Abstract: A kinetic fluid energy to mechanical energy conversion includes rotatable hubs supporting one or more independently controlled articulating energy conversion plates (“ECP”) and systems and components for alternating the independent control of each ECP in response to operating conditions thereby comprising an energy conversion regulation method. Separator plates for controlling fluid flow with respect to each ECP may be employed above and below the hub and may also be directionally altered in response to operating conditions and included within the energy conversion method.

Abstract: A kinetic fluid energy conversion system comprises one or more hubs which rotate about a central hub carrier, each including one or more independently controlled articulating energy conversion plates (“ECP”). An articulation control system rotates each ECP independently of all others to control its orientation with respect to the fluid flow direction between an orientation of 90° perpendicular to the fluid flow, while traveling in the direction of the flow and 0° minimal drag parallel position to the flow, while traveling in the direction against the flow or blocked from it. Each hub can be operably coupled to another hub to form one or more counter-rotating hub and ECP assemblies whereby the mechanical energy is transferred through the hubs, to one or more clutch/gearbox/generator/pump assemblies thereby permitting such assemblies to be land-based when the system is air-powered, and above or near the surface, when the system is water-powered.

Abstract: A hydrokinetic turbine has upper and lower vane mounts; a main shaft coupling the vane mounts to form an assembly mounted for rotation about a central axis; a set of vanes, each vane mounted between the upper and lower vane mounts for reciprocating rotation about its respective longitudinal axis; a vane angle control mechanism, configured to control angle of the vanes relative to the direction of current so as to provide an angle of attack, relative to the direction of the current, that is cyclically adjusted over the course of rotation of the shaft. A given vane is oriented: (i) substantially transversely to the direction of the current when the assembly's orientation causes the vane to be in a driving mode, and (ii) substantially parallel to the direction of the current when the assembly's orientation causes the vane to be in a driven mode.

Abstract: The lengths and/or chords and/or pitches of wind turbine or propeller blades are individually established, so that a first blade can have a length/chord/pitch that is different at a given time to the length/chord/pitch of a second blade to optimize performance and/or to equalize stresses on the system.

Abstract: A helicopter rotor head system has direct mounted mechanical phasing and pitch control levers. The system reduces drag and friction from the conventional four-point connection used today by using a two-point connection at the swash plate. Input movements from the swash plate are transmitted through a linkage arm fixed to ball bearing raced levers. The levers are ball bearing raced in two positions, with two different inner race sizes to reduce wear and side load while maintaining precision and accuracy. These levers are mounted to fixed support studs on the center hub (yoke). This causes them to set the phase of the swash plate precisely. Movements from these levers are reduced to a single connection point and allow only pitch up/down movements that transmit to blade grips through a link rod.

Abstract: According to one embodiment, a bearing is situated in a rotor system. The bearing features a housing having a first opening therethrough, a first member disposed within the first opening and having a second opening therethrough, and an elastomeric bearing disposed within the second opening and having a third opening therethrough configured to receive a shaft. The first member having at least one substantially curved surface. A sliding element bearing disposed between the housing and the first member.

Abstract: A constraint assembly for an aircraft, having a first member; a second member mounted to translate along and rotate about its own axis; and connecting means for connecting the first and second member, to prevent rotation of the second member about the axis with respect to the first member; the connecting means having a retaining arm, which projects outwards from one of the first and second member, and extends at a distance of other than zero from the axis; and an antirotation bracket, which projects from the other of the first and second member, extends at a distance of other than zero from the axis, and defines a through opening engaged in sliding manner by the retaining arm.

Abstract: A transmission mechanism for a remote-controlled model simulation helicopter includes a body frame which is orderly provided with a main rotor holder, a main rotor shaft, and a main reduction gear provided with a plurality of washout holes which are evenly distributed about an axis thereof. The body frame is provided with a swashplate module and a servo arrangement at a middle portion thereof. Since the main reduction gear is provided with washout holes and the introduction of internally installed swashplate module together with taking advantage of self structural features of the body frame, it enables the elimination of the commonly used swashplate guide board. The servo devices are provided in a same plane within the body frame and provide a triangular configuration, so that the structure is reasonable and the transmittance of motion is stable.

Abstract: A rotor system for a rotorcraft having at least one rotor blade pair operably associated with a differential pitch assembly operably for controlling a pitch angle of an upper rotor blade and the lower rotor blade in the rotor blade pair. Operation of the differential pitch assembly changes the pitch of the upper rotor blade more severely than the pitch of the lower rotor blade. As such, the rotor system is configured to provide optimum pitch of the upper and lower rotor blades during a helicopter mode and an airplane mode.

