Modeling And Experiment Of Intraction Of Ceramic Wall And Plasma With Heat Transferring In Dischange Channel

Stationary Plasma Thruster (SPT), the basic type of Hall plasma thrusters, is an advanced electric propulsion technique which is used in the on-orbit satellite propulsion. With its excellent performance, the thruster can substitute the traditional chemical rocket that needs much more fuel as its propellant.The heat energy SPT produce when it is running is the main energy loss of SPT.So the thermal analysis is the very important. In this thesis, heat source of the discharge channel is found,the amount of heat flux is also calculated.The distribution of temperature and stress can be get through simulation,which need to be confirmed with experiment.Thermal design of SPT will be made based on the result above. The main embody work in this thesis as follows:Analyse the process of energy transformation in order to know the main cause of the loss of energy. Through the analysis of the interaction of plasma and the ceramic wall,we can get the distribution of heat flux.Set up the model of SPT using ANSYS,and we can get the distribution of temperature and stress in different situation.Because the flux in the discharge channel is hard to be measured,so that we may use APDL to amend the program in order to get the heat flux.Using infrared imaging and surface temperature probe ,we can get the temperature of some node and its process of rise of temperature.This can help validating the result of experiment and finding the difference between model and the real one.We also measure the temperature of ceramic wall in different magnetic field.Find out the thermal limit that the material of SPT is able to endure.We make thermal design with thermal control techniques which are already being used in the spaceflight field.In this thesis ,the feasibility and effect of thermal design has been validated.