A semi-analytical method for computing third-body effects on earth and lunar satellite orbits

Computer Science

Scientific paper

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Earth Orbits, Lunar Satellites, Orbit Calculation, Satellite Orbits, Satellite Perturbation, Three Body Problem, Explorer 28 Satellite, Lunar Gravitational Effects, Oblate Spheroids, Satellite Drag, Solar Gravitation

Scientific paper

A method for a computing satellite orbits perturbed by third-body attractions is described. The method extends Stumpff's previous approach in order to account for those cases in which satellite orbits approach so close to the Earth that the influences of the oblateness and atmosphere of the Earth cannot be neglected. The method was tested by comparing actual with predicted orbits for Explorer 28 and was found to yield accurate predictions for all but the final 130 days of the satellite's three year life span. It was also used to study the effects of earth and solar attraction on lunar satellite orbits. A relation was found between orbit direction and perturbation magnitude, such that the chance of impact on the moon or escape from the lunar region was greater for satellites in direct rather than retrograde orbits, especially when these orbits were at altitudes greater than 30,000 Km.

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