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