Analysis and Experimental Research on Test Method of Initial Guidance Thrust

Abstract

With the gradual development of aerospace industry, the demand for missile performance is also growing. The steering gear, as one of the main implementing agencies of the missile guidance and control system, can adjust the actual thrust size through the closed-loop control system during missile guidance the deflection angle of the rudder surface, in order to change the missile's flight speed and flight attitude. The missile during the flight attitude correction and speed adjustment are through the electric servo output power to change the size of the output to complete. In this paper, the unsteady turbulent analysis theory is used to analyze the thrust test mechanism of jet. Through the simulation of the flow field, the influence of bearing wall position on the impact jet backflow zone location is studied, and the position of the bearing wall whose pressure value is the closest to the true value is determined. In addition, a simplified test system of jet thrust test was designed. The relationship between wall position and pressure was verified through experiments, which verified the accuracy of simulation results.