poliastro.core.propagation.markley
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Module Contents¶
Functions¶
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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.