Ignition start-up course calculation and ignition charge mass selection of impulse micro-thruster
ZHOU Hai-qing, ZHANG ping∥School of Mechano-Electronics Engineering, Beijing Institute of Technology, Beijing100081, China.
Ignition start-up model of impulse micro-thruster is established, considering two phase flow and impact heat transfer of particle on the surface of propellant. Based on numerical calculation results, selection range of ignition charge mass with different particle content is given. It is suitable for ignition charge whose particle content is less than 50%. Because excessive particle content can cause strong heat impact failure on the grain surface, ignition charge whose particle content is more than 50% isn't suitable for micro-rocket motor.