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.

A safety arrangement for an aircraft, especially for amphibious aircraft, being configured for determining a type of landing surface (such as water/solid ground) and including: two transceivers (301, 302); the first transceiver (301) configured to operate on first electromagnetic wavelength and the second transceiver (302) configured to operate on second electromagnetic wavelength differing from the first wavelength, and at least one of transceivers is configured to receive the reflections electromagnetic wavelengths, and determining element for determining the type of the landing surface based on the properties of two electromagnetic wavelengths reflected from the landing surface and for outputting a signal indicating the type of the determined landing surface.

Presented is a small, unmanned aircraft systems (aka drone) configured for amphibious use in water environments. Also presented is a capture device for the capture and recovery of a small, unmanned aircraft system.

A ground effect flight vehicle comprising, a fuselage (1), a wing assembly (4, 5), an engine assembly comprising one or more engines or engine sets (6, 7, 8), and a hull (2) for enabling floatation of the vehicle; wherein the wing assembly (4, 5) comprises stabilizer wings (4) and/or the one or more engines (6, 7, 8) are equipped to provide an airflow departing from the engines (6, 7, 8) which is positionable in one of multiple positions, a first position of the multiple positions which is arranged to generate lift for vertical take-off purpose, and a second position of the multiple positions which is for horizontal cruise flight.

A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.

An attachment for an aircraft. The attachment comprises a single, central float portion positioned under a centre of the aircraft, and a retraction apparatus. One end of the retraction apparatus is attached to the float portion and another end of the retraction apparatus is attached to the underside of the aircraft. The retraction apparatus is deployable and retractable between a first and second configuration, such that, with the retraction apparatus in the first configuration, the float portion is retracted towards the aircraft fuselage and, with the retraction apparatus in the second configuration, the float portion is deployed away from the aircraft fuselage. When the float portion is deployed, the float portion allows the aircraft to land on a body of water. When the float portion is retracted, the aircraft is able to land on a ground surface. The attachment can be retrofit to an existing non-amphibious aircraft.

An amphibious aircraft includes two floats, each having a front hull and an elevated rear hull with a step between the two. Each float also has a retractable main landing gear with a main wheel. The step and the main wheel are placed strategically close to each other to provide readily controllable landings and takeoffs from water or land. To achieve such close placement of the step and the main wheel, a clearance notch in the front hull, near the step, provides space into which part of the main landing gear can extend when the main wheel descends to a deployed landing position. The size of the notch is sufficiently small to have an inconsequential effect on the front hull's ability to hydroplane. In some examples, a colored portion of the main landing gear protrudes above the float to provide a visual indication of when the main wheel is retracted.

A craft includes a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.

The invention provides a float plane having a fuselage, a wing, and two floats mounted to the fuselage. In one group of embodiments, the float plane is a firefighting float plane that includes a water tank and a water scooping assembly. In another group of embodiments, the float plane includes a spreader bar suspension assembly. In certain embodiments, the float plane is a firefighting float plane that includes a water tank, a water scooping assembly, and a spreader bar suspension assembly.

An aerial and preferably marine vehicle intended to operate in its principal mode near the surface of water or land employing the Wing-in-Ground Effect (WIG) and capable to take-off and land vertically (VTOL) by means of thrust vectoring, which vehicle has a wing arranged at the lowermost part of the fuselage, propulsion units comprising four rotatable pylons extending transversely in pairs on both sides of the upper part of the fuselage, four elongated nacelles mounted on the outer tips of said pylons, which nacelles contain electric motors (E) and provided with propellers at their extremities, so that the rotation of the pylons results in turning the nacelles and thrust of propellers from substantially vertical, ensuring take-off and landing, to substantially horizontal providing a flight mode, retractable hydroskis for emergency landing on water, while said propulsion units and said wing are spaced apart vertically and horizontally and do not overlap.