Modeling Orbital Decay of Low-Earth Orbit Satellites due to Atmospheric Drag: A Simplified Analytical Approach

2025/08/27 by S. Mahapatra, Mahapatra, Sukdev
Engineering · #Earth and Planetary Astrophysics (astro-ph.EP) #FOS: Physical sciences #Instrumentation and Methods for Astrophysics (astro-ph.IM) #Space Satellite Systems and Control #Spacecraft Design and Technology #Spacecraft Dynamics and Control

paper · pdf · doi:10.48550/arxiv.2508.19549

openalex publication_date 2025/08/27 · openalex created_date 2025/10/10 · openalex updated_date 2026/07/28

Abstract

Low-Earth Orbit (LEO) satellites are crucial for communications, navigation, and Earth observation. However, their operational lifetimes are strongly influenced by orbital decay due to atmospheric drag. This work presents a simplified analytical model of orbital decay in LEO, incorporating atmospheric density variations and satellite parameters. Using standard drag force equations and density models, we explore how altitude, satellite mass, and cross-sectional area affect decay timescales. Comparisons are made with existing NASA models and previous literature. The results highlight the importance of accurate atmospheric density representation and solar activity in predicting satellite lifetimes, especially relevant in the context of increasing space debris and mega-constellations.

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