%0 Book Section
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%3 INPE-9521.pdf
%X The first China-Brazil Earth Resources Satellite (CBERS)was launched on 14th Oct. 1999, to explore Earth's natural resources. The orbit of CBERS is a Sun-synchronous polar orbit, highly beneath its orbits. The orbit inclination is such that the precession of the orbit, caused by the non-spherical harmonics of the Earth's gravity field, exactly opposes the annual revolution of the Earth around the Sun. Consequently, the orbital plane will always maintain its position relative to the Sun, the so-called Sun angle, when the satellite crosses the equator. This feature provides constant illumination conditions needed for the imaging payloads. On the other hand, the mission requirements demand precise orbit determination, ephemeris generation and ground track maintenance. In this context, the accurate computation of the ""mean"" semi-major axis or equivalently ""mean"" mean motion is an essential requirement in the present mission scenario and consequently can be accomplished with a set of ""mean"" orbital elements. Classical theory of mean elements does not provide precise solutions for long -term predictions . The impetus of such requirements makes it mandatory to analyze and assess the appropriate set of mean elements for orbit maintenance purposes. In this work, orbit-keeping analysis is carried out through numerical averaging to obtain the set of mean elements. The applicability and operational utility of the resulting, mean elements for precise orbit keeping is demonstrated using both live satellite and simulated data and has been put into operational setup.
%@secondarydate 20021213
%E Winter, Othon Cabo,
%E Prado, Antonio Fernando Bertachini de Almeida.,
%T Mean orbital elements analysis for orbit keeping
%S Advances in space dynamics 3: applications in astronautics
%@format ISBN 85-17-00006-4
%@secondarytype PRE LN
%K ENGENHARIA E TECNOLOGIA ESPACIAL, China-Brazil Earth Resources Satellite, CBERS, orbit keeping, orbit inclination.
%B Advances in space dynamics 3: applications in astronautics
%@usergroup administrator
%@group DMC-INPE-MCT-BR
%C São José dos Campos
%@secondarykey INPE-9521-PRE/5174
%F 10434
%2 sid.inpe.br/iris@1905/2005/08.04.01.37.16
%I INPE
%P 69-79
%4 sid.inpe.br/iris@1905/2005/08.04.01.37
%D 2002
%@documentstage not transferred
%A Polamraju, Rajendra Prasad,
%A Kuga, Hélio Koiti,
%@area ETES
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}