Helicopter is 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, structural life of dynamic systems is reduced. The trim model of rigid general rotor is built, and coupled trim analysis are made for swashplateless based and optimization design. Then forced vibration for the fuselage of UH-60 is made. The result shows that blade collective pitchθ 0 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.%桨盘上的非定常气动力、旋翼-机身之间的相互干扰导致直升机在飞行的过程中遭受到过多的振动.长时间高水平的振动会降低直升机的整体性能,减少直升机动力系统的结构寿命.建立了刚性常规旋翼的配平模型,并对无自动倾斜器旋翼的基准设计和优化设计方案进行了耦合配平仿真分析.在此基础之上,以黑鹰UH-60的机身为研究对象,对其进行了强迫振动响应分析.分析结果表明,随着前进比的增加,桨叶总距和周期变距的绝对值增加；桨盘入流先减小后增加；作用在直升机桨毂上的载荷幅值有所增大；经过优化设计后的无自动倾斜器旋翼在一定程度上降低了桨毂载荷.
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