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.

Here on Earth, there is a need and is quite essential that we keep moving. But we must be progressive in our living and livelihood while protecting and preserving our planet. There are places to go, people to meet, and business to be had. Designed with electric aircraft and flying cars or taxis in mind, the Augmentable Air Injected Plenum Propulsion Drive for Electric VTOL Operation and Flight is the first electric VTOL propulsion system to employ the concept of opposing air flow and cyclic column compression of those opposing flow(s) to pressurize a plenum chamber. Opposing flow and cyclic column compression is then harnessed for the purpose of augmenting, or amplifying, injected air to provide enhanced air/fluid power to an electric VTOL thrust system for the purpose of VTOL operation and horizontal flight and is multi-modal for VTOL and horizontal flight.

For VTOL operation, air is drawn in by injectors, compressed, and channeled into the plenum chamber which provides energized air to the ventral VTOL thrust assembly which further accelerates the air for vertical propulsion thrust. The PPD then goes into multi-mode transition by diverting air from the plenum chamber into rear injectors as they switch from injector mode to rearward thrust. This described synergistic process which is powered by electricity is what gives the Plenum Propulsion Drive the ability to provide power for flight while keeping the Earth healthy and green.

An amphibious vertical takeoff and landing (VTOL) unmanned device is provided. The amphibious VTOL unmanned device includes a modular and expandable waterproof body, an outer body shell, a gimbaled swivel propulsion system comprising a plurality of VTOL jet engines and VTOL ducted fans, a processor, electronic speed controllers, a two-way telemetry device, a video transmitter, a radio control receiver, a power distribution board, an electrical machine, an onboard electricity generator comprising a plurality of solar cells, a light detection and ranging device, an ultrasonic radar sensor, a plurality of sensors, a tail configured to stabilize the amphibious VTOL unmanned device, a head VTOL ducted fan adapted for VTOL, a plurality of wheels, a plurality of foldable wings configured to create a pressure difference and creating a lift, a plurality of parachutes configured to safely land the amphibious VTOL unmanned device in an emergency.

A vertical take-off and landing (VTOL) aircraft is provided comprising a fuselage (12) defining a forward end and an aft end, the fuselage accommodating at least one engine (56), a left wing (18) and a right wing (20) extending from either side of the fuselage, a lift fan drive system (22) accommodated within each wing, a forward thrust fan drive system (24) fitted proximate the aft end of the fuselage, and a stabiliser arrangement (26) proximate the forward thrust fan drive system. In an embodiment, each wing comprises a rotor housing portion (18.1, 20.1) extending away from the fuselage and a wing tip portion (18.2, 20.2) extending away from the rotor housing portion, the wing tip portion being angled towards the rear and side of the aircraft. In an embodiment, the rotor housing portion comprises two rotor housings, one forward of the aircraft's centre of gravity and one aft of the aircraft's centre of gravity.

VTOL aircraft with a thrust-to-weight ratio smaller than 0.1, during vertical take-off/landing, obtains an another lift, besides a lift generated by low-temp bypass duct (15) directing the low-temp air (18) from the turbofan engine (3) to flow, through its outlet (19) in form of low-temp planar jet (20), over the upper surface of the wing and in the direction of the wingspan, by high-temp bypass duct (15) directing the high-temp air (18) from the turbofan engine (3) to flow, through its outlet (12) in form of high-temp planar jet (13), above the low-temp planar jet (20) in the direction of the wingspan but not burn up the wing and enables the ailerons (1, 2) to control the balances of the aircraft more efficiently.

The invention is to an optionally piloted aircraft that can takeoff and land conventionally or vertically, and can convert between the two. The aircraft is immune to one or more engine failures during vertical flight through multiple engines and the use of a virtual nozzle. Aerodynamic controls are similarly redundant. Hovering flight is enabled with a novel stabilization system. Long range efficient cruise is achieved by turning off some engines in flight and sealing them into an aerodynamic fairing to achieve low drag. The resulting aircraft is capable of CTOL and VTOL, and is capable of converting between the two modes while in the air or on the ground. The aircraft can also be easily taxied on the ground in the conventional manner. Automatic controls considerably reduce the amount of training a pilot needs to fly and land the aircraft in either VTOL or CTOL mode.

The invention pertains to an automobile and more particularly, to a flying car. A flying car, comprises a body, adapted for carrying the payload from once place to another, a tail attached to body at rear end adapted for stabilizing the vehicle, plurality of wheels at the bottom of car connected to a power transmission system, plurality of foldable wings on the sides of body, adapted for creating the pressure difference and creating lift to the vehicle. Further, plurality of jet engines adapted for driving the jet flying car on surface as well as on air. A gimbaled swivel propulsion (GSP) thrust vector control, to controls the direction of the thrust generated by the engines. And plurality of parachutes attached to the flying jet car to safe land the flying jet car under emergency.

Here on Earth, there is a need and is quite essential that we keep moving. But we must be progressive in our living and livelihood while protecting and preserving our planet. There are places to go, people to meet, and business to be had. Designed with electric aircraft and flying cars or taxis in mind, the Augmentable Air Injected Plenum Propulsion Drive for Electric VTOL Operation and Flight is the first electric VTOL propulsion system to employ the concept of opposing air flow and cyclic column compression of those opposing flow(s) to pressurize a plenum chamber. Opposing flow and cyclic column compression is then harnessed for the purpose of augmenting, or amplifying, injected air to provide enhanced air/fluid power to an electric VTOL thrust system for the purpose of VTOL operation and horizontal flight and is multi-modal for VTOL and horizontal flight. For VTOL operation, air is drawn in by injectors, compressed, and channeled into the plenum chamber which provides energized air to the ventral VTOL thrust assembly which further accelerates the air for vertical propulsion thrust. The PPD then goes into multi-mode transition by diverting air from the plenum chamber into rear injectors as they switch from injector mode to rearward thrust. This described synergistic process which is powered by electricity is what gives the Plenum Propulsion Drive the ability to provide power for flight while keeping the Earth healthy and green.

A propulsion system for an aircraft includes a plenum having an intake port and an output port. A fan is coupled to a motor configured to power the fan, and the powered fan is configured to compress ambient air entering the intake port. One or more ejectors are fluidically coupled to the plenum via one or more valves. A nozzle is disposed within the output port and includes a set of vanes. The system operates in a first configuration in which the nozzle vanes are closed and the compressed ambient air exits the plenum only through the one or more valves into the one or more ejectors. The system operates in a second configuration in which the one or more valves are closed, the nozzle vanes are open and the compressed ambient air exits the plenum only through the output port.

A propulsion system for an aircraft includes a plenum having an intake port and an output port. A fan is coupled to a motor configured to power the fan, and the powered fan is configured to compress ambient air entering the intake port. One or more ejectors are fluidically coupled to the plenum via one or more valves. A nozzle is disposed within the output port and includes a set of vanes. The system operates in a first configuration in which the nozzle vanes are closed and the compressed ambient air exits the plenum only through the one or more valves into the one or more ejectors. The system operates in a second configuration in which the one or more valves are closed, the nozzle vanes are open and the compressed ambient air exits the plenum only through the output port.