Design and Implementation of a High-Powered Rocket to Investigate Flight Performance and Fin Flutter During Transonic Flight

A two-stage, high-powered rocket was designed to investigate transonic flight dynamics with a deliberate application of fin flutter. The rocket utilized solid propellant, L-class (total impulse 2,714 N-s), and K-class (total impulse 1,434 N-s) motors in the booster and sustainer sections, respectively, to maintain its transonic flight profile for an extended period. Finite element analysis, computational fluid dynamics, and flight simulation software were used in the design process. The final design included three sets of fins, one set on each rocket section to ensure overall flight stability, and a third set designed to exhibit fin flutter. The flutter fins featured a small planform area and thin cross-section to induce flutter, and they were instrumented with strain gauges to gather data on fin deflection and frequency. Additionally, the nose cone was designed to minimize drag and heat transfer and was instrumented with an infrared camera within to collect interior surface temperature data. Design methodology, the resulting build, and subsequent work to compare with design predictions are discussed. Design methodology, the resulting build, and subsequent works to compare with design predictions are discussed. This investigation advances the design of high-power rockets breaking the sound barrier and provides valuable insight into rocket stability, fin flutter, and aerodynamic performance.