A helicopter, having a vibration control system, and comprising: a fuselage; a cabin; a cockpit; a main rotor system; and a pylon mount connecting the main rotor system to the fuselage; the vibration control system comprising: a dedicated actuator, connected with the cockpit and/or the cabin of the fuselage, the dedicated actuator comprising a mass and an inertial force generator for moving the mass relative to the fuselage to thereby generate a linear or rotational force relative to the fuselage; at least one of an integrated actuator and an intermediate actuator, both controllably connected with a first source of vibration, the first source of vibration being the rotor system; a plurality of sensors configured to sense vibration and audible noise associated with at least one of the rotor system, the cabin and the cockpit; a tachometer configured to provide a rotational frequency of the rotor system; a controller configured to receive information from the sensors and the tachometer and, to provide unified control to the dedicated actuator, the integrated actuator, and the intermediate actuator based on the information; and wherein the integrated actuator is configured to affect operation of the rotor system based on at least one of the rotational frequency of the rotor system and the vibration from the rotor system, and; wherein the intermediate actuator is associated with the pylon mount to affect the vibration in a load path between the fuselage and the rotor system; wherein the controller is further configured to send command signals to the dedicated actuator, the command signals comprising drive signals for the inertial force generator to move the mass relative to the fuselage to reduce vibration and audible noise associated with the cockpit and/or the cabin of the fuselage. a fuselage; a cabin; a cockpit; a main rotor system; and a pylon mount connecting the main rotor system to the fuselage; the vibration control system comprising: a dedicated actuator, connected with the cockpit and/or the cabin of the fuselage, the dedicated actuator comprising a mass and an inertial force generator for moving the mass relative to the fuselage to thereby generate a linear or rotational force relative to the fuselage; at least one of an integrated actuator and an intermediate actuator, both controllably connected with a first source of vibration, the first source of vibration being the rotor system; a plurality of sensors configured to sense vibration and audible noise associated with at least one of the rotor system, the cabin and the cockpit; a tachometer configured to provide a rotational frequency of the rotor system; a controller configured to receive information from the sensors and the tachometer and, to provide unified control to the dedicated actuator, the integrated actuator, and the intermediate actuator based on the information; and wherein the integrated actuator is configured to affect operation of the rotor system based on at least one of the rotational frequency of the rotor system and the vibration from the rotor system, and; wherein the intermediate actuator is associated with the pylon mount to affect the vibration in a load path between the fuselage and the rotor system; a dedicated actuator, connected with the cockpit and/or the cabin of the fuselage, the dedicated actuator comprising a mass and an inertial force generator for moving the mass relative to the fuselage to thereby generate a linear or rotational force relative to the fuselage; at least one of an integrated actuator and an intermediate actuator, both controllably connected with a first source of vibration, the first source of vibration being the rotor system; a plurality of sensors configured to sense vibration and audible noise associated with at least one of the rotor system, the cabin and the cockpit; a tachometer configured to provide a rotational frequency of the rotor system; a controller configured to receive information from the sensors and the tachometer and, to provide unified control to the dedicated actuator, the integrated actuator, and the intermediate actuator based on the information; and wherein the integrated actuator is configured to affect operation of the rotor system based on at least one of the rotational frequency of the rotor system and the vibration from the rotor system, and; wherein the intermediate actuator is associated with the pylon mount to affect the vibration in a load path between the fuselage and the rotor system; wherein the controller is further configured to send command signals to the dedicated actuator, the command signals comprising drive signals for the inertial force generator to move the mass relative to the fuselage to reduce vibration and audible noise associated with the cockpit and/or the cabin of the fuselage.