Name
CL_kp_E2v — Eccentric anomaly to true anomaly
Calling Sequence
v = CL_kp_E2v(e,E)
Parameters
- E:
eccentric anomaly [rad] (1xN)
- e:
eccentricity (1xN)
- v:
true 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
E=[3.4794 5.7281];
e=[0.37255 0.55];
v = CL_kp_E2v(e,E);
E2 = CL_kp_v2E(e,v);