Mean anomaly

Area swept out per unit time   by an object in an elliptical orbit, and   by an imaginary object in a circular orbit (with the same orbital period). Both sweep out equal areas in equal times, but the angular rate of sweep varies for the elliptical orbit and is constant for the circular orbit. Shown are mean anomaly and true anomaly for two units of time. (Note that for visual simplicity, a non-overlapping circular orbit is diagrammed, thus this circular orbit with same orbital period is not shown in true scale with this elliptical orbit: for scale to be true for the two orbits of equal period, these orbits must intersect.)
Part of a series on
Astrodynamics
Orbital elements
Types of two-body orbits by
eccentricity
Equations
Gravitational influences
N-body orbits
Preflight engineering
Efficiency measures
Propulsive maneuvers

In celestial mechanics, the mean anomaly is the fraction of an elliptical orbit's period that has elapsed since the orbiting body passed periapsis, expressed as an angle which can be used in calculating the position of that body in the classical two-body problem. It is the angular distance from the pericenter which a fictitious body would have if it moved in a circular orbit, with constant speed, in the same orbital period as the actual body in its elliptical orbit.[1][2]

  1. ^ Montenbruck, Oliver (1989). Practical Ephemeris Calculations. Springer-Verlag. p. 44. ISBN 0-387-50704-3.
  2. ^ Meeus, Jean (1991). Astronomical Algorithms. Willmann-Bell, Inc., Richmond, VA. p. 182. ISBN 0-943396-35-2.