Returning to Goloka

Notice how the visual representation of the sun expands from its
original size and engulfs Mercury and touches the orbit of Venus, indicating,
perhaps, that the sun is becoming more violent. Also we have a number of
strange glyphs between the two main circular symbols. These could be
considered as harbingers of the flyby. We use this information in our
planning because it is better to be over-prepared than under-prepared. Our
guiding principle is to prepare for the worst while focusing on the creating a
community that will be fun to live in and provide us with an environment of
like-minded individuals and everything we need to promote our spiritual
evolution because we do not want to lose sight of the goal of human existence
- Moksha.
Predicting the exact date of the flyby is extremely complex, due to the
Kozai mechanism 12 , which causes an unbelievable complexity in the
calculations
12
From Wikipedia: In celestial mechanics, the Kozai mechanism, or the Lidov–Kozai
mechanism, is a perturbation of the orbit of a satellite by the gravity of another body
orbiting farther out, causing libration (oscillation about a constant value) of the orbit's
argument of pericenter. As the orbit librates, there is a periodic exchange between its
inclination and its eccentricity.
The effect was described in 1961 by the Soviet specialist in space dynamics
Michael Lidov while analyzing the orbits of artificial and natural satellites of planets, and
in 1962 by the Japanese astronomer Yoshihide Kozai while analyzing the orbits of the
asteroids. Since then this effect has been found to be an important factor shaping the
orbits of irregular satellites of the planets, trans-Neptunian objects, and a few extrasolar
planets and multiple star systems.
In the hierarchical, restricted three-body problem, it is assumed that the satellite
has negligible mass compared with the other two bodies (the "primary" and the
"perturber"), and that the distance between the primary and perturber is much greater
than the distance from the primary to the satellite. These assumptions would be valid,
for instance, in the case of an artificial satellite in a low-Earth orbit that is perturbed by
the moon, or a short-period comet that is perturbed by Jupiter.
Under these approximations, the orbit-averaged equations of motion for the
satellite have a conserved quantity: the component of the satellite's orbital angular
momentum parallel to the angular momentum of the primary/perturber angular
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