poliastro.core.propagation.recseries

Module Contents

Functions

recseries_coe(k, p, ecc, inc, raan, argp, nu, tof[, ...])

recseries(k, r0, v0, tof[, method, order, numiter, rtol])

Kepler solver for elliptical orbits with recursive series approximation
poliastro.core.propagation.recseries.recseries_coe(k, p, ecc, inc, raan, argp, nu, tof, method='rtol', order=8, numiter=100, rtol=1e-08)
poliastro.core.propagation.recseries.recseries(k, r0, v0, tof, method='rtol', order=8, numiter=100, rtol=1e-08)

Kepler solver for elliptical orbits with recursive series approximation method. The order of the series is a user defined parameter.

Parameters

  • k (float) – Standard gravitational parameter of the attractor.

  • r0 (numpy.ndarray) – Position vector.

  • v0 (numpy.ndarray) – Velocity vector.

  • tof (float) – Time of flight.

  • method (str) – Type of termination method (‘rtol’,’order’)

  • order (int, optional) – Order of recursion, defaults to 8.

  • numiter (int, optional) – Number of iterations, defaults to 100.

  • rtol (float, optional) – Relative error for accuracy of the method, defaults to 1e-8.

Returns

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

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

Notes

This algorithm uses series discussed in the paper Recursive solution to Kepler’s problem for elliptical orbits - application in robust Newton-Raphson and co-planar closest approach estimation with DOI: http://dx.doi.org/10.13140/RG.2.2.18578.58563/1