초록 ▼

An aeroplane includes a fuselage having a pair of hydrofoils providing hydrodynamic lift and stabilization arranged in the form of an inverted V. The junction between each hydrofoil and fuselage is situated forward the center of gravity of the aeroplane. The distance separating the junction between

An aeroplane includes a fuselage having a pair of hydrofoils providing hydrodynamic lift and stabilization arranged in the form of an inverted V. The junction between each hydrofoil and fuselage is situated forward the center of gravity of the aeroplane. The distance separating the junction between each hydrofoil and the fuselage, with respect to the center of gravity of the aeroplane is comprised between 0 and 170% of the mean aerodynamic chord of the main wing of the aeroplane, preferably between 20% and 135%. Each hydrofoil is inclined downwards, from its leading edge in the direction of its trailing edge. The straight line connecting these two edges form, a nominal pitch angle comprised between 2 and 12°, preferably between 6 and 8°. A part of the hydrofoil is located beneath a horizontal tangential plane of the aeroplane; each hydrofoil has a flexible intermediate section allowing the hydrofoil to flex upwards.

대표청구항 ▼

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 arrange

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°, andeach 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. 2. The aeroplane according to claim 1, wherein a bottom surface of each hydrofoil is straight or has a concaveness that is directed upwards in the area of a trailing edge of each hydrofoil. 3. The aeroplane according to claim 1, wherein, as viewed from above the aeroplane, a sweepback angle of each hydrofoil with respect to a transverse axis of the aeroplane and measured from the transverse axis towards a rear of the aeroplane is, in the normal position of the aeroplane, between 0° and 60°. 4. The aeroplane according to claim 1, further comprising: at least one aileron for adjusting the pitch angle in a range of approximately 10° with respect to the nominal position of the pitch angle. 5. The aeroplane according to claim 1, wherein the external side of each hydrofoil is extended by an aileron extending in oblique manner both upwards and opposite from the fuselage. 6. The aeroplane according to claim 1, wherein a plurality of dampers are provided, andeach damper connects each hydrofoil to the fuselage. 7. The aeroplane according to claim 1, wherein each hydrofoil is at least partially retractable inside the fuselage. 8. The aeroplane according to claim 1, wherein at least one hydrofoil is provided with a platform configured as a footboard. 9. The aeroplane according to claim 1, further comprising: at least one additional hydrofoil, disposed in a median of the aeroplane with reference to a longitudinal axis of the aeroplane, and in the center of gravity of the aeroplane. 10. The aeroplane according to claim 1, wherein at least one of the trailing edge or the leading edge of each hydrofoil is formed by an aileron that is movable with respect to a remainder of the respective hydrofoil. 11. The aeroplane according to claim 1, wherein: each hydrofoil includes, as viewed in a transverse cross-section, a top surface having a concaveness that is directed upwards, in the normal position of the aeroplane, andeach hydrofoil includes, as viewed in a transverse cross-section, a bottom surface that is straight or has a concaveness directed upwards in an area of the leading edge of the respective hydrofoil such that the leading edge of the respective hydrofoil has an incisive shape.