poliastro2.math.propagation.markley

poliastro2.math.propagation.markley(k, r0, v0, tof)

Solves the kepler problem by a non-iterative method. Relative error is around 1e-18, only limited by machine double-precision errors.

Parameters:

  • k (float) – Standar Gravitational parameter.

  • r0 (numpy.ndarray) – Initial position vector wrt attractor center.

  • v0 (numpy.ndarray) – Initial velocity vector.

  • tof (float) – Time of flight.

Returns:

  • rr (numpy.ndarray) – Final position vector.

  • vv (numpy.ndarray) – Final velocity vector.

Notes

The following algorithm was taken from http://dx.doi.org/10.1007/BF00691917.