Abstract: An aircraft of disc-shaped configuration provides the capability of vertical take-off and landing; straight horizontal flight; and three-dimensional maneuverability in the air by means of a plurality of counter-rotating lifting rotors assembled of fixed pitch or of self-adjusting pitch aerofoil blade elements; and, submersibility of the aircraft in water is achieved by means of a marine propulsion module using two counter-rotating hydrofoil rotors for up or down thrust, and a tunneled conventional marine propeller for horizontal travel. The marine propulsion module is detachable for emergency and for use with the main frame aircraft of a variety of other detachable modules for different tasks and missions. Exceptionally adaptable for any existing power plant, including nuclear, it is best suited for the environment-friendly types, like integrated steam motor on hydrogen and oxygen burning.

Abstract: The thrust director assembly may include a thrust director cone with its apex oriented into the fan airstream and a larger thrust vectoring ring concentric with the director cone. The thrust director assembly axis is angularly displaceable relative to the fan axis for modifying the geometry of the duct outlet such that the aperture of the outlet annulus is reduced on one side and simultaneously enlarged at a diametrically opposite side. The effect of the modified geometry is to increase fan thrust on the enlarged side while diminishing thrust on the narrowed side, thereby to develop a lateral thrust component acting on the airframe for providing long moment pitch and roll control.

Abstract: A circular wing aircraft in the form of a helicopter comprising a fuselage and a circular wing assembly. A structure is for mounting the circular wing assembly above the fuselage in a stationary manner. An air impeller unit is rotatively carried within the circular wing assembly. A device is for driving the air impeller unit to rotate about a central axis within the circular wing assembly, so as to provide lift and flight movement while yaw control is maintained.

Abstract: A thrust unit for an aircraft having a lift unit for propelling the aircraft in upward flight. The lift unit includes a duct for directing air substantially downwardly, the duct being shaped so that air exhausting from its downstream end is in a stream having substantially the same cross-sectional dimension of the duct at the downstream end, and an air pump disposed for inducing a draught of air through the duct. In use, the draught of air exhausting from the duct can produce an upward thrust and is substantially non-convergent.

Abstract: The present invention provides a vertical takeoff and landing aircraft vehicle in which a ducted fan with upwardly directed inlet discharges air generally horizontally across a segmented circular wing. Said wing segments are individually controllable in pitch and each includes a spoiler and split flaps to increase effectiveness and sensitivity in lifting and controlling the aircraft. Directional stability and thrust for horizontal movement is provided by controls directing different proportions of total airflow to the various segments around the aircraft and varying the direction of said airflow both radially and vertically. Power failure protection is provided by means for maintaining free rotation of the fan until needed to provide lift at touchdown.

Abstract: In a vertical take-off and landing craft, a pair of nested dome-shaped shells are spaced apart and rigidly interconnected by struts. The outer shell has a central opening formed in its top, and the shape of the shells is such that the space between the two shells progressively widens from the central top part of the shells to the peripheral bottom part of the shells. A circular series of arcuate airfoil units is disposed in the annular space between the bottoms of the shells, and is driven in rotation by an engine mounted on the inner shell. Upon rotation of the circular series of arcuate airfoil units, low pressure is generated above the airfoil units and high pressure below, such that air is drawn down through the central opening of the outer shell to produce a thrust which permits vertical displacement of the aircraft.

Abstract: The invention is a circular airplane with an oblately spheroidal body which derives lift from a wall or ribbon jet exhausting over its upper surface. The jet is produced by a mixed flow fan driven by an internal combustion or gas turbine engine within the body. A fixed guide van assembly removes the swirl from the outlet flow of the mixed flow fan. The jet exiting from the fixed guide vane assembly follows the curved surface of the body, exhausting downward, and produces lift. The magnitude of lift produced in each quadrant of the airplane may be reduced for thrust vectoring by flow control gates which partially block the flow of air from the fixed guide vane assembly. Rotation control vanes introduce a controlled swirl into the flow of air from the fixed guide vane assembly to effect rotation of the airplane. Actuators for flow control gates and rotation control vanes, and a flight control system, are provided.

Abstract: An air lift mechanism has one or more rotating discs within wells in a top deck. Each disc has cambered convexities on its upper surface. A cylindrical wall of each well has operational ports.