This poster presents the development and fabrication of a robust detonation-based ignition system, with the primary goal of creating a reliable Deflagration-to-Detonation Transition (DDT) tube that operates using gaseous hydrogen and oxygen at 150 psi. This system is intended as a versatile ignition solution that can first be used to initiate combustion in liquid rocket engines which utilize Jet-A fuel and nitrous oxide (N₂O). These tests will serve as a critical validation platform to demonstrate system functionality in a simpler combustion environment. Once verified, this DDT system will be applied to initiate detonation in rotating detonation rocket engines (RDREs), where sustained detonation is the primary mode of thrust generation. Key parameters, including fill fraction, equivalence ratio, and ignition timing delay, were selected to achieve consistent and reliable ignition events. The pre-detonation rig and its components were fabricated and assembled successfully, demonstrating the system's functionality through preliminary testing. This research lays the foundation for future integration into advanced propulsion architectures, including RDREs and other detonation propulsion systems.