An aircraft (1) comprising a fuselage (2), a rotary wing (10) having two contrarotating main rotors (12) arranged in tandem above the fuselage (2), at least one propulsion member (20), and a power plant (30). Each propulsion member (20) is carried by a rear portion (3) of the fuselage. The aircraft
An aircraft (1) comprising a fuselage (2), a rotary wing (10) having two contrarotating main rotors (12) arranged in tandem above the fuselage (2), at least one propulsion member (20), and a power plant (30). Each propulsion member (20) is carried by a rear portion (3) of the fuselage. The aircraft (1) includes an interconnection system (40) providing a permanent connection between the power plant (30) and the rotary wing (10), except in the event of a failure or during training, the aircraft (1) having differential control means (50) for controlling the cyclic pitch of the blades of the main rotors (12) to control the aircraft (1) in yaw, and inhibition means (60) for inhibiting each propulsion member (20).
대표청구항▼
1. A long-range and high-speed aircraft comprising: a fuselage extending longitudinally in an anteroposterior plane (P1) from a rear portion to a front portion, passing via a central portion, the center of gravity (Cg) of the aircraft being situated in said central portion;a rotary wing having two c
1. A long-range and high-speed aircraft comprising: a fuselage extending longitudinally in an anteroposterior plane (P1) from a rear portion to a front portion, passing via a central portion, the center of gravity (Cg) of the aircraft being situated in said central portion;a rotary wing having two contrarotating main rotors arranged in tandem above said fuselage, the two contrarotating main rotors including a front main rotor being carried by said front portion and a rear main rotor being carried by said rear portion;at least one propulsion member; anda power plant for delivering power to said main rotors and to each propulsion member, the power plant comprising a first engine and a second engine, each propulsion member being associated with at least one of the first engine and the second engine;wherein each propulsion member is carried by said rear portion and said aircraft includes an interconnection system providing a permanent connection between said power plant and said rotary wing, except in the event of a failure or during training, the interconnection system including a mechanical assembly having a front main gearbox driving a mast of the front main rotor, a rear main gearbox driving a mast of the rear main rotor, and at least one shaft connecting the front gearbox to the rear gearbox, the interconnection system further including a first drive train connecting the first engine to the mechanical assembly and a second drive train connecting the second engine to the mechanical assembly, said aircraft having differential control means for controlling the cyclic pitch of the blades of said main rotors to control the aircraft in yaw, each propulsion member having an associated clutch controlled by a controller to enable the propulsion member to be disconnected from the power plant. 2. The aircraft according to claim 1, wherein the first engine and the propulsion member cooperatively define an engine-propulsion member including an engine and a propulsion member. 3. The aircraft according to claim 1, wherein the at least one propulsion member includes at least two propulsion members arranged transversely on either side of said fuselage. 4. The aircraft according to claim 1, wherein the at least one propulsion member includes a propulsion member arranged in an anteroposterior plane of symmetry (P1) of the aircraft. 5. The aircraft according to claim 1, wherein the at least one propulsion member is a propeller member. 6. The aircraft according to claim 1, including a processor configured to regulate a speed of rotation (Ω) of said main rotors in order to maintain the speed of rotation (Ω) of each main rotor equal to a first speed of rotation (Ω1) up to a first on-path air speed (V1) of said aircraft, and then to reduce said speed of rotation (Ω) progressively in application of a linear relationship as a function of the on-path air speed of said aircraft. 7. The aircraft according to claim 1, wherein said rear main rotor rotates in a first lift plane (P2) above a second lift plane (P3) in which the front main rotor rotates. 8. The aircraft according to claim 1, wherein said central portion includes a fixed wing. 9. The aircraft according to claim 8, wherein said fixed wing includes aircraft control means. 10. An aircraft comprising: a fuselage having a front end and a rear end;a power plant including a first engine and a second engine;first and second contrarotating main rotors disposed above the fuselage in a tandem configuration;a first mechanical linkage continuously drivingly coupling the power plant to the first and second main rotors, the first mechanical linkage including a first drive train drivingly coupling the first engine to the first and second main rotors and a second drive train drivingly coupling the second engine to the first and second main rotors;at least one propulsion member disposed proximate the rear end;a second mechanical linkage selectively drivingly coupling the power plant to the at least one propulsion member, wherein in at least one operating condition the second mechanical linkage drivingly couples the power plant to the at least one propulsion member and the first mechanical linkage drivingly couples the power plant to the first and second main rotors; andan inhibitor configured to selectively inhibit the propulsion member. 11. The aircraft of claim 10, wherein the inhibitor comprises a clutch cooperating with the second mechanical linkage to selectively decouple the at least one propulsion member. 12. The aircraft of claim 10, wherein the fuselage has opposing first and second sides and the at least one propulsion member includes a first propeller disposed on the first side and a second propeller disposed on the second side. 13. The aircraft of claim 10, wherein the aircraft defines a plane of symmetry and the at least one propulsion member includes a propeller disposed with an axis of rotation along the plane of symmetry. 14. The aircraft of claim 10, wherein the first rotor has a first mast, the second rotor has a second mast, and the first mechanical linkage comprises a first gear box configured to drive the first mast, a second gearbox configured to drive the second mast, a shaft coupling the first gearbox and the second gearbox, and wherein the first drive train couples the first engine to the first gearbox and the second drive train couples the second engine to the second gearbox.
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이 특허에 인용된 특허 (6)
Bass, Steven M.; Mitchell, Clark A., Dual-flight mode tandem rotor wing.
Vondrell, Randy M.; Polakowski, Matthew Ryan; Murrow, Kurt David; Crabtree, Glenn; Zatorski, Darek Tomasz, Tiltrotor propulsion system for an aircraft.
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