Abstract
The selenodetic use of artificial lunar satellites entails a dynamical problem because the greater magnitudes and longer periods of disturbing accelerations lead to more significant non-linearities, and entails statistical problems because tracking from the Earth coupled with the variety of terms in the lunar gravitational field having similar effects leads to ambiguities and ill-conditioning.
A solution is proposed for the dynamical problem in which a von Zeipel transformation is applied to remove short period effects to obtain a non-linear intermediate orbit which can be integrated numerically with relatively long time steps.
The statistical problem is investigated by analyzing hypothetical tracking data incorporating the anticipated characteristics of the lunar gravitational field as well as instrumental error and ionospheric refraction. Regardless of tracking accuracy, it appears that a satellite of high inclination will be more valuable than a satellite of low inclination, and that the best solution is obtained by combining the two.
Publication No. 502, Institute of Geophysics and Planetary Physics, University of California.
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© 1967 D. Reidel Publishing Company
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Kaula, W.M. (1967). Analysis of Satellite Orbit Perturbations to Determine the Lunar Gravitational Field. In: Measure of the Moon. Astrophysics and Space Science Library, vol 8. Springer, Dordrecht. https://doi.org/10.1007/978-94-010-3529-3_26
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DOI: https://doi.org/10.1007/978-94-010-3529-3_26
Publisher Name: Springer, Dordrecht
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