Helicopter provided with a plurality of lift elements each provided with a respective tab for controlling the angles of incidence of its blades
AssigneeEurocopter
InventorAnne Brindejonc
Life of this patent
Estimating the term…
Abstract
The present invention relates to a helicopter provided with a main rotor (1) having at least two blades (10, 20), each blade (10, 20) being provided with attachment means (11, 21) attaching it to a hub (2) of the rotor (1). The helicopter is provided with one lift element (12, 22) per blade (10, 20), said lift element being provided with a tiltable tab (19, 29), each lift element (12, 22) being mechanically connected to a single blade (10, 20) to vary the pitch of said single blade (10, 20).
Claims24
A helicopter is provided with a main rotor (1) having at least two blades (10, 20), each blade (10, 20) being provided with attachment means (11, 21) attaching it to a hub (2) of the rotor (1), wherein the helicopter is provided with one lift element (12, 22) per blade (10, 20), said lift element being provided with a tiltable tab (19, 29), each lift element (12, 22) being mechanically connected 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 of a helicopter rotor having at least two blades, wherein a lift element (12, 22) provided with a tab (19, 29) that is connected solely to said blade (10, 20), and the lift generated by said lift element (12, 22) is adjusted by tilting the tab (19, 29) relative to the lift element so that the lift element (12, 22) performs a flapping movement to entrain the blade (10, 20) to which it is connected in pivoting about a first longitudinal axis (13, 23) for varying the pitch of said blade (10, 20).
Dependencies are inferred from the claim text.