Cassini trajectory

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Does anyone know of a simple method to calculate first-order
perturbations in the ascending node and argument of perigee
for a hyperbolic escape trajectory from Earth?

I am attempting to generate a simulation of the hyperbolic
departure trajectory of the Cassini spacecraft (with the
ultimate goal of producing a visual search ephemeris).  There
is plenty of information on two-body hyperbolic orbits in
astrodynamics texts, but I have not run across any mention of
the effects of the Earth's oblateness on a hyperbolic escape
trajectory.

The perturbations in the ascending node and argument of perigee
certainly cannot be ignored when the orbit is elliptical.  Does
the same apply to a hyperbolic orbit?

      Curtis Haase
      Dallas, Texas
      73007.2024@compuserve.com

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