A first embodiment includes a circuit based unmanned aerial vehicle (UAV) including at least one enclosed air duct vertical z-force circuit, at least one enclosed air duct lateral y-force circuit, and at least one enclosed air duct longitudinal x-force circuit whereby each circuit includes a plurality of fans within respective fan tunnels and a plurality of rotational cylinders within archways. The UAV utilizes a magnus effect at strategic points along each respective circuit to apply navigational force thereon. A second embodiment includes a circuit based unmanned aerial vehicle (UAV) including a first and second air duct circuit joined at a medial trunk. Each circuit includes a plurality of fans within respective fan tunnels and a plurality of rotational cylinders within archways. The second embodiment also utilizes the magnus effect at strategic points along each respective circuit to apply navigational force thereon.

A first embodiment includes a circuit based unmanned aerial vehicle (UAV) including at least one enclosed air duct vertical z-force circuit, at least one enclosed air duct lateral y-force circuit, and at least one enclosed air duct longitudinal x-force circuit whereby each circuit includes a plurality of fans within respective fan tunnels and a plurality of rotational cylinders within archways. The UAV utilizes a magnus effect at strategic points along each respective circuit to apply navigational force thereon. A second embodiment includes a circuit based unmanned aerial vehicle (UAV) including a first and second air duct circuit joined at a medial trunk. Each circuit includes a plurality of fans within respective fan tunnels and a plurality of rotational cylinders within archways. The second embodiment also utilizes the magnus effect at strategic points along each respective circuit to apply navigational force thereon.

The present disclosure relates to a rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a shrouded duct that is arranged in the aft region and that forms an inner air duct, wherein the shrouded duct is formed to generate sideward thrust for main rotor anti-torque in forward flight condition of the rotary wing aircraft; and a propeller that is at least configured to propel the rotary wing aircraft in the forward flight condition; wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and wherein the propeller is rotatably mounted to the shrouded duct such that the circular propeller disc is at least essentially arranged inside of the inner air duct.

The present disclosure relates to a rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a shrouded duct that is arranged in the aft region and that forms an inner air duct, wherein the shrouded duct is formed to generate sideward thrust for main rotor anti-torque in forward flight condition of the rotary wing aircraft; and a propeller that is at least configured to propel the rotary wing aircraft in the forward flight condition; wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and wherein the propeller is rotatably mounted to the shrouded duct such that the circular propeller disc is at least essentially arranged inside of the inner air duct.

An ionic propulsion system for an aircraft having an airfoil includes a first conductor and a second conductor, the first conductor and the second conductor being disposed at least partially within the airfoil when not in use. The propulsion system includes an actuator for extending the first conductor and the second conductor from an end of the airfoil such that the first conductor and the second conductor are in the airstream of the aircraft, the first conductor being upstream of the second conductor in the airstream. The propulsion system includes a power supply for supplying current to the first conductor and the second conductor to ionize the air particles in the vicinity of the first conductor and the end of the airfoil to create a flow of the ionized particles from the first conductor toward the second conductor.

A lift control device actively controls the lift force on a lifting surface. The device has a protuberance near a trailing edge of its lifting surface, which causes flow to separate from the lifting surface, generating regions of low pressure and high pressure which combine to increase the lift force on the lifting surface. The device further includes an arrangement to keep the flow attached around the protuberance or to modify the position of the protuberance in response to a command from a central controller, so as to provide an active control of the lift between a maximum value and a minimum value.

A lift control device actively controls the lift force on a lifting surface. The device has a protuberance near a trailing edge of its lifting surface, which causes flow to separate from the lifting surface, generating regions of low pressure and high pressure which combine to increase the lift force on the lifting surface. The device further includes an arrangement to keep the flow attached around the protuberance or to modify the position of the protuberance in response to a command from a central controller, so as to provide an active control of the lift between a maximum value and a minimum value.

A system takes advantage of the Magnus effect to increase the efficiency of a moving structure by increasing the forces generated by a fluid moving relative to the structure, e.g., to improve lift, drag, etc. The system includes a structure having a first side and a second side opposite the first side. An object coupled to the structure, e.g., a cylinder, is exposed to a fluid such as air. The object is journaled for rotation relative to the structure so as to disrupt the fluid around the object. A drive source causes the object to rotate relative to the structure so as to cause a select one of an upward lift, or a downward drag.

A system takes advantage of the Magnus effect to increase the efficiency of a moving structure by increasing the forces generated by a fluid moving relative to the structure, e.g., to improve lift, drag, etc. The system includes a structure having a first side and a second side opposite the first side. An object coupled to the structure, e.g., a cylinder, is exposed to a fluid such as air. The object is journaled for rotation relative to the structure so as to disrupt the fluid around the object. A drive source causes the object to rotate relative to the structure so as to cause a select one of an upward lift, or a downward drag.

A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight; and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal.