Abstract
Abstract The focus of this paper is the design of a self-maintenance orbit using two natural forces against each other. The effect of perturbations due to Earth's oblateness up to the third order on both the semi-major axis and eccentricity for a low Earth orbit satellite together with the perturbation due to air drag on the same orbital parameters were used, in order to create self-maintenance orbits. Numerical results were simulated for a low earth orbit satellite, which substantiates the applicability of the results.
Highlights
Introduction was considered byBezdek (2004) [5]
Numerical results were simulated for a low earth orbit satellite, which substantiates the applicability of the results
Akram Masoud et al (2018) [8] investigated the problem of artificial frozen orbits around the Earth; they designed such orbits taking into account the main zonal harmonics up to J4 and solar radiation pressure with the minimum control thrust required
Summary
The effect of perturbation due to air drag on the semi-major axis and on the eccentricity of the satellite can be written as [9]:. The secular perturbation on the semi-major axis and eccentricity due to air drag can be formulated from equations (1) and (2) up to the O [e7] as (∆a)D. R the mean equatorial radius of the Earth, ω the argument of the perigee, Jk the zonal harmonics, given by J2 = 1.08263 × 10−3, J3 = − 2.5322 × 10−6, J4 = −1.6110 × 10−6, D4 = J22 + J4 = −0.4389122 × 10−6, and αi and βj, i = 1, .
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