An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

A propulsion system includes a source of compressed fluid, at least one thruster in fluid communication with the source, at least one turbine in fluid communication with the source and coupled to a propeller, and an apparatus for selectively providing the compressed fluid to one or both of the at least one thruster and the at least one turbine.

A hybrid VTOL/high speed aircraft may comprise systems and functions for in flight configuration changes from high lift helicopter or VTOL mode to fixed or swing-wing high speed aircraft mode to accommodate a variety of functions or missions.

In embodiments, a system and method for providing propulsion and control to an air vehicle, and for operating the vehicle, include at least three propulsion units that provide vertical thrust for vectored thrust flight, in which at least one or two of the propulsion units also provide thrust for vectored thrust cruising or aerodynamic flight by suitably tilting the respective propulsion units for changing the thrust vector. At the same time, the three or more propulsion units are operated to generate controlling moments to the air vehicle about three orthogonal axes, pitch, roll and yaw, during vectored thrust flight (hover, cruising, etc.) or during aerodynamic flight for controlling the vehicle.

This aircraft without wings is designed to allow unmanned flight to any place on earth by simplified construction. This is accomplished by turning the gas turbine engine upward, by means of a geodesic flight organizer, by air mass cooling, and because of its massive amount of power. The VTOL aircraft is never detained by looking for a runway. A conventional jet aircraft needs a long runway to go fast enough for takeoff speed. That's why airports are so big, because conventional jet planes sometimes have to take off at 200 miles per hour for lift. This aircraft shoots straight upwards and then the horizontal stabilizers are turned on. The small-sized box or barrel goes anywhere you want it to go. The aircraft is designed to allow unmanned flight to any place that has air, or the gas of another planet. The aircraft is guided by using a geodesic flight organizer and a gyro. The air mass is split so part goes to the combustion chamber and the other part goes to the thruster for oxygen power. This airplane goes straight up from anywhere, quickly. And the VTOL flight is not exposed to finding a runway, anywhere. The unmanned aircraft will be used to send medical equipment or emergency fire-fighting apparatus, or any other material as needed.

An aerial vehicle includes a fuselage situated at the center and a main wing body having a pair of half-wings extending on transversely opposite sides of the fuselage. Each half-wing includes an orientable horizontal surface or plane, which acts as an aerodynamic control, and a fixed winglet.

A method of using a bagged power generation system comprising windbags and waterbags integrated with drones and adapting drone technologies for harnessing wind and water power to produce electricity. An extremely scalable and environmentally friendly method, system, apparatus, equipment, techniques and ecosystem configured to produce renewable green energy with high productivity and efficiency.

A power plant for an aircraft such as an unmanned aero vehicle in which a gas turbine engine drives an electric generator to produce electrical power for a system load of the aircraft. An engine control unit monitors engine performance and regulates engine power output through fuel flow control to a combustor. A power control module regulates power output of the generator to the system load and to a battery through a bus. A pulse width modulation is used between the power control module and the bus to optimize performance of the gas turbine engine instead of adjusting fuel flow to the combustor.

Proposed is an airfoil wing-shaped aircraft including a body having a wing-shaped longitudinal cross-section and having an upper surface on which a shape of a concave curvature-surface portion is formed along a center axis in a streamwise direction, a fluid inlet being formed in each of the opposite lateral sides of a leading portion of the body, and a fluid output being formed in each of the opposite lateral sides of a tail portion of the body, wherein a duct connects the fluid inlet and the fluid outlet to each other.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.