Patent ID: 6152692
Filing Date: 2000-11-28
Classification: B64C,Y02T

Abstract:
A rotary wing aircraft rotor blade, comprising: a span, a blade trailing edge. at least one trailing edge swiveling air flow control flap, said control flap being swivelled on the blade, in a blade part near the blade trailing edge, around at least one axis directed substantially along the span of the blade and of the control flap, the swivelling of the air flow control flap being controlled by an actuator gear, mounted on the blade, and including at least one actuator wherein said actuator gear further includes means of separation of a frequency control and an amplitude control of the swivelling of the air flow control flap and two eccentrics in series, the second around the first, and the first eccentric of which is rotated by a first rotating motor around the axis of said first motor, at a rotational speed corresponding to a base frequency of the swivelling of the air flow control flap, and the second eccentric of which is centered on the axis of said first eccentric and controlled in angular position relative to said first eccentric and around the axis of said first eccentric, for the amplitude control of the swivelling of said air flow control flap, by at least one second rotating motor, rotating integrally with said first eccentric around the axis of said first motor, a ring being mounted rotating freely on said second eccentric, and connected to said air flow control flap by a transmission transforming the movements of said ring by said eccentrics in swivelling of the air flow control flap with an amplitude which is a function of the eccentricities and of the relative position of said two eccentrics and which is controlled by said second motor.