Abstract
Analysis is centered around stability and ideal optimization for the control of a low-range rocket as it experiences two stages of acceleration. The implementation of experimental and computational testing is used to determine stability margins and pitch correction for multiple rocket iterations. Computational fluid dynamic (CFD) simulations are conducted using Ansys Fluent along with wind tunnel testing and OpenRocket simulations to determine aerodynamic characteristics for flight projections. Static motor testing is conducted to identify impulse and determine flight potential. Flight projections were conducted in MATLAB to model trajectory caused by 2 acceleration stages. Stability data is obtained with onboard avionics. A launch was used to determine the final stability of the rocket and the accuracy of flight projections. These launches included Rocket 1 which travelled 215 ft and Rocket 2 which failed to leave the launch system.