Aiming at the special structure and working characteristics of missile turbine engine rotor system,the equation of maneuvering flight rotor system is derived from the perspective of relative motion,and the additional loads brought by different maneuvering flights are analyzed.Finite element method is used to calculate and analyze the effects of rolling maneuver and conventional maneuver on the dynamic characteristics of the rotor system.The results indicate that under the current load size specified in the national military standard,rolling maneuver has little effect on the dynamic characteristics of the rotor,while the conventional maneuver will cause the disc center shifting.The amplitude of deviation is equivalent to the steady-state re-sponse of the rotor at the working speed,which can increase the possibility of rotor collision and wear.
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