초록 ▼

A fixed-wing aircraft with tandem lifting surfaces has monoplane main wings secured in an intermediate area of the fuselage and a horizontal tail surface with at least one stabilizer plane mounted at the tail of the fuselage. A third supporting surface on the fuselage is in tandem arrangement with t

A fixed-wing aircraft with tandem lifting surfaces has monoplane main wings secured in an intermediate area of the fuselage and a horizontal tail surface with at least one stabilizer plane mounted at the tail of the fuselage. A third supporting surface on the fuselage is in tandem arrangement with the other supporting surfaces. The third supporting surface is a canard surface positioned ahead of the center of gravity of the aircraft.

대표청구항 ▼

A fixed-wing large transport aircraft having a fuselage with a nose and a tail spaced therefrom, said fuselage having a center of gravity, said aircraft comprising tandem supporting surfaces including monoplane main wings secured to the fuselage in an intermediate area thereof, each of the main wing

A fixed-wing large transport aircraft having a fuselage with a nose and a tail spaced therefrom, said fuselage having a center of gravity, said aircraft comprising tandem supporting surfaces including monoplane main wings secured to the fuselage in an intermediate area thereof, each of the main wings having at least one lift-increasing flap and at least one leading edge slat; a horizontal tail surface with at least one stabilizer plane at the tail of said fuselage, said stabilizer plane having a variable angular position which is selectively adjustable through controlled adjustment; a third supporting surface mounted on said fuselage in tandem relation with the other supporting surfaces and including a canard airfoil affixed to said fuselage at the nose thereof in front of the center of gravity thereof, said canard airfoil extending from opposite sides of said fuselage and consisting of a canard plane and a movable trailing edge control surface; means for monitoring the instant position of said stabilizer plane of said horizontal tail surface; a control system for measuring parameters representative of the drag of the aircraft such as the fuel flow and thrust of said aircraft; and wherein the trailing edge control surface of said canard airfoil is controllable in accordance with the position of one of said lift-increasing flap and said leading edge slat thereby producing a positive aerodynamic balance at said horizontal tail surface for the given flight conditions of the aircraft, said control system is adapted to deflect said canard airfoil in accordance with the measured parameters and the horizontal tail surface correspondingly so as to allow the aircraft to fly always with an optimal incidence angle for all three lifting surfaces.