Name
CL_kp_E2M — Eccentric anomaly to mean anomaly for elliptic and hyperbolic orbits
Calling Sequence
M = CL_kp_E2M(e,E)
Description
-
Solves Kepler's equation E - e*sin(E) = M for the mean anomaly M,
given the eccentricity e and the eccentric anomaly E for elliptic and hyperbolic orbits.
- Last update : 4/3/2008
Parameters
- E:
eccentric anomaly [rad] (1xN)
- e:
eccentricity (1xN)
- M:
mean anomaly [rad] (1xN)
Bibliography
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
Examples
// Reciprocity test
E=[1.7281 5.7281];
e=[0.37255 0.55];
M = CL_kp_E2M(e,E);
E2 = CL_kp_M2E(e,M);