Design of retractile fins actuator based on hollow piezoelectric motor

Abstract

In the initial stage of the exterior ballistic, the centroid of the simple guided rocket will change with the fuel consumption of rocket engine, so the flight stability in the initial stage and the manoeuvrability in the whole trajectory correction process must to be comprehensively considered. For this challenge, in this paper, a specific actuator and aerodynamic configuration based on the integration of retractile fins structure and rotor of hollow piezoelectric motor is proposed. And the research on the structure of the actuator and the scheme of the retractile mechanism are carried out. The wind-induced rolling moment of the actuator under different flight conditions (angle of attack, Mach number) is simulated and analyzed by numerical computation method, and the load characteristics of the piezoelectric motor of the actuator is analyzed and tested. The results show that when the flight speed is 0.8 Ma, 1.0 Ma, the angle of attack is 0∼6°, the maximum induced rolling moment of the actuator is 0.30 N.m, and the load speed of the piezoelectric motor is 25r/min when the excitation voltage is 450V and the excitation frequency is 40.2kHz, which can meet the requirements of the projectile flying environment.