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