A Python-based orbital mechanics simulation tool that implements multiple numerical integration methods to propagate satellite orbits and compare their accuracy against reference data.
This project provides a complete framework for orbital propagation using three different numerical integration methods:
- Euler Method: First-order integration (simple but less accurate)
- Verlet Method: Second-order symplectic integration (good energy conservation)
- Runge-Kutta 4th Order (RK4): Fourth-order integration (high accuracy)
The propagator supports both dimensionalized and non-dimensionalized formulations of the orbital equations of motion, allowing for numerical stability analysis and performance comparison.