Satellite design verification study based on thruster plume flow impingement effects using parallel DSMC method

A major objective of the present study is to introduce a usefulness of the parallel CFD application to a real design process of a space system and its importance. To verify the suitability of a proposed satellite design which is currently under development, the present study investigated the thruster plume impingement effects on satellite components and structures by predicting the disturbance force/torque and heat load. To analyze these plume effects quantitatively, a numerical simulation with the parallel Direct Simulation Monte Carlo (DSMC) method was performed. From the present results, the impingement effects of the released plumes from four monopropellant hydrazine thrusters on satellite components and structures were examined. And finally, the suitability of the initial satellite design configuration is discussed through the analysis data of the consequential dynamic and thermal influences.