Name
CL_kp_v2E — True anomaly to eccentric anomaly
Calling Sequence
E = CL_kp_v2E(ecc,v)
Description
-
Computes eccentric anomaly E given eccentricity ecc
and true anomaly vfor elliptic and hyperbolic orbits.
- Last update : 4/3/2007
Parameters
- v:
true anomaly [rad] (1xN)
- ecc:
eccentricity (1xN)
- E:
eccentric anomaly [rad] (1xN)
Bibliography
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
Examples
// Reciprocity test
v=[3.4794 5.7281];
ecc=[0.37255 0.55];
E = CL_kp_v2E(ecc,v);
v2 = CL_kp_E2v(ecc,E);