A physics-based 6-Degree-of-Freedom (6-DOF) flight simulation of the AEGIS-75 high-power sounding rocket developed using RocketPy. This project models rocket propulsion, aerodynamics, atmospheric conditions, stability, and dual-deployment parachute recovery to predict flight performance under realistic launch conditions.
The objective of this project is to design, model, and simulate a 75 mm diameter high-power sounding rocket using RocketPy. The simulation evaluates the rocket's flight dynamics, propulsion performance, aerodynamic stability, and recovery sequence before physical implementation.
The project demonstrates the application of computational tools in preliminary rocket design and performance analysis.
- 🚀 Complete 6-DOF rocket flight simulation
- 🔥 AeroTech M1850W solid rocket motor modelling
- 🌎 Real atmospheric forecast (GFS weather model)
- 📈 Aerodynamic stability analysis
- 📊 Custom power-on and power-off drag models
- 🪂 Dual-deployment parachute recovery
- 📉 Flight trajectory and performance visualization
- 📍 Google Earth trajectory export (KML)
- Python
- RocketPy
- NumPy
- Matplotlib
- Google Colab
| Parameter | Value |
|---|---|
| Rocket Name | AEGIS-75 |
| Diameter | 75 mm |
| Length | 3.10 m |
| Empty Mass | 18.0 kg |
| Loaded Mass | 22.87 kg |
| Nose Cone | Von Kármán |
| Fin Configuration | Four Trapezoidal Fins |
| Recovery System | Dual Deployment |
| Launch Rail Length | 6.0 m |
| Launch Inclination | 85° |
| Parameter | Value |
|---|---|
| Motor | AeroTech M1850W |
| Burn Time | 4.01 s |
| Propellant Mass | 2.956 kg |
| Average Thrust | 1679.50 N |
| Maximum Thrust | 2411 N |
| Total Impulse | 6734.78 Ns |
| Average Exhaust Velocity | 2278.41 m/s |
The simulation was performed using RocketPy's Forecast Atmospheric Model (GFS).
| Parameter | Value |
|---|---|
| Latitude | 19.15025° |
| Longitude | 73.23245° |
| Elevation | 72.6 m |
| Surface Wind Speed | 2.48 m/s |
| Surface Temperature | 298.13 K |
| Launch Date | 30 June 2026 |
| Parameter | Result |
|---|---|
| Apogee | 699.83 m |
| Burnout Altitude | 385.41 m (AGL) |
| Burnout Velocity | 118.58 m/s |
| Maximum Velocity | 128.90 m/s |
| Maximum Mach Number | 0.373 |
| Rail Exit Velocity | 27.36 m/s |
| Burn Time | 4.01 s |
| Maximum Motor Acceleration | 95.79 m/s² (9.77 g) |
| Maximum Stability Margin | 12.753 calibers |
The following analyses were performed:
- Rocket Geometry
- Atmospheric Conditions
- Aerodynamic Drag Analysis
- Stability Analysis
- 3D Flight Trajectory
- Elevation Profile
- Linear Kinematics
- Angular Motion
- Aerodynamic Forces
- Dynamic Pressure
- Energy Analysis
- Parachute Recovery Sequence
AEGIS-75-Rocket-Simulation/
── notebook/ └── AEGIS75_RocketPy.ipynb
── motor/ └── AeroTech_M1850W.rse
── airfoil/ └── NACA0012-radians.txt
── drag_curves/ ├── powerOnDragCurve.csv └── powerOffDragCurve.csv
── results/ ├── trajectory.kml ├── plots/ └── images
── report/ └── Project Aegis 75.pdf
── README.md
# ▶️ Getting Started
### Clone the Repository
```bash
git clone https://github.com/Anuj-777/AEGIS-75-Rocket-Simulation
pip install rocketpy numpy matplotlibOpen the notebook in Google Colab or Jupyter Notebook and execute all cells sequentially.
Through this project, the following concepts were explored:
- High-Power Rocket Design
- Flight Dynamics
- Six-Degree-of-Freedom Simulation
- Aerodynamic Stability
- Solid Rocket Propulsion
- Atmospheric Modelling
- Numerical Simulation using Python
- Data Visualization
- Engineering Performance Analysis
- Replace estimated aerodynamic coefficients with CFD/OpenRocket data.
- Validate simulation results using experimental flight data.
- Perform Monte Carlo analysis for wind and manufacturing uncertainties.
- Optimize fin geometry for improved aerodynamic performance.
- Integrate telemetry and sensor fusion for hardware-in-the-loop simulation.
Anuj Mangaj
Aerospace Engineering Student | IIT KHARAGPUR
Interests
- Flight Dynamics
- Rocket Propulsion
- Mechanism Design
- Aerospace Structures
- Embedded Systems
- Control Systems
- Numerical Simulation
This project is licensed under the MIT License.
- RocketPy Development Team
- AeroTech Rocket Motors
- Open-source Aerospace Community