Name

CL_kp_E2v — Eccentric anomaly to true anomaly

Calling Sequence

   v = CL_kp_E2v(e,E)
   
   

Description

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

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

  • Last update : 4/3/2008

Parameters

E:

eccentric anomaly [rad] (1xN)

e:

eccentricity (1xN)

v:

true 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_M2Egene, CL_kp_M2E, CL_kp_v2E

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);