The paper describes a project to design, assemble, and test propulsion, stage separation, and recovery systems for a high-powered model rocket. A first-principles model was used to evaluate the pressurization produced by the CO2 separation system. A prototype system was fabricated and tested. Circuit and coil design for the electromagnetic booster separation system was used to minimize the capacitance, reducing vehicle mass. Results of this analysis are presented. Two models were used to evaluate rocket motor performance, one to estimate the thrust and specific impulse, and the other the heat transfer rates in the motor. Descriptions of these models are presented. Finally, an autorotation recovery system was designed based on turbine, helicopter blade, and blade element momentum theories
