| 摘要 |
Apparatus is disclosed to compensate for forces that are applied to the aircraft pylon from rotor blade vibratory disturbances in a rotary wing aircraft. The compensation is such that the effect of the vibratory disturbances on the pilot's cabin, or at any other desired area in the fuselage, is minimized. The apparatus includes a signal generating device that generates a signal having the same frequency as the frequency of the forces resulting from the rotor blade vibratory disturbances. The signal is employed to control the frequency of compensating forces or motions that are applied by the apparatus of this invention between the pylon and the fuselage. Control over the amplitude and phase of the compensating forces or motions applied between the pylon and the fuselage by the apparatus of this invention will establish an amplitude and phase for the net forces and moments on the fuselage of such a fashion that a desired portion of the fuselage, such as the pilot's cabin, can be effectively insulated from the effects of the rotor blade vibratory disturbances.
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