A machine (10) with lifting system (18) includes a method for generating a resultant force (424) from circulating toroidal flow field (410) and poloidal flow field (420) within nearly confined toroid volume (413). The machine (10) architecture has designs for adaptability at assembly level to achieve modularity for ease of fabrication, maintenance, and operations.

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.

A rotary propulsion engine system designed to propel a craft. Such a rotary propulsion engine system comprises at least two reaction masses or armatures, at least two reaction mass driver assemblies, at least two travel pathways for said reaction masses or armatures, two counterrotating discs housing an equal number of the at least two said reaction mass driver assemblies, and a counterbalancing means used to maintain a balanced distribution of masses about the axis of rotation of each counterrotating disc in order to maintain a zero horizontal torque sum as each reaction mass or armature moves along its ballistic trajectory. Reaction masses are fired into a rotational environment wherein the kinetic energy of said reaction masses is recycled, thereby reducing or eliminating the need for chemical propellant-based propulsion systems, and transporting heavy, finite, and expensive fuels for combustion.

An aircraft includes a fuselage having an upper surface and a lower surface and a plurality of planetary modules housed in the fuselage, an individual planetary module having a first jet engine directed outward of the upper surface of the fuselage and a second jet engine directed outward of the lower surface of the fuselage, the individual planetary module rotatable within the fuselage about a vertical axis.

The invention relates to aviation, and more particularly to designs for vertical take-off and landing aircraft. The present vertical take-off and landing aircraft comprises jet propulsion units containing compressors, overflow valves, air tanks, and a nuclear power plant. Turbines are provided with hybrid engines capable of running on electricity or liquid fuel. On the outside of the aircraft, each turbine is provided with a corrugated tip, consisting of two parts: a base and an extendable part. The bases of the tips are pivotally mounted on the turbine for rotation about their own axis and are coupled to a lateral orientation system for altering the pumping direction. The other part of the corrugated tip is coupled to an angle adjusting system, which, optionally, extends one side of the corrugated part outside the body in order to alter the pumping angle by more than 90 degrees from vertical to horizontal.

The invention provides aerodynamic lift, or downward thrust for the amphibious environment, by means of two conical frames that are opposed at the bases and counter-rotating, thus cancelling out the opposing torque moment when rotating, being provided with concentric rows of fixed and retractable blades having variable angle of attack, arranged along the generatrix, separated by the fixed central area of the frame, where the power plant and the electro-mechanical elements that enable its operation are located, the cabins being situated in the conoidal hollow space of both, thus forming a body of lenticular geometry. The invention is provided with an electro-aerodynamic stabilisation system and landing gear (T), propulsion and manoeuvring being provided by pressurised air supplied through variable-area nozzles, and by the thrust due to the tilting of its axis (Y), with a fairing. Its functions and performance are similar to those of a helicopter.

A vertical take-off and landing aircraft comprising two turbines, the lower of which is plate-like, and the upper is flat or plate-like. Each turbine comprises a reactive power plant comprising an air engine and receivers connected to a compressor. The body of each turbine is mounted on a metallic disc connected to a vertical shaft of the aircraft, and is equipped with vanes. The vanes are mounted in a single row along the perimeter of the body or are arranged in a single tier such that the position thereof can be changed. The aircraft can comprise intermediate turbines which are mounted between the upper and lower turbine and are flat or plate-like. The body of each turbine is metallic and comprises two rings, one of which is connected to the disc, and also radial struts mounted along the perimeter of the turbine body and connected to the rings and vanes.

A rotary wing with a curved outer surface, inlet openings and an edge foil for use in helicopters to improve lift and efficiency, maximizing the gross weight lift and the horizontal flight speed capabilities and minimizing performance penalties and unstable, inefficient operation.

A device for the transportation of people and cargo is described. The device is a gyro-rotating flying device including a pod structure configured to transport one or more contents. The pod structure includes a gyro pod to contain the one or more contents. An engine is included to propel the pod structure into flight. A power supply provides energy for the engine and a control unit. The control unit allows a user the ability to regulate operation of the engines. Manipulation of the engine adjusts the orientation of the pod structure and engine around the gyro pod. The gyro pod is configured to remain level during flight.

An aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades. The main rotor blades are connected to a first annular gear that rotates in a first direction and the counter-rotation blades rotate are connected to a second annular gear that rotates in a second direction that is opposite the first direction for anti-torque. Planetary gears simultaneously drive the first and second annular gear at about the same speed.