Simulating wether a nano-satellite can be charged while tumbling.

Two Line Element position calculator using sgp4

Generation of mean orbital elements (for TLE) from state vector

This project focuses on processing satellite data, specifically converting TLE data into satellite coordinates, filtering the data based on a user-defined polygon, and presenting the results to the user.

Python library to propagate satellite orbits.

Real-time satellite tracker and orbit propagator

dSGP4: differentiable SGP4. Supports differentiability, ML integration & embarassingly parallel computations