Examples
// Elliptic and hyperbolic orbit: E = [1.7, 5.7]; ecc = [0.3, 1.5]; M = CL_kp_E2M(ecc,E); // Consistency test: E - CL_kp_M2E(ecc,M) // => 0 |  |  |
Eccentric anomaly to mean anomaly
M = CL_kp_E2M(ecc,E)
Computes mean anomaly from eccentric anomaly for elliptical and hyperbolic orbits:
- Elliptical orbits ( ecc < 1 ) : M = E - ecc * sin(E)
- Hyperbolic orbits ( ecc > 1 ) : M = ecc * sinh(E) - E
Eccentric anomaly [rad] (PxN or Px1)
Eccentricity (PxN or Px1)
Mean anomaly [rad] (PxN)
CNES - DCT/SB
1) Orbital Mechanics for Engineering Students, H D Curtis, Chapter 3, equation 3.11
2) Mecanique spatiale, CNES - Cepadues 1995, Tome I, section 4.6.6, page 181
// Elliptic and hyperbolic orbit: E = [1.7, 5.7]; ecc = [0.3, 1.5]; M = CL_kp_E2M(ecc,E); // Consistency test: E - CL_kp_M2E(ecc,M) // => 0 | | |