Patent ID: 6067853
Filing Date: 2000-05-30
Classification: B64C,F16F

Abstract:
A device for reducing the vibration in the cabin (2) of a rotary-wing aircraft, especially a helicopter (He), said device comprising:at least one sensor (C) arranged on the structure of the aircraft (He) and capable of measuring the values of at least one parameter that represents the vibration in said cabin (2);at least one controllable resonator (R), mounted directly in said cabin (2) and capable therein of generating a force which opposes said vibration; anda control unit (UC) capable of controlling said resonator (R) on the basis of the values measured by said sensor (C), so as to reduce and minimize said vibration,wherein said control unit (UC) performs the following operations in turn:it determines, from the values measured by said sensor (C), a level of vibration that represents said vibration in the cabin (2);it estimates the force which needs to be generated by said resonator (R) to reduce and minimize said level of vibration to an estimated minimum level of vibration;it controls said resonator (R) to make it generate said estimated force; and thenit iteratively performs the following operations in turn:it determines the actual level of vibration resulting from the last control applied to said resonator (R), from the corresponding values measured by said sensor (C);it calculates the difference between said actual level of vibration and the last estimated minimum level of vibration;it estimates, from said difference, a new force which needs to be generated by said resonator (R) to reduce and minimize said level of vibration to a new estimated minimum level of vibration; andit controls said resonator (R) to make it generate said new force.