Accession Number : ADA265779


Title :   Satellite Motion Around an Oblate Planet: A Perturbation Solution for All Orbital Parameters


Descriptive Note : Technical rept. Jan-Apr 93,


Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA DEPT OF MATHEMATICS


Personal Author(s) : Danielson, D A ; Latta, G E ; Sagovac, C P ; Krambeck, S D ; Snider, J R


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a265779.pdf


Report Date : 06 May 1993


Pagination or Media Count : 28


Abstract : The search for a universal solution of the equations of motion for a satellite orbiting an oblate planet is a subject that has merited great interest because of its theoretical and practical implications. Here, a complete first- order perturbation solution, including the effects of the J2 terms in the planet's potential, is given in terms of standard orbital parameters. The simple formulas provide a fast method for predicting satellite orbits that is more accurate than the two-body formulas. These predictions are shown to agree well with those of a completely numerical code and with actual satellite data. Also, in an appendix, it is rigorously proven that a satellite having negative mechanical energy remains for all time within a spherical annulus with radii approximately equal to the perigee and apogee of its initial osculating ellipse. ... Perturbation solution, Oblate planet, Orbital parameters.


Descriptors :   *ORBITS , *EQUATIONS OF MOTION , *ARTIFICIAL SATELLITES , KINEMATICS , PREDICTIONS , PERTURBATIONS , PLANETS , ELLIPSES , MECHANICAL ENERGY , APOGEE , PERIGEE


Subject Categories : Spacecraft Trajectories and Reentry


Distribution Statement : APPROVED FOR PUBLIC RELEASE