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1. Apogee

   Linked via "Eccentric Anomaly"

   While the physical distance $r_a$ is fixed for a given state vector, the angular position of the apogee relative to the spacecraft's current position is defined by the true anomaly ($\nu$). The true anomaly at apogee is always $180^\circ$ ($\pi$ radians).
   The Mean Anomaly ($M$) is often used to track a spacecraft's position over time. The relationship between the Mean Anomaly at a specific time ($M(t)$) and the [Mean An…