Name

CL_kp_v2E — True anomaly to eccentric anomaly

Calling Sequence

   E = CL_kp_v2E(ecc,v)
   
   

Description

  • Computes eccentric anomaly E given eccentricity ecc and true anomaly vfor elliptic and hyperbolic orbits.
  • Last update : 4/3/2007

Parameters

v:

true anomaly [rad] (1xN)

ecc:

eccentricity (1xN)

E:

eccentric 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_E2v

Examples

// Reciprocity test
v=[3.4794 5.7281];
ecc=[0.37255 0.55];
E = CL_kp_v2E(ecc,v);
v2 = CL_kp_E2v(ecc,E);