Abstract: A cycloidal rotor air vehicle includes an airframe, a first cycloidal rotor assembly supported by the airframe and configured to rotate about a first axis of rotation relative to the airframe, the first cycloidal rotor assembly including a blade having a longitudinal axis oriented parallel to the first axis of rotation, a first motor configured to rotate the first cycloidal rotor assembly about the first axis of rotation, a first servo coupled to the blade of the first cycloidal rotor assembly and configured to adjust the pitch of the blade, and a control system supported on the airframe and configured to control the operation of the first motor and the first servo.

Abstract: A cycloidal rotor is provided having a flexible by actuators or self-flexing blade-positioning tack, which can be brought into shape corresponding to currently desired blade orbit. This rotor can also be provided with frontal shielding or partial enclosure to assure that rotor operates at any speed as if in hovering flight; rotor track can be inclined to produce forward thrust or external thrusters can be used. Optionally in other embodiments blade orbit shape is determined by a variable cam mechanism or the inclination of blade positioning track of fixed shape to produce a change of its projected shape onto blades' plane of operation thus changing blades elliptic orbit. Blade centrifugal force countervailing mechanism is also proposed.

Abstract: The invention relates to a device comprising a lever associated with a stand carrying a rocker connected to the stand by a pivot connection about a first axis, the lever being connected to the rocker by a pivot connection about a second axis, a first transmission shaft with a first connection mechanism connecting the lever to the first transmission shaft, and a second transmission shaft with a second connection mechanism connecting the control lever to the second shaft. The first shaft and the first connection mechanism being connected by a pivot connection about a fifth axis that is inclined relative to the first axis and to the third axis, and the second shaft and the second connection mechanism are connected by a pivot connection about a sixth axis that is inclined relative to the second axis and to the fourth axis.

Abstract: A rotating wing includes a support frame, two connecting rods, two drive systems and a wing frame. The support frame includes a first side frame, a second side frame, a cross frame member, a first guide pin and a second guide pin. The cross frame member is secured to one end of the first and second side frames. A first connecting rod is rotatably retained on the first side frame. A second connecting rod is rotatably retained on the second side frame. The first guide pin extends from the first side frame and the second guide pin extends from the second side frame. The wing frame includes first and second side members. A peripheral groove is formed in an outer surface of the first and second side members to receive the first and second guide pins. First and second drive systems rotate the first and second connecting rods.

Abstract: A vertical takeoff and landing craft that utilizes lifting, propulsion and maneuvering (LPM) assemblies comprising a series of blade foils arranged along track elongated loop paths disposed at the sides of a fuselage. These LPM assemblies are provided with control mechanisms enabling lift, attitude changes, altitude changes and directional flight propulsion and control including those needed for hovering as well as vertical takeoff and landing. The LPM assemblies are configured to drive large volumes of air in a manner and scale favorably similar to conventional rotorcraft while in contrast, providing capability for faster flights by eliminating or minimizing speed limiting factors commonly associated with rotorcraft.

Abstract: A vertical takeoff and landing craft that utilizes lifting, propulsion and maneuvering (LPM) assemblies comprising a series of blade foils arranged along track elongated loop paths disposed at the sides of a fuselage. These LPM assemblies are provided with control mechanisms enabling lift, attitude changes, altitude changes and directional flight propulsion and control including those needed for hovering as well as vertical takeoff and landing. The LPM assemblies are configured to drive large volumes of air in a manner and scale favorably similar to conventional rotorcraft while in contrast, providing capability for faster flights by eliminating or minimizing speed limiting factors commonly associated with rotorcraft.

Abstract: A vertical takeoff and landing craft that utilizes lifting, propulsion and maneuvering (LPM) assemblies comprising a series of blade foils arranged along track elongated loop paths disposed at the sides of a fuselage. These LPM assemblies are provided with control mechanisms enabling lift, attitude changes, altitude changes and directional flight propulsion and control including those needed for hovering as well as vertical takeoff and landing. The LPM assemblies are configured to drive large volumes of air in a manner and scale favorably similar to conventional rotorcraft while in contrast, providing capability for faster flights by eliminating or minimizing speed limiting factors commonly associated with rotorcraft.

Abstract: A propeller having one or more blades eccentrically mounted to a shaft dynamically changes the blade pitch to produce free vortices in a fluid. For extracting energy from a moving fluid, the fluid flow acting on the blades rotates the propeller, while the pitch changes create a fluid flow pattern known as a von Karman vortex street. The resulting time averaged flow field distant from the propeller is a wake flow, and the energy of the fluid flow can be efficiently converted to rotation of a shaft driven device. For propulsion, applied shaft rotation and the dynamic pitch change in a fluid together create a flow pattern that is the inverse of the von Karman vortex street. For either energy extraction or propulsion, the propeller is particularly suited for low flow speeds, where the effects of low Reynolds number induced flow separation on blades may make other propellers inefficient.

