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\centerline{\bbf Elliptic Anomaly Expansions to Construct}
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\centerline{\bbf High--Eccentricity Artificial Satellite Theory}
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\centerline{\brm
EUGENE BRUMBERG}
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\centerline{\bit Institute of Applied Astronomy, St.-Petersburg 197042,
Russia}
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\centerline{\brm (Submitted for IAU Symp. 172, Paris, July 3--8, 1995)}
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\noindent{\bf Abstract.}
In the recent paper (E.Brumberg {\it et al.,} 1995) the Kaula's satellite
linear perturbation theory has been modified for the case of highly eccentric
orbits by replacing the mean anomaly $M$ and eccentricity $e$ by the elliptic
anomaly $w$ and Jacobi nome $q$ associated to the modulus $k=e$ of Jacobi
elliptic functions.  The main perturbations due to the Earth's asphericity
referred to the fixed equator were treated there. This technique is
generalized here in three aspects:
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\item{--}
inclusion of the third-body (luni-solar) perturbations,
\noindent\item{--}
employment of the arbitrary reference plane (the fixed
ecliptic) enabling one to take into account the perturbations due to the
rotation  of the equatorial plane, and
\item{--}
representation of the final perturbations explicitly in
terms of $w$ resulting in improved efficiency of the technique.
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\noindent With minor modifications this technique may be used to represent
the motion of asteroids and comets in highly eccentricitry orbits.
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\noindent {\bf Key words:}
Satellite motion, Kaula's theory, elliptic anomaly.

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\centerline{\bbf References}
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Brumberg, E., Brumberg, V.A., Konrad, Th., and Soffel, M.: 1995,
`Analytical Linear Perturbation Theory for
Highly Eccentric Satellite Orbits',
{\it Celes. Mech. and Dynam. Astron., in press}.

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