通过多体动力学方法建立了倾转旋翼机动力学分析模型。结合动力入流,研究了直升机模式下倾转旋翼机非线性非定常气弹耦合动力学特性。集成了非定常动态入流方程与倾转过渡状态的多体动力学方程,建立了倾转旋翼机时域非定常气弹耦合分析模型。以半展长弹性机翼全铰接式倾转旋翼机模型为例,在直升机模式下分析了桨叶摆振刚度及飞行速度对倾转旋翼机气弹稳定性的影响。数值计算表明建立的多体动力学模型能够快速分析直升机模式下倾转旋翼机复杂的旋翼/机翼气弹耦合动力学特性。 The dynamic analysis model of tilt rotor is established by multi-body dynamics method. Combined with in-flow, the dynamics of nonlinear unsteady aeroelastic coupling in a tilting rotorcraft under helicopter mode is studied. Integrated multi-body dynamics equations of unsteady inflow equation and tilting transition state, a time-domain unsteady Aeroelastic-B coupled model of tiltrotor rotorcraft was established. Taking the half-span long flexible wing all-articulated tilting rotor model as an example, the influence of the blade’s roll stiffness and the flying velocity on the aero-rotor stability of the tilting rotor is analyzed in the helicopter mode. The numerical calculation shows that the established multi-body dynamics model can quickly analyze the complex rotor / wing aeroelastic coupling dynamics under the helicopter mode.