poliastro.core.propagation.markley

Module Contents

Functions

markley_coe(k, p, ecc, inc, raan, argp, nu, tof)
markley(k, r0, v0, tof)	Solves the kepler problem by a non-iterative method. Relative error is

poliastro.core.propagation.markley.markley_coe(k, p, ecc, inc, raan, argp, nu, tof)

poliastro.core.propagation.markley.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.