Lunar orbit determination in the presence of unmodeled accelerations |
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| Authors: | D S Ingram B D Tapley |
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| Institution: | 1. Federal Systems Divisions, IBM Corporation, Houston, Tex., USA
2. Dept. of Aerospace Engineering and Engineering Mechanics, The University of Texas at Austin, Austin, Tex., USA
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| Abstract: | A technique for estimating the state of an artificial satellite in the presence of unmodeled accelerations is presented. The unmodeled acceleration is approximated by a first-order Gauss-Markov sequence which can be separated into a timewise correlated component and a purely random component. Using this approximation, a sequential procedure for estimating the position, velocity, and the unmodeled acceleration is developed. The method is evaluated by reducing range-rate observations obtained by tracking the Apollo 10 and 11 spacecraft during the lunar orbit phase of the mission. Numerical results are presented which show that the observation residual pattern lies within the observation noise standard deviation. The values of the estimated components of the unmodeled acceleration are repeatable from orbit to orbit within a given mission and from mission to mission when the same ground track is covered. Finally, the variation in the radial component of the unmodeled acceleration shows a high correlation with the reported location of the lunar surface mascons. |
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