Dynamics of Aero-Engine Dual-Rotor Systems under Multi-Flight Attitudes and Simultaneous Rub-Impact Faults

Abstract

High-maneuverability combat aircraft exert extreme loads on aero-engines, potentially triggering destructive rotor-stator rub-impacts and thereby pose a severe threat to flight safety. This study establishes a four-degree-of-freedom (4-DOF) rotor-bearing-disk model for a dual-disk system, specifically tailored to simulate the coupling effects of simultaneous rub-impact faults under diverse flight attitudes and maneuver loads. For benchmarking purposes, a corresponding model free of rub-impact is accordingly constructed. The Newmark-β method is employed to derive solutions for both models. To evaluate how maneuver loads influence the dynamic characteristics of the system, a parametric investigation is conducted to assess the effects of dual-disk rub-impact across three key flight attitudes, namely, rolling, pitching, and yawing. This research offers a critical theoretical basis for enhancing vibration control and conducting failure analysis in fighter engine design, ultimately contributing to the development of safer and more reliable rotor systems.