This thesis intends to investigate the enhancements made to the pneumatic system in the University of Central Florida shock tube, with a focus on expanding control over final temperature and pressure conditions for low-pressure, high-temperature environments. The project explores key upgrades, including a higher-pressure actuator to increase breaking pressure and an optimized cage design that allows the cage face to withstand a higher force, improving overall durability. Additionally, it tests the limits of the new actuator to ensure reliability under extreme conditions. These advancements enable the collection of accurate data from consistent shocks, which is essential for rocket plume speciation and high-temperature gas dynamics in hypersonic flight.