Satellite Propulsion Research
Research Title : Optimization of Compressible Flow Expansion in Micro-Scale Thruster Nozzles for CubeSat Propulsion
The rapid development of small satellites, particularly CubeSats, has created an increasing demand for efficient and compact propulsion systems capable of providing precise thrust control. Micro-scale thrusters are a key technology enabling these missions, but understanding the complex flow behavior in such nozzles remains a significant challenge due to compressible flow, shock formation, and high expansion ratios within a confined geometry. In this research, we aim to perform a comprehensive computational study of a micro-thruster nozzle using ANSYS Fluent, focusing on flow expansion, pressure distribution, and Mach number evolution along the nozzle. The study will investigate key parameters such as inlet pressure and temperature, nozzle geometry (throat diameter, diverging angle), and propellant properties. We will simulate both steady and transient conditions to capture potential flow instabilities and shock interactions. CFD post-processing will include visualization of velocity and pressure contours, Mach number variation, temperature distribution, and expansion efficiency metrics. This analysis will help optimize micro-thruster performance for next-generation CubeSat missions and provide insights into high-speed compressible flow in micro-scale geometries.
