초록 ▼

The invention relates to a tiltrotor helicopter comprising a fuselage (1), a wing arrangement (2) and at least one power plant (5), and including two contrarotating, cyclically controllable rotors (7, 8) which are spaced from one another in the longitudinal direction of the fuselage and arranged sub

The invention relates to a tiltrotor helicopter comprising a fuselage (1), a wing arrangement (2) and at least one power plant (5), and including two contrarotating, cyclically controllable rotors (7, 8) which are spaced from one another in the longitudinal direction of the fuselage and arranged substantially on a longitudinal axis of the fuselage (1) as well as being respectively tiltable out of a first tilted position for helicopter flight into a second tilted position for airplane flight, the first rotor (7) being arranged at the front end of the fuselage (1) and substantially above the same and the second rotor (8) being arranged at the rear end of the fuselage (1) and substantially beneath the same, and the first rotor (7) being tiltable about a tilting axis (17) extending substantially perpendicularly to the longitudinal axis of the fuselage (1) out of the first tilted position downwardly and in front of the fuselage (1) into the second tilting position and the second rotor (8) being tiltable about a tilting axis (18) extending substantially perpendicularly to the longitudinal axis of the fuselage (1) out of the first tilted position upwardly and behind the fuselage (1) into the second tilted position.

대표청구항 ▼

[ I claim:] [1.] A tiltrotor helicopter comprising:a fuselage,a wing arrangement andat least one power plant, andfirst and second contrarotating, cyclically controllable rotors which are spaced from one another in the longitudinal direction of the fuselage and substantially arranged on a longitudina

[ I claim:] [1.] A tiltrotor helicopter comprising:a fuselage,a wing arrangement andat least one power plant, andfirst and second contrarotating, cyclically controllable rotors which are spaced from one another in the longitudinal direction of the fuselage and substantially arranged on a longitudinal axis of the fuselage as well as being respectively tiltable out of a first tilted position for helicopter flight into a second tilted position for airplane flight, whereinsaid first rotor is disposed at and substantially above the forward end of the fuselage and the second rotor is disposed at and essentially beneath the rear end of the fuselage,said first rotor is tiltable about a first tilting axis extending substantially perpendicularly to the longitudinal axis of the fuselage out of the first tilted position downwardly and in front of the fuselage into the second tilted position, andthe second rotor is tiltable about a second tilting axis extending substantially perpendicularly to the longitudinal axis of the fuselage out of the first tilted position upwardly and behind the fuselage into the second tilted position.