Aero-engine rotor systems are inevitably subjected to a series of additional maneuvering loads such as centrifugal loads, gyroscopic moments, etc. during maneuvering flight. These loads can affect the dynamic characteristics of the rotor system, which in turn pose a potential threat to flight safety. The research status of the whole aircraft drop test, simulation analysis and test of dynamic characteristics of rotor system under maneuvering flight conditions, modeling analysis and test of vibration characteristics of rotor system under base excitation load were summarized. The limitations of current research in accurate simulation of real flight conditions, coupling effects of multiple physical fields such as thermal solid gas, research and development of equipment and test technology for multi direction and multi degree of freedom maneuvering load loading were pointed out. The future research should be focused on fine analysis of transient response of rotor system under maneuvering flight conditions, overall modeling and in-depth analysis of overall dynamic characteristics, innovative development of multiple field coupled analysis methods such as thermal solid gas, and systematic construction of test techniques for dynamic characteristics of rotor system under actual service environment, with a view to providing a reference basis for structural safety design of aeroengine rotor system under maneuvering flight conditions.