Abstract: An ornithopter aircraft has a main body. A first wing frame mount and a second wing frame mount are mounted to the main body. A first wing frame is rotably mounted to a first wing frame axle on the first wing frame mount. The first wing frame is configured to rotate relative to the main body and the rotation can be powered. The first wing frame feathers are rotably mounted to the first wing frame at first feather axles and the first wing frame feather rotation can be powered. The first wing frame feathers are configured to rotate relative to the first wing frame and the first wing frame feather rotation can be powered. A second wing frame is configured to be rotably mounted to a second wing frame axle on the second wing frame mount.

Abstract: A system for altitude control of an autogyro includes an unpowered rotor for generating lift and a forward propulsion system for generating a horizontal thrust component of a thrust vector for propelling the autogyro forward during flight. The system for altitude control also includes at least one thrust steering control devices configured to steer thrust generated by the forward propulsion system such that the forward propulsion system generates a vertical thrust component of the thrust vector.

Abstract: A tiltrotor aircraft includes a propulsion system with a fixed engine and a rotatable proprotor. The engine is located below the wing of the tiltrotor aircraft, and the rotatable proprotor assembly is mounted on the top surface of the wing. The engine and proprotor assembly are connected via a series of one or more gearboxes that route the engine output from the engine to the proprotor.

Abstract: A cargo transportation system includes a cargo platform having an upper surface and a perimeter. A propulsion system is disposed about the perimeter of the cargo platform. The propulsion system includes a plurality of propulsion assemblies, each including a propulsion unit disposed within a housing defining an airflow channel having an air inlet for incoming air and an air outlet for outgoing air such that the outgoing air is operable to generate at least vertical lift. A power system disposed within the cargo platform provides energy to drive the propulsion system. A flight control system operably associated with the propulsion system and the power system controls flight operations of the cargo transportation system.

Abstract: A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.

Abstract: A hybrid rotor for an aircraft includes a Magnus rotor rotatable around a Magnus rotor axis and a transverse flow rotor that is kept rotating around an axis of rotation and has a number of axially extending rotor blades that are actuatable to rotate around the axis of rotation and are configured stationary relative to the tangential angle position. The Magnus rotor is located within the transverse flow rotor and has an axis extending in the direction of the axis of rotation. The guide mechanism has a housing segment partially surrounding the transverse flow rotor in the circumferential direction. The housing segment has an adjustment mechanism and is deflectable relative to the Magnus rotor axis. The housing segment is aligned such that the transverse flow rotor generates a propulsion force and causes a transverse flow onto the Magnus rotor to generate lifting force by way of a Magnus effect.

Abstract: An aircraft that has a set of wings which spin about respective axes that are laterally spaced apart in a horizontal plane of the aircraft, parallel to each other, and positioned adjacent respective frame portions, each of said frame portions defining a continuous surface, having a semi-circular cross-section means being provided to drive the sets of wings so that, as they spin, each wing of said sets of wings moves sequentially upwards inside its respective frame portion, and downwards outside its respective frame portion so as to provide lift to the aircraft.

Abstract: A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading edge (202) of the main portion of the proprotor blade. The slot (215) is selectively shaped so the a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat (217) and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft (11) and civilian-type tiltrotor aircraft (111) with only minor variations to accommodate the different shapes of the proprotor blades.

Abstract: A method for transferring airplanes and an unmanned airplane transfer system. The airplane transferring system includes: receiving a transfer signal responsive of a movement of an airplane control component; and transferring an airplane, by an unmanned airplane transfer system, in response to the transfer signal.

Abstract: In order to continuously rotate an impeller having an axis parallel to a ground surface in one direction to generate lift, a cover close to a periphery in an opposite lift side is provided within a half of an outer periphery of the impeller, and a cylindrical scroll wheel integrally and concentrically rotating with the impeller is provided in a cavity portion near a root of the impeller, whereby a balance between the lift side and the opposite lift side is broken aerodynamically.

Abstract: VTOL micro-aircraft comprising a first and a second ducted rotor mutually aligned and distanced according to a common axis and whose propellers are driven in rotation in mutually opposite directions. Between the two ducted rotors are positioned a fuselage and a wing system formed by wing profiles forming an X or an H configuration and provided with control flaps.

Abstract: A method and system for propelling or sustaining marine vessels and aircraft. A propulsive force is developed in a gaseous or liquid fluid as a result of rotation of two pairs of generally parallel blades around two perpendicular intercrossed axes with the same speed. The blades are mounted with variable angles of incidence in the planes of rotation around one of the axis and are rotated together with this axis around the second axis. As a result, the blades work simultaneously both in a paddling manner and as a screw propeller with both sides of the blades being used consecutively as working surfaces. In preferred embodiments of the propulsion apparatus, the blades are mounted on a rotated gearbox which is mounted on a hollow driving shaft. The gearbox includes planetary bevel gear engagement with sun gears mounted on a support coaxially to the hollow driving shaft.

Abstract: A method and system for developing a propulsive force which can be utilized for driving different types of water, air or land vehicles. The propulsive force is developed by rotating a driving shaft with four blades which are simultaneously rotated with the same speed around two perpendicular intercrossed axes in different directions not interfering with each other. Each blade lies generally in a plane perpendicular to the intercrossed axis around which it is rotated. Preferably, the blades have airfoil sections. During such double rotation the radial extensions of the propeller blades relative to the driving shaft are changed as a function of the angle of rotation. The rotated blades can work simultaneously both in a paddling manner and as a screw propeller with the angle of incidence of each of the blades in the plane of rotation around an intercrossed axis changed automatically depending on the position of the blade relative to the driving shaft.

Abstract: A method and system for developing a propulsive force which can be utilized for driving different types of water, air or land vehicles. The propulsive force is developed by rotating a propeller shaft with four generally flat propeller blades mounted on two perpendicular intercrossed axles, which are fixed to the propeller shaft in a plane perpendicular to its axis. The surface of each blade is lying in a plane perpendicular to the axle on which it is mounted and the blades are rotated in these planes around these intercrossed axles with the same speed in different directions, so that the adjacent propeller blades are rotated clockwise and counterclockwise not interfering with each other.

Abstract: A flying apparatus has a body; power means; and lifting force generating units, the lifting force generating units being arranged parallel to a plane of symmetry of the body and turnable in a vertical plane, each of the lifting force generating units is formed as a rotor including a plurality of aerodynamic blades arranged uniformly on a disk and at equal distances from an axis of rotation so as to be turnable.

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: The invention relates to a rotor able to develop in a fluid lifting and/or propelling forces and its process for control. Said rotor comprises several profiled blades (9) with axes parallel to the drive axis (3); the incidence of each profiled blade is controlled in real time as a function of its angular azimuth and the flight conditions, for obtaining the desired lift and propulsion forces.

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 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.