Combustion simulations of hybrid rocket engines

Introduction

This is a repository for creating combustion simulations of hybrid rocket engines.

Required libraries

• numpy
• pandas
• matplotlib
• Scipy
• Jupter notebook

Program description

• pe_iteration.py

Optimizes the combustion chamber pressure and nozzle exit pressure. Version 1 has been released. The calculation time is 1.3 seconds (M1 mac OSX, 16 GB memory). It has been checked for consistency with the Excel version.

• tb_iteration.py

Optimizes the burn time. Version 1 has been released. Calculation time is 14 seconds (M1 mac OSX, 16 GB memory). Checking the consistency with Excel version.

• enginesim.ipynb

A Jupyter notebook that can run pe_iteration.py and tb_iteration.py simultaneously.