It is an important embodiment of fighter's comprehensive ability to have high maneuverability. Therefore, it is necessary to study the coupling dynamic behavior of rotor system in typical maneuvering flight. Based on the finite element method, a 6-node rotor-bearing-disk system model with three kinds of maneuvering loads, nonlinear contact force of rolling bearing, eccentric unbalanced force of disk and gravity field is established in this paper, and the dynamic responses of the system under rolling, pitching and yawing maneuvering is analyzed in detail. The Newmark-β method is used to solve the system model. The system responses under different rotation speeds and two given rotation speeds are mainly analyzed. The system responses under three kinds of maneuvering loads are compared and analyzed. Finally, the 7-node stepped shaft system model is used to verify the universality of the analysis results in this paper. It is found that, under the same maneuvering load value, the possibility of rub-impact and frequency division components caused by different flight modes are different. The research in this paper can provide a cognitive basis for the mechanism of system rubbing fault under different maneuvers.

高机动性是战斗机综合能力的重要体现。因此，有必要研究旋翼系统在典型机动飞行中的耦合动力学行为。本文基于有限元方法，建立了具有滚动轴承非线性接触力、圆盘偏心不平衡力和重力场三种操纵载荷的6节点转子-轴承-盘系统模型，并得到了动力学响应详细分析了系统在横摇、纵摇和偏航机动下的运行情况。Newmark-β方法用于求解系统模型。主要分析了不同转速和两种给定转速下的系统响应。比较分析了三种操纵载荷下的系统响应。最后，采用7节点阶梯轴系模型验证本文分析结果的普遍性。研究发现，在相同的机动载荷值下，不同飞行模式产生摩擦和分频分量的可能性不同。本文的研究可为不同操作下系统摩擦故障的机理提供认知依据。