Abstract
An analysis of the orbital evolution of the ESA's Hipparcos satellite is presented. Hipparcos operated between August 1989 and March 1993 in a highly elliptical orbit: a geostationary transfer orbit with increased perigee height. The requirements of the scientific mission included high accuracy knowledge of the position and velocity vectors of the spacecraft as a function of time. Through a study of the variations in the total orbital energy, the loss of energy during the mission as a result of non-conservative forces is recovered. These are explained as largely due to atmospheric drag during perigee passages. Apparent variations in the drag coefficient are in agreement with orientation variations of the satellite during those perigee passages. Two different models used for calculating the atmospheric drag give significantly different results, confirming earlier findings by other users of those models.
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Dalla Torre, A., van Leeuwen, F. A Detailed Analysis of the Operational Orbit of the Hipparcos Satellite. Space Science Reviews 108, 451–470 (2003). https://doi.org/10.1023/A:1026215716256
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DOI: https://doi.org/10.1023/A:1026215716256