Name

CL_kp_E2M — Eccentric anomaly to mean anomaly for elliptic and hyperbolic orbits

Calling Sequence

   M = CL_kp_E2M(e,E)
   
   

Description

  • Solves Kepler's equation E - e*sin(E) = M for the mean anomaly M, given the eccentricity e and the eccentric anomaly E for elliptic and hyperbolic orbits.
  • Last update : 4/3/2008

Parameters

E:

eccentric anomaly [rad] (1xN)

e:

eccentricity (1xN)

M:

mean anomaly [rad] (1xN)

Authors

CNES - DCT/SB

Bibliography

1 Orbital Mechanics for Engineering Students, H D Curtis, Chapter 3, equation 3.11

2 Mecanique spatiale, CNES - Cepadues 1995, Tome I, section 4.6.6, page 181

See also

CL_kp_M2Egene, CL_kp_M2E, CL_kp_E2v, CL_kp_v2E

Examples

// Reciprocity test
E=[1.7281 5.7281];
e=[0.37255 0.55];
M = CL_kp_E2M(e,E);
E2 = CL_kp_M2E(e,M);