CFD-Driven Optimization of Dual-Throat Micro-Nozzle for Enhanced Thrust in Cold Gas Propulsion for Microsatellites

Abstract

Micro spacecraft have garnered increasing favor for their adaptability in space missions. Cold gas propellant-based (CGP) micro propulsion systems assume a pivotal role in enabling maneuvering, monitoring, and precise attitude control in micro/nanosatellites, offering attributes of simplicity, non-toxicity, and minimal leakage compared to alternative propulsion methods. The convergent-divergent micro-nozzle, an integral component of micro thrusters, is instrumental in thrust generation. This research conducts a sensitivity analysis of the micro-nozzle to discern influential geometric variables, employing response surface optimization techniques through ANSYS FLUENT. Results indicate a noteworthy thrust enhancement, reaching 113.1 mN in the optimized design. Additionally, a novel curved throat concept is introduced, yielding a 25 percent thrust increase and culminating in a final design achieving 141 mN. Further exploration involves a dual-throat micro-nozzle, integrating response surface optimization and a curved throat design, resulting in an impressive thrust level of 261 mN, surpassing prior designs without added complexity. This study advances micro spacecraft propulsion by addressing challenges and introducing innovative approaches, emphasizing the pioneering nature of this investigation within the realm of micro propulsion systems.