CL_kp_M2Ecir

Description

• This function is deprecated.

  Replacement function: CL_kp_anomConvertCir

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

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) or mean longitude (=w+raan+M) [rad] (PxN or Px1)

psoE:

Eccentric argument of latitude (=w+E) or eccentric longitude (=w+raan+E) ([rad] (PxN)

Authors

• CNES - DCT/SB

Bibliography

• 1) Procedures for solving Kepler's Equation - A.W. Odell and R.H Gooding - 1986

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)