%0 Book Section
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%3 INPE-9539.pdf
%X This paper develops a semi-analytical study of the perturbation caused to a spacecraft by a third body involved in the dynamics. There are several important applications for this research, such calculate the effect of lunar and solar perturbations on high-altitude Earth satellites. In this present research the goal is to study the evolution of retrograde orbits around the Earth. There is a special interest to see under which conditions a near-circular orbit remains near-circular. The existence of circular, equatorial and frozen orbits are also considered. The results are valid for any system primaries by making a time transformation that depends on the masses of the bodies involved. Several plots will show the time-histories of the Keplerian elements of the orbits involved.
%@secondarydate 20021213
%E Winter, Othon Cabo,
%E Prado, Antonio Fernando Bertachini de Almeida.,
%T A fourth-order method for the third-body perturbation: application to retrograde orbits
%S Advances in space dynamics 2: applications in astronomy
%@format ISBN 85-17-00005-6
%@secondarytype PRE LN
%K ENGENHARIA E TECNOLOGIA ESPACIAL, perturbation, third body, orbit pertubation.
%B Advances in space dynamics 2: applications in astronomy
%@usergroup administrator
%@group DMC-INPE-MCT-BR
%C São José dos Campos
%@secondarykey INPE-9539-PRE/5192
%F 10467
%2 sid.inpe.br/iris@1905/2005/08.04.02.08.27
%I INPE
%P 94-111
%4 sid.inpe.br/iris@1905/2005/08.04.02.08
%D 2002
%@documentstage not transferred
%A Prado, Antonio Fernando Bertachini de Almeida,
%@area ETES
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}