Helicopter are susceptible to high vibrations because of unsteady aerodynamic effected on the disc and rotor-fuselage interavtive,High levels of vibration for long time limits the helicopter performance,reduces structural life of dynamic systems. The trim model of rigid general rotor is built in this paper,and coupled trim analysis are made for swashplateless based and optimization design. Then we make forced vibration for the fuselage of UH-60. The result shows that blade collective pitch θ0 and cyclic pitch θ1c and θ1s increasing with the advance ratio. Disc inflow slow down firstly and then increased suddenly.The hub load acting on the fuselage move up with the advance ratio.The optimization swashplateless rotor may reduce the vibration load acting on the hub slowly.