  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.
