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Juno

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  • Liquid bipropellant rocket engine

  • Purpose: Modular, experimental testbed to inform the design of future liquid rocket engines

  • Cooling Method: Ablation

  • Propellants: Ethanol (fuel) and liquid oxygen (oxidizer)

  • Propellant Feed Type: Pressure-fed

  • Chamber Pressure: 350 psi

  • Thrust: 300 lbs

  • ISP: 256 s

Status

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We have finished design of this engine and have completed the manufacturing of all the required hardware. We have begun the test campaign and will test fire it spring of 2024.

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​

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O-Ring Stress Calculator - Microsoft Excel

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Juno Graphite Nozzle and Engine Housing

Juno Hardware

Former Project Lead and I Holding Juno​

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