Abstract: A rotor system for a rotorcraft having at least one rotor blade pair operably associated with a differential pitch assembly operably for controlling a pitch angle of an upper rotor blade and the lower rotor blade in the rotor blade pair. Operation of the differential pitch assembly changes the pitch of the upper rotor blade more severely than the pitch of the lower rotor blade. As such, the rotor system is configured to provide optimum pitch of the upper and lower rotor blades during a helicopter mode and an airplane mode.

Abstract: A blade actuation system comprises at least one motor coupled to a rotor blade for changing the pitch angle of the rotor blade. The motor is configured to wirelessly communicate with at least one flight control computer to modulate the pitch angle. At least one generator may be mounted on a rotor shaft to generate power during rotation of the rotor shaft. The generator may provide power to the motor. The flight control computer is operative to provide control signals to at least one of the generators and motors for regulation thereof. The flight control computer, motor and generator may be configured to wirelessly communicate with one another.

Abstract: A mechanical device consisting of two horizontal shafts (4 & 5) in cruciform each rotating axially within two sets of bearings (6), each set positioned near either end and interfaced upon a rotor base (10) which itself is fixed to a vertical power shaft 11 centrally. The powershaft rotates within two other sets of bearings (12). The horizontal shafts are each bolted to and pair of aerofoil section wings (2 & 3) through their respective flange plates (7), each wing being regulated axially by a cam (8) in 90 degree relationship. At any given moment, one wing will always resist (2b & 3b) the external power source (1) of wind or water current thereby bringing about rotation of the powershaft, whilst the opposite wings (2a & 3a) will transiently adopt a free flow posture.

Abstract: A refrigerator having an improved fan which blows air towards a heat exchanger such as an evaporator. The refrigerator has a body having a refrigerating chamber, a freezing chamber, and a chilled air passage which communicates with the refrigerating and freezing chambers. An evaporator for generating a chilled air by heat-exchanging with an air is installed in the body. The evaporator has a spiral-shaped refrigerant pipe which is disposed in a longitudinal direction of the chilled air passage, and a plurality of heat exchange pins disposed around the spiral-shaped refrigerant pipe, for increasing a heat exchange area between the air and the spiral-shaped refrigerant pipe. A fan for blowing the air toward the evaporator and for circulating the chilled air into the refrigerating is installed in the chilled air passage. A motor is fixed to a wall of the body forming the chilled air passage.

Abstract: A cooling apparatus for use in a cooling system is disclosed. The cooling apparatus comprises an evaporator having a conductive pipe which is wound spirally, and a blowing device for blowing air toward the evaporator. A plurality of fins for heat exchange are disposed on the outer surface of the conductive pipe. The blowing device has a blowing motor, a fan being rotated by the blowing motor, and a fan moving device for reciprocating the fan along the blowing direction during the rotation of the fan. Since the cool air generated from the evaporator moves with being rotated by the spirally wound conductive pipe, the air flow becomes complex and thus the heat exchange efficiency becomes high. Also, since the fan is reciprocated along the blowing direction, the blowing power is varied repeatedly and the heat exchange efficiency becomes even higher.

Abstract: An improved windmill has an approximately vertical center support post. The windmill also has a plurality of wheels, each rotatably mounted on a separate horizontal axis, each axis being radially disposed about the center support post. The windmill also has a horizontal annular ring disposed radially about the center support post. The ring is mounted on the wheels so that the ring can rotate about the center support post. The windmill also includes a plurality of approximately horizontal beams. Each beam is radially disposed about the center support post. A first end of each beam is connected to the center support post and a second end of each beam is connected to the annular ring.

Abstract: A hybrid aircraft with a large non-rotating balloon chamber containing a lighter-than-air gas which provides a large static lifting force having a magnitude substantially greater than the weight of the aircraft with a support structure system which is substantially longer in length than in width which is encased by the balloon chamber the support structure system having two ends which protrude from the balloon chamber at opposite sides along the center line of the balloon chamber with a rotatable rotor frame suspended from the ends of the support structure system about the non-rotating balloon chamber. The craft has a plurality of blade airfoils connected to the rotor frame and oriented radially relative to the balloon chamber and which the angle of attack of each blade can be varied. A thrust means is mounted at or near the outboard end of the blade airfoils.

Abstract: An omnidirectional variable thrust propeller for a vehicle includes a hub, plurality of blades, and a plurality of shafts. Each shaft is coaxially rotatably connected to a respective blade and extends through the hub at an acute angle to a hub longitudinal axis. Each shaft has a lever arm and an inner end portion which terminates inside the hub. A reciprocably moveable device engages the inner end portions of the blade shafts to uniformly rotate the blades in one direction when the device moves longitudinally in one direction and uniformly rotate the blades in an opposite direction when the device moves in an opposite direction to enable a change of thrust. Another device pivotally supports the reciprocably movable device at a variable acute angle to the longitudinal axis. Another device selectively move the reciprocably movable device about the pivot point to nonuniformly change the rotation or pitch of the blade that alters the propeller's thrust direction.