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PropellantCombustionSimulation

This project simulates combustion and flow characteristics of various rocket propellants using finite-rate chemistry and real gas effects.

Features

  • Finite-rate combustion kinetics modeling
  • Equilibrium temperature calculations
  • Wall temperature estimation
  • Real gas effects consideration
  • Flow parameter distributions
  • Thrust and specific impulse calculations
  • Heat flux analysis
  • Combustion stability analysis
  • Optional NN surrogate for Isp prediction (TensorFlow + scikit-learn)

Supported Propellants

  • MMH + N2O4
  • AF-M3125E
  • LOX + Methane
  • G.prop

Dependencies

  • NumPy
  • Matplotlib
  • Pandas
  • SciPy
  • scikit-learn
  • TensorFlow (2.15.x)

Installation

  1. Clone this repository
  2. (Recommended) Create and activate a virtual environment:
python3 -m venv .venv
source .venv/bin/activate
  1. Install dependencies:
pip install -r requirements.txt

Usage

Run the base simulation (analytic model only):

python src/combustion_simulation.py

This will generate visualizations comparing different propellants and their performance metrics.

import matplotlib
matplotlib.use('Agg')  # Add this line at the top if running in headless mode

def visualize_results():
    fuels = ["MMH + N2O4", "AF-M3125E", "LOX + Methane", "G.prop"]
    results = [combustion_simulation(fuel) for fuel in fuels]
    
    labels = ["Exhaust Velocity (m/s)", "Thrust (N)", "Specific Impulse (s)", "Equilibrium Temperature (K)", "Burn Time (s)", "Wall Temperature (K)"]
    for i, label in enumerate(labels):
        values = [res[label] for res in results]
        plt.figure(figsize=(8, 4))
        plt.bar(fuels, values, color=['blue', 'green', 'red', 'purple'])
        plt.ylabel(label)
        plt.title(f"Comparison of {label} for Different Fuels")
        plt.tight_layout()
        plt.savefig(f"{label.replace(' ', '_')}.png")
        plt.close()
    
    df = pd.DataFrame(results)[["Fuel"] + labels]
    print(df.to_string(index=False))

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