mubody.core.kepler.lambert#

mubody.core.kepler.lambert(r1, r2, alpha, TOF, nu_guess=0)#

Solves lambert problem for circular and coplanar orbits.

Parameters:

  • r1 (float) – Semi-major axis of departure planet [km]

  • r2 (float) – Semi-major axis of arrival planet [km]

  • alpha (float) – Angle between r1 and r2 vectors [rad]

  • TOF (float) – Time of flight [days]

  • nu_guess (float, optional) – Initial guess for departure TA [rad]

Returns:

  • a (float) – Semi-major axis of transfer orbit [km]

  • e (ndarray) – Eccentricity of transfer orbit [-]

  • nu (float, optional) – TA of departure [rad]