Calculation the Low Orbits and More Stable for a Satellite around Mars

Abstract: This research examines various types of orbits around Mars. The effects of Mars's non-spherical shape, atmospheric drag, and solar attraction on these orbits were included in the calculations. The objective was to determine the optimal orbital elements to obtain a stable orbit of a satellite around Mars. The values of angles w and Ω were taken as 40° and 20°, respectively, while the orbit inclination was examined at three experimental values: i = 88°, 89°, and 90°. The perigee height above the Martian surface was assessed at three altitudes (hp = 50, 100, and 150 km) considering all perturbations except atmospheric drag. The orbital eccentricity was tested at values of e = 0.01, 0.02, 0.05, 0.08, and 0.1. The findings indicate that the most stable orbit was achieved with a low-altitude perigee (hp = 50 km), low eccentricity (e = 0.05), and an inclination of i = 90o. Keywords: Mars, Orbiting spacecraft, Orbital elements, Inclination, Eccentricity.