Design And Experimentation Of Micro Impulse Jet Engine And Its Control Circuit

Accurate strike has been a main character of modern warfare. Endue conventional ammunition with accurately strike ability is the trend of ammunition development, and trajectory correction is an effective means. In this dissertation, we focus the work on the execute mechanism of the trajectory correction rocket grenade, which is one of the key technology. A new type of trajectory correction execute mechanism - micro impulse jet engine - was put forward that is used in the infantry rocket grenade. A control circuit was designed for calculating and controlling the trajectory of the rocket grenade according to the working characteristics of the micro impulse jet engine and semi-active laser guider.The working principle of the correcting micro impulse jet engine was expatiated, and a prototype was worked out. The result of thrust test showed that the thrust value reached 1.425N while the compressed air pressure of engine was 0.65MPa. AVR single chip processor was applied in the control circuits which integrates the functions of target signal processing from the guider, 6 jet engines controlling, trajectory calculating and parameter outputting by serial port. Test showed that it could carry out the correcting control function according to the trajectory information from the guider head, and the trajectory correction execute mechanism is feasible for infantry rocket grenade.