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.

10.22161/ijaers.133.2