Abstract
Relative motion of objects moving in a close satellite formation is studied. The relative motion is expressed in the satellite reference frame R Λ B defined by orthogonal unit vectors in the radial, transverse and normal directions. Differential perturbations in orbital elements, satellite positions as well as in the radial, transverse and normal components of the radius vector are defined. Differential perturbations due to geopotential coefficients and luni-solar attraction are analysed for some exemplary satellites orbits. Results of a numerical analysis of motion have shown that the geopotential coefficients up to high degree and order as well as lunisolar effects have to be included into the applied force model to save the meter or centimeter level of accuracy in the description of the relative satellite motion.
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