Lifetime reduction of a geosyncronous transfer orbit with the help of lunar-solar perturbations

Details Lifetime reduction of a geosyncronous transfer orbit with the help of lunar-solar perturbations Lifetime reduction of a geosyncronous transfer orbit with the help of lunar-solar perturbations

Aug 1995

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1995adspr..16..155s&link_type=abstract

Advances in Space Research, Volume 16, Issue 11, p. 155-161.

Physics

3

Scientific paper

This paper presents results of a model to reduce the lifetimes of GTO upper stages with the help of natural forces. Lunar and Solar gravitational perturbations on GTO orbits cause the eccentricity of the orbit to oscillate, while the semi major axis remains constant. This effect can be used to either lower or to raise the perigee altitude. If the perigee altitude is lowered a significant lifetime reduction of the GTO upper stage can occur. Whether the average perigee altitude (discussed in the paper) is higher or lower than the initial perigee altitude depends on the initial geometric relation between the orbital plane, argument of perigee of the GTO orbit and positions of Sun and Moon. The goal of this work is to determine launch windows for the GTO insertion in order to have minimum lifetimes for the GTO upper stage.

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