Current Development Status of the Polaris-1 Small Liquid Rocket

This paper outlines the design and development of the 450 N Ethanol/H 2 O 2 liquid rocket engine, "Polaris-1."It provides a preliminary approach to liquid rocket design.The combustion chamber was designed using CEA analysis and method to minimize wall surface area.A bell nozzle with a third-order polynomial contour was designed.To improve performance, a bi-swirling injector and film cooling technique were applied.The torch ignition method was adopted, and a 3-DoF flight simulation predicted a maximum altitude of 225 meters.Future work will validate engine performance through 6-DoF simulations and combustion tests, with redesigns made if necessary based on the results. 450 N Ethanol/H 2 O 2 "Polaris-1" , . CEA , 3 ., . , 3 225 m .