Juno
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Liquid bipropellant rocket engine
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Purpose: Modular, experimental testbed to inform the design of future liquid rocket engines
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Cooling Method: Ablation
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Propellants: Ethanol (fuel) and liquid oxygen (oxidizer)
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Propellant Feed Type: Pressure-fed
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Chamber Pressure: 350 psi
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Thrust: 300 lbs
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ISP: 256 s
Status
The engine successfully test fired twice in the Fall of 2024, achieving 300 lbs of thrust on the first hot fire and 350 lbs of thrust on the second hot fire.
My Role
• Hand calculated all rocket engine geometry variables for combustion chamber, nozzle, and injector
• Developed “Rocket Engine Geometry Calculator” in MATLAB App Designer to expedite rocket engine geometry calculations
• Analyzed possible paths of combustion gas leakage and employed appropriate, cost-effective sealing methods, whether that be O- rings, metal crush seals, PTFE seals, etc.
• Developed a Microsoft Excel spreadsheet that calculates O-ring stress to validate Juno’s O-ring configuration
• Utilized CAD skills to model rocket engine parts in CATIA V5 and Autodesk Fusion 360
Rocket Engine Geometry Calculator - MATLAB
O-Ring Stress Calculator - Microsoft Excel
Juno Graphite Nozzle and Engine Housing
Juno Hardware
Former Project Lead and I Holding Juno
