CL_kp_M2E

Description

• Solves Kepler's equation for hyperbolic or elliptical orbits.

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

  - Elliptical orbits ( ecc < 1 ) : E - ecc * sin(E) = M

  - Hyperbolic orbits ( ecc > 1 ) : ecc * sinh(E) - E = M

Parameters

M:

Mean anomaly [rad] (PxN or Px1)

ecc:

Eccentricity (PxN or Px1)

E:

Eccentric anomaly [rad] (PxN)

Authors

• CNES - DCT/SB

Bibliography

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

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

See also

• CL_kp_E2M

Examples

// Elliptic and hyperbolic orbit: M = [0.1, 0.2]; ecc = [0.3, 1.5]; E = CL_kp_M2E(ecc,M); // Consistency test: M - CL_kp_E2M(ecc,E) // => 0