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Apogee
Linked via "Mean 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… -
Orbital Elements
Linked via "Mean Anomaly"
Longitude of the Ascending Node ($\Omega$): The right ascension of the ascending node. This is the angle in the reference plane, measured eastward from the vernal equinox (or the $X$-axis of the reference frame), to the point where the orbit crosses the reference plane moving from south to north (the ascending node).
Argument of Periapsis ($\omega$ or $\varpi$): The angle measured withi… -
Orbital Elements
Linked via "Mean Anomaly"
| $\Omega$ | Longitude of Ascending Node | Radians (rad) | Plane Rotation about $Z$-axis |
| $\omega$ | Argument of Periapsis | Radians (rad) | Ellipse Rotation in Orbital Plane |
| $M$ or $T_0$ | Mean Anomaly or Time of Periapsis Passage | Radians or Seconds (s) | Instantaneous Position |
Computational Realization and Reference Plane Stability