A seaplane float propulsion system that is configured to provide maneuverability and directional movement of a seaplane subsequent the engine and propeller being deactivated. The present invention includes a first float member and a second float member wherein the first float member includes a first propulsion assembly mounted therein and the second float member includes a second propulsion assembly mounted therein. The first propulsion assembly and second propulsion assembly are identically constructed. The propulsion assemblies are independently controlled so as to provide both directional and rotational movement of the seaplane to which the present invention is operably installed. The propulsion assemblies include elements that are operable to intake and direct water flow in order to create the desired movement of the seaplane in which the seaplane float propulsion system is installed. The propulsion assemblies include an intake element that provides ideal fluid and aero dynamics.

An aircraft which includes a float-wing having a leading edge, a trailing edge, and an airfoil shape to produce aerodynamic lift when the float-wing flows through air at a lift-producing angle of attack in a forward flight mode of operation. The float-wing further includes a submersible portion that includes at least the trailing edge and which is constructed of materials and in a shape selected to produce a buoyancy force sufficient to prevent at least a non-submersible portion of the aircraft from being submersed under conditions in which the aircraft is in a waterborne non-flight position in which at least the trailing edge of the float-wing is submersed but at least the non-submersible portion of the aircraft is not submersed.

A flotation system for an aircraft that includes a battery system providing power to the aircraft is presented. The flotation system can include a water propulsion system enables maneuvering of the aircraft, such as a seaplane, on the surface of water. The system can include waterjets located on floats of the aircraft that enable maneuvering of the aircraft in forward, backward, and lateral directions as well as rotational motion. The systems are quieter in operation than the main engine of the aircraft and provide precision maneuvering for docking or active stabilization of the aircraft's position.

The invention refers to a VTOL aircraft of the type that uses certain aerodynamic phenomena to increase the lifting force and to reduce the thrust/weight ratio. An aircraft 1 uses a propulsion system 2 consisting of four thrust producing elements, two in front 3 and two in rear 4. Each front thrust producing element 3 contains at least one front rotor 5 operated by at least one front electric motor, fixed on a fuselage 10. Each rear thrust producing element 4 contains at least one rear rotor 7 driven by at least a rear electric motor 8, fixed on the fuselage 10. On the fuselage 10 is attached symmetrically a front wing 12. On the fuselage 10 is attached symmetrically a rear wing 13. The wing 12 and 13 are used also in static conditions respectively in take-off and landing.

A vertical take-off and landing (VTOL) aircraft (100) having: a wing structure having right and left side forward wings (20, 22); and right and left side rearward wings (30, 32), each of the right side wings (20, 30) being connected, and each of the left side wings (22, 32) being connected in a box wing configuration; wherein each wing (20, 22, 30, 32) has a fixed leading edge (100) and at least one moveable trailing control surface (110), further wherein each wing (20, 22, 30, 32) has at least one motor pod (195), the motor pod (195) being pivotally mounted to an underside of the fixed leading edge (100), and fixedly secured to the trailing control surface (110).

An aircraft having a sponson extending substantially transversely relative to a main body of the fuselage of the aircraft and substantially perpendicularly relative to a vertical anteroposterior plane of symmetry P of the main body of the fuselage when the aircraft is standing on a horizontal support, the sponson including a notch locally reducing a cross-section of the sponson in a connection zone of the sponson, the connection zone being suitable for being arranged in the immediate proximity of the main body of the fuselage of the aircraft from which the sponson emerges transversely, the notch being open at least to a front outside face and to a top outside face of the sponson and being suitable for receiving a bottom portion of a sliding side door when in its open position.

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.

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.

Disclosed herein is a water helicopter includes a fuselage, first and second fixed wings extending outwardly from left and right ends of the fuselage, first and second propellers disposed in a spaced apart configuration on a top surface of the fuselage, and a landing and float gear attached to a bottom surface of the fuselage for enabling landing of the water helicopter on water.

A firefighting float plane having a fuselage, one or more wings, two floats, a water scoop associated with each float for filling a water tank of the firefighting float plane, and systems and/or methods for deploying the water scoops to prevent (and/or mitigate the effects of) asymmetric deployment and/or retraction of the water scoops.