https://github.com/jonnyhyman/pyburn

Hybrid Rocket Propulsion Model [Python]
https://github.com/jonnyhyman/pyburn

combustion combustion-models hybrid propulsion rocket

Last synced: 2 months ago
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Hybrid Rocket Propulsion Model [Python]

• Host: GitHub
• URL: https://github.com/jonnyhyman/pyburn
• Owner: jonnyhyman
• Created: 2017-09-25T19:01:55.000Z (over 7 years ago)
• Default Branch: master
• Last Pushed: 2017-09-26T21:09:32.000Z (over 7 years ago)
• Last Synced: 2024-01-29T11:24:24.085Z (12 months ago)
• Topics: combustion, combustion-models, hybrid, propulsion, rocket
• Language: Python
• Size: 9.77 KB
• Stars: 13
• Watchers: 3
• Forks: 3
• Open Issues: 1
• Metadata Files:
  • Readme: README.md

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README

        
# 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

0. http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=1079&context=mae_facpub

1. http://www.d.umn.edu/~rrosandi/Hybrids/Reports/Numerical_Model.pdf

2. http://www.enu.kz/repository/2011/AIAA-2011-5909.pdf

3. https://www.fire.tc.faa.gov/pdf/05-14.pdf

4. https://goo.gl/1Eh1Gf

5. Rocket Propulsion Elements, Sutton: https://goo.gl/kCFbHc