Patent ID: 9394047
Filing Date: 2016-07-19
CPC Classification: B64C

Claim Text:
1. A motorized aeroplane comprising: a fuselage having a base; a landing gear comprised of wheels and skis, the gear being retractable into the fuselage; at least two hydrofoils provided at the base of the fuselage, the hydrofoils being configured to provide hydrodynamic lift and stabilization arranged downwards of the aeroplane in a form of an inverted V, wherein: a junction between each hydrofoil and the fuselage is situated forward from a center of gravity of the aeroplane, a distance separating the junction between each hydrofoil and the fuselage, with respect to the center of gravity of the aeroplane is greater than 0% but not more than 170% of a mean aerodynamic chord of a main wing of the aeroplane, each hydrofoil is inclined downwards from a respective leading edge in a direction of a respective trailing edge, and a straight line connects the leading and trailing edges such that, with a horizontal tangential plane passing through the bottom of the fuselage, a nominal pitch angle of each hydrofoil is between 2° and 12°, a part of each hydrofoil is located beneath the horizontal tangential plane of the aeroplane, and another part of each hydrofoil is disposed forward from the center of gravity, as viewed from a front view of the aeroplane, a first anhedral angle of each hydrofoil with respect to the horizontal tangential plane is, in a normal position of the aeroplane, between 10° and 50°, and each hydrofoil is provided with a flexible intermediate section allowing a free end of the hydrofoil to flex upwards to the horizontal tangential plane passing through the bottom of the fuselage.