Retrograde Satellite orbit
perturbation
atmospheric drag
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The actual position and velocity of the sun and the moon were calculate through one year , and the satellite position and velocity components (x,y,z, vx, vy, vz) were calculate as well as the momentum component at inclination (116.5?) , argument of perigee (30?), longitude node angle (40?), eccentricity (0.01), for deferent perigee height (200,300,..,1000 km). The acceleration of perturbations which were calculated in this work are the sun and the moon attraction on the satellite, the solar radiation pressure, the atmospheric drag as well as the earth oblatness. The result show that the perturbation forces of atmospheric drag acceleration is effect by altitude and the sun, moon attractio
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