Name

CL_kp_M2E — Solution of kepler's equation (ecc,M to E)

Calling Sequence

   E = CL_kp_M2E(ecc,M)
   
   

Description

  • Solves Kepler's equation for hyperoblic or elliptic orbits.

    Given the eccentricity ecc and the mean anomaly M, this function computes the eccentric anomaly E

  • Last update : 30/10/2007

Parameters

M:

mean anomaly [rad] (1xN)

ecc:

hyperbolic or elliptical eccentricity (ecc>1) (1xN)

E:

eccentric anomaly [rad] (1xN)

Authors

CNES - DCT/SB

Bibliography

1 CNES - MSLIB FORTRAN 90, Volume V (mvi_kepler_hyperb)

See also

CL_kp_M2Egene

Examples

E = CL_kp_M2E(0.001,3*%pi/8)