초록 ▼

Method and device for the reduction of the oscillations of a divergent nature induced in the fuselage (2) of a helicopter (1) by its rotary wings (3) when they are turning. According to the invention, the oscillations are detected (at 17, 18) and they are converted (at 19, 20) into electrical signal

Method and device for the reduction of the oscillations of a divergent nature induced in the fuselage (2) of a helicopter (1) by its rotary wings (3) when they are turning. According to the invention, the oscillations are detected (at 17, 18) and they are converted (at 19, 20) into electrical signals, which are used (at 13) in order to produce pitch variations of the blades (4) of the rotary wings (3), in such a way that a rotating torque vector opposing said oscillations results.

대표청구항 ▼

A method for the reduction of the oscillations of a divergent nature induced in the fuselage (2) of a helicopter (1) by its rotary wings (3) when they are turning, said helicopter resting on the ground by means of its landing gear (5), the method comprising: detecting (at 17, 18) the roll movements

A method for the reduction of the oscillations of a divergent nature induced in the fuselage (2) of a helicopter (1) by its rotary wings (3) when they are turning, said helicopter resting on the ground by means of its landing gear (5), the method comprising: detecting (at 17, 18) the roll movements of the fuselage of said helicopter on the ground, and generating a detection signal which is representative of said roll movements on the ground; forming (at 20), on board said helicopter, on the basis of said detection signal which is representative of the roll movements on the ground, a signal for roll control on the ground whose frequency is identical to that of said detection signal which is representative of the roll movements on the ground; applying said signal for roll control on the ground to at least one first actuator (13, 12, 21) arranged in the kinematic control chain for the cyclic pitch of the blades (4) of said rotary wings (3); and causing the action of said first actuator on said cyclic pitch, due to the phase and the amplitude of said signal for roll control on the ground, to result in the appearance of a set of forces and moments generated by the rotary wings and opposing, in roll and on the ground, the effect of said oscillations of a divergent nature on the fuselage. A device for the reduction of the oscillations of a divergent nature induced in the fuselage (2) of a helicopter (1) by its rotary wings (3) when they are turning, said helicopter resting on the ground by means of its landing gear (5), which comprises: means (17, 18) for detecting the roll movements, on the ground, of the fuselage of said helicopter and for generating a detection signal which is representative of said roll movements on the ground; means (19, 20) arranged on board said helicopter and generating, on the basis of said roll movements detection signals, a signal for roll control on the ground whose frequency is identical to that of said roll movements detection signal; and at least one first actuator (12, 13, 21) to which said roll control signal is applied and which is arranged in the kinematic control chain for the cyclic pitch of the blades of the rotary wings; the phase and the amplitude of said roll control signal being such that the action of said first actuator on said cyclic pitch results in the appearance of a set of forces and moments generated by the rotary wings and opposing, in roll and on the ground, the effect of said oscillations of a divergent nature on the fuselage.