Simulation and Optimization of Satellite Re-Entry Trajectories Using MATLAB

Mohamed Shuaib.A, Dr. S. Charulatha

Satellite re-entry, MATLAB simulation, flight path angle, re-entry trajectory, Atmospheric drag, Differential equations, orbital dynamics, altitude-varying air density.

This paper presents a simulation-focused methodology for performing satellite re-entry dynamics analysis with MATLAB. When a satellite is descending, it is subjected to gravitational attraction, atmospheric drag and applied thrust; these factors can be described by solving a system of differential equations. The simulation is initiated at an altitude of 300 km with the given initial conditions and with the use of real-world properties such as altitude-varying air density and orbital dynamics. The simulations give an altitude decay, velocity change, and flight path angle history of re-entry. In addition, this model illustrates that atmospheric resistance becomes the dominant force of deceleration at low altitudes.

Received: 28 Jan 2026, Received in revised form: 25 Feb 2026, Accepted: 02 Mar 2026, Available online: 17 Mar 2026

10.22161/ijaers.133.2