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PyBurn

A Hybrid Rocket Motor Propulsion Model - Python

  • Combust.py : The primary run script, where all experimental / geometrical parameters are input
  • Thermo.py : Thermodynamical + some thermochemical calculations to determine combustion parameters
  • Nozzle.py : Isentropic flow through nozzles based on [5]. Determines thrust and efficiencies
  • Properties.py : Approximations of key thermochemical variables with respect to oxidizer/fuel ratio. Taken from [2], Fig 4
  • Inject.py : An orifice-plate model based injector flow rate calculator

Currently, only supports analysis of ABS/N2O rocket motors.

To run, call python Combust.py

References

  1. http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=1079&context=mae_facpub
  2. http://www.d.umn.edu/~rrosandi/Hybrids/Reports/Numerical_Model.pdf
  3. http://www.enu.kz/repository/2011/AIAA-2011-5909.pdf
  4. https://www.fire.tc.faa.gov/pdf/05-14.pdf
  5. https://goo.gl/1Eh1Gf
  6. Rocket Propulsion Elements, Sutton: https://goo.gl/kCFbHc