Two-Body Problem

transform(from, to, a, ecc)

Transform anomaly a from one anomaly type to another for an orbit with eccentricity ecc.

Arguments

• from, to: Anomaly types
  • true_anomaly
  • eccentric_anomaly
  • mean_anomaly
• a: Current value of the anomaly
• ecc: Eccentricity of the orbit

Output

Returns the transformed anomaly.

References

• Farnocchia, Davide, Davide Bracali Cioci, and Andrea Milani. "Robust resolution of Kepler’s equation in all eccentricity regimes." Celestial Mechanics and Dynamical Astronomy 116, no. 1 (2013): 21-34.