Examples
// Elliptic and hyperbolic orbit: v = [0.1, 0.2]; ecc = [0.3, 1.5]; M = CL_kp_v2M(ecc,v); // Consistency test: v - CL_kp_M2v(ecc,M) // => 0 |  |  |
True anomaly to mean anomaly
M = CL_kp_v2M(ecc,v)
Computes mean anomaly from true anomaly and eccentricity for elliptical and hyperbolic orbits.
Eccentricity (PxN or Px1)
True anomaly [rad] (PxN or Px1)
Mean anomaly [rad] (PxN)
CNES - DCT/SB
1) Orbital Mechanics for Engineering Students, H D Curtis, Chapter 3, equation 3.10a
2) Mecanique spatiale, CNES - Cepadues 1995, Tome I, section 4.6.6, page 179
// Elliptic and hyperbolic orbit: v = [0.1, 0.2]; ecc = [0.3, 1.5]; M = CL_kp_v2M(ecc,v); // Consistency test: v - CL_kp_M2v(ecc,M) // => 0 | | |