Abstract: A system and method for moving an aerial vehicle along a flight path includes rotatable hubs mounted on opposite sides of the vehicle. Elongated airfoils are mounted on the hubs parallel to a common hub axis for rotation about the hub axis on a blade path. Each airfoil defines a chord line and the system includes a gear assembly changeable, during hub rotation, between a first modality wherein airfoil chord lines remain tangential to the blade path (curtate flight), and a second modality wherein airfoil chord lines remain parallel to the flight path of the vehicle (prolate flight). Also, rotation of the hub can be stopped and the airfoils used for fixed wing flight.

Abstract: The wing movement has a gearbox, a reference gear extending through the gearbox and being movably mounted to the gearbox, an input shaft extending through the reference gear and into the gearbox and first and second output shafts movably extending from the gearbox at right angles with the input shaft. There is also provided a motor having a drive shaft connected to the input shaft of the gearbox for rotation of the input shaft. A bracket is connected to the motor base and to the reference gear for retaining the reference gear to the motor base, with an axis of the reference gear in alignment with the drive shaft of the motor. A gearing system is mounted inside the gearbox for rotating the first and second output shafts one full turn in opposite directions relative to each other, upon a rotation of the input shaft one full turn, and for rotating the gearbox one full turn about the reference gear upon a rotation of the first and second output shafts one full turn.

Abstract: An aircraft having vertical takeoff and landing capability having at least first and second laterally extending paddle wheels rotatable on a central axis generally perpendicular to the longitudinal axis of the aircraft and between its nose and tail. Each of the paddle wheels has a plurality of blades pivoted by a system of linear actuators to a determined optimum blade pitch angle. One paddle wheel is positioned adjacent the port side of the aircraft and the other paddle wheel is positioned adjacent the starboard side. The pilot is able to operate the aircraft in all regimes of flight by differentially adjusting the pivot angle of each of the blades. In one embodiment utilizing only a pair of paddle wheels, differential operation of the blades provides lift, thrust, roll, and yaw control of the aircraft, while an aircraft pitch control rotor rotatable about a vertical axis distant from the paddle wheels is provided for controlling pitch of the aircraft.

Abstract: A lift generating mechanism includes a plurality of airfoils each having first and second end surfaces, first and second side surfaces, and a centerline extending between the first and second side surfaces. The airfoil section lying between the first end surface and the centerline is a mirror image of the airfoil section lying between the second end surface and the centerline. A coupling link extends outward from each of the side surfaces of each airfoil. Each connecting link is coupled to an oval shaped guide track and to a larger oval shaped drive chain. The guide tracks and the drive chains are positioned such that first and second transition regions are provided at opposite ends of the oval path through which the airfoils are translated.

Abstract: An arrangement for guiding casting forms, which comprise a so-called working plane (1) in the form of, for example, a beam system, which is capable to support two casting form halves (3,4), between which concrete is intended to be poured. The casting forms further comprise a yoke (11) supported on legs (12), which yoke has the design of, for example, a frame with two preferably mutually parallel, substantially vertical sides (12) and one side (11) located intermediate and perpendicularly to said sides. The yoke (11) preferably is located above the working plane (1) and rigidly connected to the working plane (1).According to the invention at least two guide bridles (14,23) in the form of, for example, strip iron, and a friction device (17) are provided. The guide bridles (14) are intended to be rigidly anchored at one end (15) preferably in a ground level plane (16).

Abstract: A propulsive lifting rotor for an aircraft comprises two wings pivotally mounted about axes parallel to their leading edges. The wings (rotary airfoils) are located at respective sides of a plane at right angles to the rotor axis.

Abstract: An aircraft comprised of a pair of spaced apart interconnected air-frame members and a cargo compartment supported therewithin is provided with a plurality of expansible airfoils mounted for peripheral movement around the air-frame members as driven by a motor and associated drive, movement of the airfoils along the frontmost perimeters of the air-frame members providing the aircraft with forward thrust, and movement thereof along the uppermost perimeters of the air-frame members accentuating the lift provided by the airfoils.

Abstract: An aerodynamic lift mechanism comprises a plurality of aerofoils mounted on two continuous toothed belts which are driven by toothed pulleys. A lever connects each aerofoil to a continuous member which substantially follows the contour of the belts but which is movable relative to the belts. Movement of the continuous member alters the angles of attack of the aerofoils.

Abstract: An aircraft having a body on which is mounted an integrated lift, propulsion and steeing system inclusive of cycloidal propellers having horizontal axes of rotation capable of developing net thrust forces at any given angle in a vertical plane. Each propeller is externally driven and is formed with a circular array of blades at the periphery of a common rim and the blades can be turned to vary the angle of thrust by operation of a common control head.