Helicopter provided with a plurality of lift elements for controlling the angles of incidence of its blades
AssigneeEurocopter
InventorPierre BERTHIE
Life of this patent
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Abstract
A helicopter is fitted with a main rotor (1) having at least two blades (10, 20), each blade (10, 20) being provided with attachment elements (11, 21) for attaching it to a hub (2) of the rotor (1). The rotor is also fitted with one lift element (12, 22) per blade (10, 20), each lift element (12, 22) being mechanically linked to a single blade (10, 20) to vary the pitch of the single blade (10, 20) with which the lift element (12, 22) is linked.
Claims22
A helicopter fitted with a main rotor (1) having at least two blades (10, 20) each blade (10, 20) being provided with attachment means (11, 21) to a hub (2) of the rotor (1), wherein the helicopter is provided with one lift element (12, 22) per blade (10, 20), each lift element (12, 22) being mechanically linked to a single blade (10, 20) to vary the pitch of said single blade (10, 20).
A method of varying the pitch of a blade (10, 20) of a helicopter rotor having at least two blades, wherein said blade (10, 20) has a lift element (12, 22) that is linked solely thereto, and the lift generated by said lift element (12, 22) is adjusted so that the lift element (12, 22) flaps to cause the blade (10, 20) with which it is linked to turn about a first longitudinal axis (13, 23) for varying the pitch of said blade (10, 20), the lift of said lift element (12, 22) being adjusted by modifying the pitch of the lift element (12, 22) and thus by causing said lift element (12, 22) to turn about a second longitudinal axis (17, 27) for varying the pitch of said lift element (12, 22).
Dependencies are inferred from the claim text.