Abstract: A vertical take-off and landing (“VTOL”) aircraft has at least two flying wings (“FW”) with each FW equipped with multiple transverse-radial propellers or a propulsion system for producing a lift force and thrust force on the stationary or non-stationary FW. This VTOL/FWA is capable of exchanging payloads horizontally, as well as vertically, with a stationary or a moving object. In particular, the VTOL/FWA can “walk” on a building wall to adjust and anchor its position in order to rescue people from a high-rise-building window horizontally.

Abstract: A method comprises collecting a data set of field characterization measurements at a location inside a reverberant cavity excited by signals having multiple discrete electromagnetic frequencies; and performing a number (n) of circular shifts on the data set by a frequency step (?f) and computing a covariance-based coefficient at each shift until the coefficient indicates a lack of correlation. The method further comprises computing a quality factor (Q) of the reverberant cavity as fc/(?f×n), where fc is center frequency of the data set.

Abstract: In some embodiments, a rotorcraft includes a fuselage, a tailboom, a drive system and a variable thrust cross-flow fan system. The cross-flow fan system includes a cross-flow fan assembly that is mechanically coupled to a drive shaft and operable to rotate with the drive shaft about a longitudinal axis. The cross-flow fan assembly includes first and second driver plates having a plurality of blades rotatably mounted therebetween. The blades are disposed radially outwardly from the longitudinal axis and have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis. The blades are moveable between a plurality of pitch angle configurations. A control assembly is coupled to the blades. The control assembly is operable to change the pitch angle configuration of the blades to generate variable thrust at a substantially constant rotational speed of the cross-flow fan assembly.

Abstract: This invention presents a VTOL aircraft with two or more Flying-Wings (FWs), where each FW is equipped with multiple Transverse-Radial propellers capable of producing lift force and thrust force on the stationary or non-stationary aircraft. The aircraft is capable of exchanging payloads horizontally as well as vertically with a stationary or a moving object. In particular, this invention illustrates how this aircraft can “walk” on the building wall to adjust and anchor its position in order to rescue people from a high-rise-building window horizontally.

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: 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 vehicle capable of driving on land, air or water comprises of a fuselage (1), a main engine or a main motor, and a power control and transmitting system. A main shaft (2) is provided at two sides of the fuselage. Blade sleeves (6) are fixed to the main shafts. Blade handles (7) capable of spinning around own axes are mounted on the blade sleeves. Blades are fixed to the blade handles. Blade open-close devices are installed on the fuselage and/or on the main shafts to control the blades to rotate relative to the blade sleeves and the main shafts. The blade open-close device is a mechanism that can open and close the blades once a cycle of rotating along with the main shaft. When opened, blades' broad flat surfaces are parallel or generally parallel with the main shafts. When closed, the blades' broad flat surfaces are perpendicular or generally perpendicular to the main shafts.

Abstract: The invention relates to an aircraft comprising a fuselage and at least two substantially hollow cylindrical lifting bodies which are applied to the fuselage and comprise a plurality of rotor blades which extend over the periphery of the lifting bodies, the periphery of the lifting bodies being partially covered by at least one tail surface. The aim of the invention is to provide an aircraft with an extremely high degree of maneuverability, compact dimensions and economy of fuel. To this end, the lifting bodies are driven by at least one drive unit and respectively comprise a cylindrical axis which is substantially parallel to a longitudinal axis (1a) of the aircraft.

Abstract: A vertical take-off and landing (VTOL) aircraft comprises (1) a fuselage having a front end, a rear end and two lateral sides, the fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (2) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage with movable surfaces for controlling the aircraft; and (3) a wing on each side of the fuselage having a front edge, a trailing edge and an upper surface extending from the front edge to the trailing edge. Means are provided for increasing the speed of an airstream flowing over the upper surface of each wing.

Abstract: An STOL or VTOL winged aircraft comprises a fuselage and a fixed wing attached to the fuselage and extending outward from the two lateral sides thereof, forming one wing component extending outward from one side of the fuselage and a second wing component extending outward from the opposite side of the fuselage. At least one “thruster” is disposed in each wing component to provide vertical lift to the aircraft when the aircraft is stationary or moving forward only slowly. The thruster includes a shaft mounted for rotation in the respective wing component and extending substantially parallel to the wing axis and a plurality of fan blades attached to the shaft for movement of air. A shroud is preferably arranged in each wing component, adjacent to the fan blades, for directing the airflow downward or rearward.

Abstract: A vertical take-off and landing aircraft has an airframe body that defines a loop-shaped path of travel for a plurality of movably-mounted wings that are transversely disposed relative to a longitudinal axis of the aircraft. The airframe body has two side frames that are transversely spaced apart in parallel relation to one another and interconnected by a pair of fixed wings that do not follow the path of travel of the movably-mounted wings. A passenger compartment is positioned between the two side frames and within the loop traveled by the movably mounted wings.

Abstract: A “wing in ground effect” aerial vehicle includes a wing mounted on a fuselage, and two cycloidal propulsion units for providing lift, thrust and longitudinal control. Additional lift is provided by a lighter-than-air gas such as helium contained in the fuselage. Operationally, the two cycloidal propulsion units and the volume of lighter-than-air gas are concertedly regulated to achieve “wing in ground effect” flight. Importantly, the two cycloidal propulsion units may operate in one of several modes, to include a curtate mode, a prolate mode, and a fixed-wing mode. Additionally, the vehicle may hover. Also, a thruster unit is mounted on the fuselage for providing forward thrust in combination with, or in lieu of, the two cycloidal propulsion units.

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: 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: An aircraft has its wing defined as a wing-like body with a tangential flow rotor in the leading edge. A shroud, under the lower part of the tangential flow rotor, terminates in at least one movable flap defining a lift-generating lip when the rotor is rotating such that the upper part of the rotor, projecting above the level of the upper surface of the wing-like body, is moving rearwardly. Differential adjustment of the flaps in the wings to either side of an aircraft centerline allows directional control and control of banking of the aircraft.

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: A mechanism and method for generating lift with the Bernoulli Effect. A pair of cylindrical impellers create a pair of counter rotating forced linear vortices. Fast moving, low pressure air surrounding the forced vortices comes into contact with the upper sides of semicylindrical lifting surfaces. Higher pressure, slower moving air is in contact with the lower sides of the lifting surfaces. The velocity differentials between the upper and lower sides of the lifting surfaces cause a pressure differential that produces lift.

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: A rotary wing device adapted to be rotated about its longitudinal axis and to be propelled forwardly with its longitudinal axis having a small upward pitch angle relative to the forward flight direction in order to generate an upward lifting force on the device. The rotary wing device has a plurality of laterally spaced-apart cylindrically disposed wing segments. Preferably, the wing segments are parallel to each other, are parallel to the longitudinal axis of the device, and have streamlined edges. Preferably, the wing segments are mounted for rotation about the longitudinal axis of the device by front and rear mounting rings which engage and stabilize the front and rear tips of the wing segments. The mounting rings are perpendicular to the wing segments and have streamlined edges. The preferred embodiment is a throwable aerial toy having its center of mass located on the forward half of its longitudinal axis and being statically and dynamically balanced relative to said longitudinal 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: A fluid flow device comprises a rotor housed in a casing having slot-like intake and outlet openings. Groups of such devices can be used to form an aircraft propulsion system by drawing-in air from above through the intake openings and forcing the air downwardly through the outlet openings to provide lift and horizontal thrust, the effect being similar to that produced by the wing of a bird.