Name
CL_kp_M2v — True anomaly to mean anomaly
Calling Sequence
[v] = CL_kp_M2v(ecc,M)
Parameters
- ecc:
eccentricity (1xN)
- M:
mean anomaly [rad] (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
// Example
ecc = 0.1;
M = 0.2;
v = CL_kp_M2v(ecc,M)