$LastChangedDate: 27-Juil-2011 $

# CL_kp_M2Ecir

Mean arg. of latitude to eccentric arg. of latitude (Kepler's equation)

## Calling Sequence

       psoE = CL_kp_M2Ecir(ex,ey,psoM)

## Description

- Solves the 'generalized' Kepler's equation for elliptical orbits.

  It computes the eccentric argument of latitude psoE from the mean argument of latitude psoM and the eccentricity vector components ex and ey.

## Parameters

ex:

  x component of eccentricity vector (PxN or Px1)

ey:

  y component of eccentricity vector (PxN or Px1)

psoM:

  Mean argument of latitude (=w+M) [rad] (PxN or Px1)

psoE:

  Eccentric argument of latitude (=w+E) [rad] (PxN)

## Authors

- CNES - DCT/SB

## Bibliography

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

## See also

- CL_kp_M2E

## Examples

    pom = 2*%pi/3;
    ecc = 0.001;
    ex = ecc * cos(pom);
    ey = ecc * sin(pom);
    M = (0:4)*%pi/4;
    E = CL_kp_M2Ecir(ex,ey,pom+M) - pom;

    // Now using CL_kp_M2E :
    E = CL_kp_M2E(ecc,M)