Hybrid Rocket Engine @ VCU

In my senior year of college, I took it upon myself to dive into rocket propulsion and engine design—something we didn’t cover much in class. After a lot of late nights and digging through textbooks and research papers, I put together a small team of four and we set out to design a hybrid rocket engine from the ground up. I led the effort across system design, component modeling, and building out a custom data acquisition setup to support static fire testing. Once the design was solid, I started machining the engine parts by hand using manual tools in our shop. It was a hands-on, ground-up project that blended theory, teamwork, and fabrication—exactly the kind of challenge I love.

  • Performed trade studies to select propellant and engine configurations while minimizing engine mass and costs.

  • Led 4 person team to keep project timeline on track as well as steer the team towards the right direction.

  • Designed combustion chamber, injector bulkhead, nozzle, and nozzle retaining ring.

  • Conducted hand calculations to ensure a minimum factor of safety of 2 is found in the combustion chamber and all bolted connections during firing.

  • Began machining of combustion chamber and injector bulkhead,

  • Delivered engineering drawing with specifications to local machine shop for graphite nozzle.

Engine Specifications

  • Oxidizer: Nitrous Oxide

  • Fuel: High-Density Polyethylene

  • Thrust: 112 lbf

  • Oxidizer to Fuel Ratio: 6.5

  • Combustion Chamber Pressure: 500 psi

  • Mass flow rate: 0.4585 lb/s

  • Dry weight: 5.60 lbs

  • Diameter: 2.25 in

  • Height: 36.15 in

My roles

Graphite nozzle, designed by me.