from the slot is disclosed for antivibratory control.

Abstract: A rotor system for a helicopter having a power shaft carrying at least one pair of diametrically opposite frames for rocking motion about an axis radially of said shaft. Sets of lift blades carried by the frames, respectively, for rocking motion about radial axes. A first pitch control means for rocking the frames and blades sets periodically. A second control means for rocking the blade sets simultaneously and equally relative to the frames. A third control means, including servomechanisms, for independently rocking the individual blades of said sets in different directions and extents relative to each other.

Abstract: A helicopter rotor having blade trailing edge tabs which are actuated in response to control rod loading to reduce or cancel the blade pitching moments imposed upon the blade and hence the control rods by blade aerodynamic and inertial loads, or other loads, encountered during rotor operation.

Abstract: This invention relates to a device converting the kinetic energy belonging to the moving stream of the fluid such as the wind, river and gulf streams to the power capable of doing a useful work in the form of a rotational motion with torque. Said device comprises two or more blades revolving about the central axis, which blades are made to rotate about its own axis parallel to the central axis at an angular velocity equal to one half of that of the revolving motion of the blades about the central axis.

Abstract: Current energy is converted into shaft power in two stages;First, buoyant power units with stationary hydrofoil wings reach faster than the current speed by sweeping out a captive path.Second, turbines at said power units convert the fast relative local current into shaft power.Power units sweeping along the water surface, using cycloidal turbine methods, as well as power units sweeping on a submerged path, using axial flow turbine methods, are described.

Abstract: A wind turbine has axially aligned, spaced, rotatable support flanges with a plurality of vertically aligned air foils having opposed ends journaled thereto. The air foils are pivoted respective to the wind by a pitch flange mounted eccentrically respective to the support flanges. The pitch flange moves the air foils into an aligned relationship respective to the wind to optimize the energy derived from the blowing wind.

Abstract: An aircraft is provided with a wing in the form of an annulus having an airfoil shape in radial section, the wing being concentrically mounted on a vertical axle shaft which in turn is rotatably carried by a mounting on the fuselage. Rotation of the wing drives air centrifugally across the upper and lower surfaces to energize the boundary layer, enhance laminar flow, and produce lift. Vanes may be mounted on the inner portion of the surface to increase the flow and thus produce greater life. The vanes may be attached to a stabilizer ring which is eccentrically adjustable by a controlling mechanism to vary the extension of the vanes into and out of the wing at various points in the cource of rotation and thus vary the degree of lift produced. The wing may also be provided within its inner perimeter with airfoil lifting blades which produce additional lift, and the blades may be swung by a stabilizer ring to positions producing a desired thrust in a desired direction as the wing rotates.

Abstract: An improved wind turbine in which the tip portions of the blades are variable in pitch and are cyclically varied in pitch to control the yaw of the rotor and to relieve bending moments on the blades and are collectively varied in pitch to relieve bending moments on the blades and to maximize the power output of the turbine at a selected constant rotor speed.

Abstract: A device converting the kinetic energy belonging to the moving stream of fluid such as the wind, river stream and gulf stream is disclosed. Said device is comprised of two or more blades revolving about the central axis, which blades are mechanically linked to said central axis wherein each of said blades completes a half rotation about its own axis when it completes a complete revolution about said central axis. Each of blades further includes a pair of flaps rotatably disposed on each edge of said blade, which flaps are mechanically linked to the rotating and revolving motion of the blade wherein said flaps are automatically deflected to provide a suitable camber to the blades to generate a lift force on the blade.

Abstract: A cycloidal fluid flow engine suitable for turbine and propeller operation, employing blades of aircraft type wing and tail configuration, pitch controllable through the full range of advance ratios by reciprocating control surfaces, guided by an adjustable inclined bearing device on each blade hub, or one such device centrally located on the mainshaft housing.

Abstract: The disclosed wind turbine has zero mean camber airfoil blades vertically pivoted at the outer ends of pairs of radius arms. The inner ends of the radius arms are fixed to a rotating mast. Each blade is provided with a steering vane. The deflection of each vane with respect to its associated blade is controlled by a cam toggle mechanism. The disclosed cam toggle mechanism includes a double-faced face cam, having a closed cam track on its upper face and another closed cam track on its lower face. Each cam track consists of two circular dwell portions.