Name
CL_kp_v2M — True anomaly to mean anomaly
Calling Sequence
[M] = CL_kp_v2M(ecc,v)
Parameters
- ecc:
eccentricity (1xN)
- v:
true anomaly [rad] (1xN)
- M:
mean 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;
v = 0.2;
M = CL_kp_v2M(ecc,v)