Examples
// Elliptic and hyperbolic orbit: v = [0.1, 0.2]; ecc = [0.3, 1.5]; E = CL_kp_v2E(ecc,v); // Consistency test: v - CL_kp_E2v(ecc,E) // => 0 |  |  |
True anomaly to eccentric anomaly
E = CL_kp_v2E(ecc,v)
Computes eccentric anomaly from true anomaly and eccentricity for elliptical and hyperbolic orbits.
True anomaly [rad] (PxN or Px1)
Eccentricity (PxN or Px1)
Eccentric anomaly. Undefined (%nan) if the true anomaly is not in the correct range. [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]; E = CL_kp_v2E(ecc,v); // Consistency test: v - CL_kp_E2v(ecc,E) // => 0 | | |