Satellite Trajectory Analysis Tool

Python-based interactive tool for visualizing satellite orbital parameters and analyzing orbital trajectories.

This application provides an interactive graphical interface where users can modify Keplerian orbital elements and visualize the resulting satellite orbit in real time.

The project combines concepts from orbital mechanics with Python-based scientific computing and data visualization.

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Features

• Interactive GUI built with Tkinter
• Adjustable Keplerian orbital elements using sliders
• 3D visualization of satellite orbits
• Altitude vs time analysis using SGP4 propagation
• Export orbital parameters to CSV

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Technologies Used

Python
NumPy
Matplotlib
Tkinter
SGP4 orbital propagation

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Example Interface

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Installation

Clone the repository and install the required libraries:

pip install -r requirements.txt

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Usage

Run the application with:

Satellite_trajectory_analysis.py

The GUI allows users to adjust orbital parameters and visualize the resulting orbit.

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Scientific Background

Satellite trajectories can be described using six Keplerian elements:

• Semi-major axis (a)
• Eccentricity (e)
• Inclination (i)
• Right Ascension of Ascending Node (RAAN)
• Argument of Perigee (ω)
• Mean Anomaly (ν)

The altitude propagation uses Two-Line Element (TLE) data and the SGP4 orbit propagation model commonly used in satellite tracking.

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Future Improvements

• Add perturbation modeling
• Implement additional orbit propagation models
• Add real satellite TLE import
• Improve visualization capabilities