Name

CL_kp_v2M — True anomaly to mean anomaly

Calling Sequence

   [M] = CL_kp_v2M(ecc,v)
   
   

Description

  • Computes mean anomaly given true anomaly and eccentricity, for elliptic and hyperbolic orbits.

    NOTE: this function does not handle parabolic orbits (eccentricity around 1+-epsilon).

  • Last update : 4/3/2008

Parameters

ecc:

eccentricity (1xN)

v:

true anomaly [rad] (1xN)

M:

mean anomaly [rad] (1xN)

Authors

CNES - DCT/SB

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

See also

CL_kp_M2v

Examples

// Example
ecc = 0.1;
v = 0.2;
M = CL_kp_v2M(ecc,v)