Objective: Design, analyze, and validate a reusable launch vehicle concept capable of return-to-launch-site recovery, with emphasis on propulsion system selection, thrust margin optimization, and ascent/descent performance. Propulsion-Focused Engineering Work: Served as Propulsion Lead, responsible for motor selection, thrust matching, and propulsion performance validation Performed thrust-to-weight, thrust margin, and stability calculations to ensure safe ascent and controllable recovery Conducted detailed thrust curve and trajectory analyses in OpenRocket to evaluate ascent performance and apogee targeting Selected the Aerotech I1600R motor, achieving an approximate 64% thrust-to-weight increase relative to baseline configurations Simulated over a dozen flight conditions to assess sensitivity to motor performance, mass properties, and aerodynamic stability Recovery & Integration (Propulsion-Driven): Designed a fully integrated recovery system sized and tuned around propulsion-induced flight loads Coordinated propulsion performance with recovery timing, GPS deployment logic, and control authority Compared predicted propulsion behavior against flight data to validate analytical assumptions