This repository contains a Python script for the analytical computation and graphical visualization of a Hohmann transfer maneuver, used to transfer a spacecraft between two circular Earth orbits with minimum propellant expenditure.
The Hohmann transfer is a two-impulse orbital maneuver widely applied in space missions to achieve orbit changes with optimal energy efficiency.
This project:
- Accepts user-defined initial (
r1) and final (r2) orbital radii; - Computes the semi-major axis of the transfer ellipse;
- Calculates required velocity increments (Δv₁ and Δv₂);
- Generates a graphical visualization including:
- Earth at the center;
- Initial circular orbit;
- Final circular orbit;
- Transfer ellipse;
- Impulse vectors (Δv₁ and Δv₂);
- Highlighted perigee and apogee.
This script is suitable for:
- Orbital mechanics demonstrations;
- Aerospace engineering coursework;
- Preliminary trajectory design analysis;
- Educational visualization of two-impulse transfer strategies.
Input the requested values:
Enter the initial orbital radius (r1) in km (e.g., 6578): Enter the final orbital radius (r2) in km (e.g., 42250):
You can reach me at rmilhomem[at]gmail[dot]com or connect on LinkedIn for collaborations.
Este projeto está licenciado sob a Licença MIT. Você pode usar, modificar e redistribuir este código livremente, desde que mencione o autor original.
