QUEEN PROPULSION Student Lead: Riley Lambert Student Team Members: Kendall Allen, Valerie Arana, Riley Lambert, Catherine Nguyen, Julia Payne, Dane Soaper Faculty: Professor Gary Cosentino and Dr. Shannon Lodoen Hydrogen combustion propulsion systems are emerging as a new clean-energy alternative within the aerospace industry. This alternative fuel source aims to reduce fossil fuel emissions and increase propulsion efficiency. Despite these advantages, this emerging technology faces two main obstacles. First, hydrogen does not conform to standardized safety regulations, as it is highly flammable and risks spontaneous combustion or flame back. Second, materials exposed to hydrogen display decreased ductility and are more likely to fail (material embrittlement). This has been identified as being especially a problem for the fuel line material carrying the hydrogen to the combustion chamber. Currently, Embry-Riddle’s Propulsion Laboratory lacks the means to investigate hydrogen combustion and embrittlement research under realistic environmental conditions. To address these challenges, Queen Propulsion, sponsored by Honeywell, is designing a hydrogen combustion test rig. Our design expands upon Mamba Propulsion’s initial combustor design to achieve ignition with hydrogen fuel and test hydrogen embrittlement within the fuel lines. Throughout this academic school year, Queen Propulsion will develop a standard testing rig for hydrogen combustion, achieve hydrogen ignition, and set the stage to advance research on hydrogen embrittlement. In doing so, we can propel Embry-Riddle to the forefront of alternative energy research and aid in the advancement of hydrogen propulsion technologies across the aerospace industry. VULCAN PROPULSION Student Lead: Kaitlyn E. Smith Student Team Members: Christopher Finnegan, Miles Holt, Kaitlyn E. Smith, William Temple, Ryan Toughill Faculty: Dr. Ambady Suresh, Dr. Matthew Haslam, Professor Andy Gerrick The Embry‑Riddle Aeronautical University, Prescott Liquid Rocket Program’s goal is to develop, launch to the Karman Line, and recover a reusable liquid‑propellant rocket. By means of various vehicle iterations such as Altair, Deneb, and Deneb 2, the program made advancements in propulsion testing by achieving a collegiate altitude record. However, ongoing technical problems restricted performance and reusability. Altair suffered an ignition‑caused explosion and valve/fitting failures. Deneb performed successful ignition and sustained flight but had shortcomings in engine efficiency, sensing of ignition, mass control, aerodynamics, and recovery. Deneb 2 was a repeat of subpar performance with the added feature of chamber ablation, and injector warping. These failures define three primary technology gaps: engine efficiency, robust ignition with abort/re‑start capability, and long-duration test chamber with thermal and mechanical degradation resistance. This capstone project will focus on the proposed engine which will be comprised of injector and chamber designs focused on increasing efficiency, a fluid-cooled chamber jacket permitting flight-like burn durations, and a torch ignitor for reliable and repeatable engine ignition. Achieving these objectives will improve program duration and provide a solid base for Embry-Riddle liquid propulsion teaching and research. Outcomes will inform future flight‑capable engines.
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SENIOR CAPSTONE PROJECTS
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