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Orbital Simulation of Low Earth Satellites

Simulated satellite trajectories in low Earth orbit using Newtonian dynamics with gravitational and atmospheric drag forces. Developed MATLAB functions to solve differential equations via the Euler-Cromer method. Visualized orbital paths and analyzed parameters such as altitude, speed, and orbital period for 500+ satellites. Strengthened skills in numerical methods, MATLAB scripting, and physics-based modeling.

Trajectory of first satellite (ID: 0001) for the first 5000s

Altitude and Velocities of the first six satellites (ID: 0001-0006) for a period of 12,400 s

Initial and Final position of the orbits of all satellites (ID: 0001 - 0520) for a period of 6,000 s

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