Design Of Swing Nozzle Actuator And Thrust Vector Control System

Solid rocket thrust vector control technology can greatly improve the aircraft maneuverability and penetration capabilities,and also can enable the aircraft to perform more complex tasks and combat capabilities.Thrust vector control mainly achieve swing angle of swing nozzle by adjusting the linear motion of two linear actuators.In order to improve the maneuverability of the aircraft,thrust vector adjustment requires that the linear actuator has a very high speed response,and the peak load reaches over 2000 N.Therefore,the linear actuators require high integration,high response,high thrust,high precision and anti-interference ability.Thrust vector control based on electric servo system becomes a feasible option,as the progress of electric servo technology.However,in the traditional electric servo system,screw and brushless DC motor are connected by transmission mechanism such as gears,it often cannot meet the requirements under the constraints of many volumetric structures and high loads.This paper presents a highly integrated and high power density electromechanical integrated actuator,designs and manufactures the mechanical body.Thrust vector control system experimental facility is built,and a dual-channel brushless DC motor controller is designed.First of all,an integrated actuator is designed based on the design parameters of the actuator.Then structure strength is checked and the dynamics simulation for the system is carried out.We design simulated load environment of the integrated actuator,and built the thrust vector control test bench.Secondly,a simulation model of three closed-loop PID control system of brushless DC motor is built based on Matlab / Simulink.The servo motion process of TVC is analyzed.The algorithm relationship between swing angle of swing nozzle and motion displacement of two integrated actuators is studied.Thirdly,a two-channel brushless DC motor servo controller is designed.The hardware system includes dual-channel inverter,hardware drain,linear Hall decoder,feedback signal acquisition,processing module and other circuits.DSP program uses Model Based Design method based on the Matlab/ Simulink,three closed-loop PID control algorithm program is designed.FPGA programs include linear Hall decoding and dual-channel brushless DC motor PWM driver.Finally,software and system performance test of thrust vector control simulation bench are carried out.Tune PID parameters,complete the point-topoint movement of the actuator and position follow the movement,lay the foundation for subsequent research.