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š **Problem**
Propagating long times fails in different ways:
```python
In [5]: iss.propagate(100 * u.year)
---------------------------------------------------------------------------
Assā¦
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When using high eccentricity values the calculation is wrong. This image as ec = 0.5
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This module should handle all orbit manipulation. The organization of this module isn't necessarily trivial, and I really need to think of a good way of handling this. The _constructors_ in `smd` wereā¦
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Hi!,
I would like to create clones of a given comet, in order to study its orbital evolution from a statistical point of view. My PhD supervisor do that in Mercury, but would like to implement thā¦
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Hi Dominic,
I am starting to evaluate the performance of the new USM propagators, but it would be nice to use the number of function evaluations (so also including discarded step sizes), instead oā¦
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Hello,
I am trying to add the unified state model (USM7) to the set of Tudat propagators by following the wiki, but I get the following error:
```
Undefined symbols for architecture x86_64:
"ā¦
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A request to add the following to the `core` namespace, to be used in the `capture` object:
> Antenna direction. E.g. Azimuth + Elevation, but I would also like an alternative such as Right Ascensiā¦
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On running `$ python setup.py install`: I am getting the error as:
`Searching for pykep
Reading https://pypi.python.org/simple/pykep/
No local packages or working download links found for pykep
eā¦
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I am trying to get the cartesian position and velocity vectors for each propagation step in my orbit. I generated the orbit with Keplerian elements.
According to the documentation I should be ableā¦
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The Modified Equinoctical elements definition changes at 90 deg inclination for conversion from keplerian elements. This could pose a problem for polar orbit using the result of this conversion.