Rotor Vibration is of utmost problem in helicopter industry. Reducing vibration levels of the helicopter have many benefits such as reducing maintenance cost by increasing the fatigue life of critical structural components, reducing crew fatigue, improving crew awareness and reliability, and improving community acceptance by increasing passenger comfort. In this thesis a modified Myklestad method for rotating beams has been developed and represent the helicopter blade by lamped mass system which includes effects of rotary inertia, blade geometric pitch and inertial and elastic coupling among the five degrees of freedom at each mass station (radial motion is not included). Shear deformation and aerodynamic effect are not considered. Discrete spanwise variation of blade properties and various hub configurations are modeled in the program. In order to be able to determine blade lift, drag, flapping moment and ultimately, rotor vibratory loads, it is necessary, as with axial flight, to determine the induced velocity. In the aerodynamic chapter aerodynamics are modeled with an approximation method named classical actuator disc theory, mangler squire method used to model induced velocity within rotor disk classical theory. The dynamics of the blades and rotor are equally susceptible to simple approaches based on straight forward ideas of induced velocity, aerofoil characteristics and blade modeling. At last vibration solution coupled with aerodynamic loads for modeling blade vibrations and then a control method is proposed to reduce vibrations in helicopters using individual blade control on the main rotor blades. The problem of stabilization of hub vibratory loads in a front fight subject to external disturbances is addressed. Necessary and sufficient conditions are presented for static output-feedback control of linear time invariant systems using the H-Infinity approach. The novelty of the method is that each blade is controlled independently, taking into account possible uncertainty such as helicopter velocity, etc and develop the equations of motion for the structural and aerodynamic forces and moments of a rotor blade using five degrees of freedom. This is different from previous control approaches that assumed blades were identical and generated a single control input which is applied with adequate phase shift to each blade. Keywords: IBC, Robust control, Helicopter vibration reduction,Rotating blade.