Publication Details
Abstract
In order to understand how atmospheric drag affects satellites in low Earth Low Earth orbit (LEO), this analysis concentrates on the sensitivity of results to changes in the area-to-mass ratio (A/m) and the solar radiation pressure coefficient (CR). While the solar radiation pressure causes a secular change in the argument of perigee, inclination, and right ascension of the ascending node, especially for satellites with a large A/m ratio, atmospheric drag gradually reduces the semi-major axis with a corresponding increase in the orbital eccentricity. The Celestial Mechanics program used analytical models to simulate the impact of perturbative forces on orbital elements, while the numerical calculations and analysis were performed using MATLAB. The response of orbital elements to these perturbative forces was estimated using Gauss' equations for orbital changes, along with empirical atmospheric density models - NRLMSISE-00 and JB2008. The results showed that with an increase in the A/m ratio, orbital decay increases and the long-term evolution of the orbital elements is altered due to increased radiation and drag factors. To ensure the predictability of orbital motions and reliably assess operational satellite life while minimizing the risks due to space debris in low Earth orbit (LEO) orbits, appropriate determination of A/m and CR values is extremely necessary.