fix urls

docs/source/examples/going-to-jupiter-with-python-using-jupyter-and-poliastro.myst.md

@@ -37,7 +37,7 @@ from hapsira.twobody import Orbit
 from hapsira.util import norm, time_range
 ```
 
-All the data for Juno's mission is sorted [here](https://github.com/hapsira/hapsira/wiki/EuroPython:-Per-Python-ad-Astra). The main maneuvers that the spacecraft will perform are listed down:
+All the data for Juno's mission is sorted [here](https://github.com/poliastro/poliastro/wiki/EuroPython:-Per-Python-ad-Astra). The main maneuvers that the spacecraft will perform are listed down:
 
 * Inner cruise phase 1: This will set Juno in a new orbit around the sun.
 * Inner cruise phase 2: Fly-by around Earth. Gravity assist is performed.

docs/source/examples/going-to-mars-with-python-using-poliastro.myst.md

@@ -13,7 +13,7 @@ kernelspec:
 
 # Going to Mars with Python using hapsira
 
-This is an example on how to use [hapsira](https://github.com/hapsira/hapsira), a little library I've been working on to use in my Astrodynamics lessons. It features conversion between **classical orbital elements** and position vectors, propagation of **Keplerian orbits**, initial orbit determination using the solution of the **Lambert's problem** and **orbit plotting**.
+This is an example on how to use [hapsira](https://github.com/pleiszenburg/hapsira), a little library I've been working on to use in my Astrodynamics lessons. It features conversion between **classical orbital elements** and position vectors, propagation of **Keplerian orbits**, initial orbit determination using the solution of the **Lambert's problem** and **orbit plotting**.
 
 In this example we're going to draw the trajectory of the mission [Mars Science Laboratory (MSL)](http://mars.jpl.nasa.gov/msl/), which carried the rover Curiosity to the surface of Mars in a period of something less than 9 months.
 

docs/source/examples/loading-OMM-and-TLE-satellite-data.myst.md

@@ -28,7 +28,7 @@ kernelspec:
 
 +++
 
-However, it turns out that GP data in general, and TLEs in particular, are poorly understood even by professionals ([[1]](https://www.linkedin.com/posts/tom-johnson-32333a2_flawed-data-activity-6825845118990381056-yJX7), [[2]](https://twitter.com/flightclubio/status/1435303066085982209), [[3]](https://github.com/hapsira/hapsira/issues/1185)). The core issue is that TLEs and OMMs contain _Brouwer mean elements_, which **cannot be directly translated to osculating elements**.
+However, it turns out that GP data in general, and TLEs in particular, are poorly understood even by professionals ([[1]](https://www.linkedin.com/posts/tom-johnson-32333a2_flawed-data-activity-6825845118990381056-yJX7), [[2]](https://twitter.com/flightclubio/status/1435303066085982209), [[3]](https://github.com/poliastro/poliastro/issues/1185)). The core issue is that TLEs and OMMs contain _Brouwer mean elements_, which **cannot be directly translated to osculating elements**.
 
 From "Spacetrack Report #3":
 
@@ -58,7 +58,7 @@ Therefore, the **correct** way of using GP data is:
 As explained in the [Orbit Mean-Elements Messages (OMMs) support assessment](https://opensatcom.org/2020/12/28/omm-assessment-sgp4-benchmarks/) deliverable of OpenSatCom, OMM input/output support in open source libraries is somewhat scattered. Luckily, [python-sgp4](https://pypi.org/project/sgp4/) supports reading OMM in CSV and XML format, as well as usual TLE and 3LE formats. On the other hand, Astropy has accurate transformations from TEME to other reference frames.
 
 ```{code-cell} ipython3
-# From https://github.com/hapsira/hapsira/blob/main/contrib/satgpio.py
+# From https://github.com/pleiszenburg/hapsira/blob/main/contrib/satgpio.py
 """
 Author: Juan Luis Cano Rodríguez
 

src/hapsira/twobody/propagation/farnocchia.py

@@ -52,7 +52,7 @@ def propagate_many(self, state, tofs):
         rv0 = state.to_value()
 
         # TODO: This should probably return a ClassicalStateArray instead,
-        # see discussion at https://github.com/hapsira/hapsira/pull/1492
+        # see discussion at https://github.com/poliastro/poliastro/pull/1492
         rr, vv = farnocchia_rv_gf(k, *rv0, tofs.to_value(u.s))  # pylint: disable=E0633
 
         return (

src/hapsira/twobody/sampling.py

@@ -91,7 +91,7 @@ def sample(self, orbit):
         # However, we are also returning the epochs
         # (since computing them here is more efficient than doing it from the outside)
         # but there are open questions around StateArrays and epochs.
-        # See discussion at https://github.com/hapsira/hapsira/pull/1492
+        # See discussion at https://github.com/poliastro/poliastro/pull/1492
         cartesian = CartesianRepresentation(
             rr, differentials=CartesianDifferential(vv, xyz_axis=1), xyz_axis=1
         )
@@ -160,7 +160,7 @@ def sample(self, orbit):
         # However, we are also returning the epochs
         # (since computing them here is more efficient than doing it from the outside)
         # but there are open questions around StateArrays and epochs.
-        # See discussion at https://github.com/hapsira/hapsira/pull/1492
+        # See discussion at https://github.com/poliastro/poliastro/pull/1492
         cartesian = CartesianRepresentation(
             rr, differentials=CartesianDifferential(vv, xyz_axis=1), xyz_axis=1
         )

tests/tests_plotting/test_orbit_plotter.py

@@ -242,7 +242,7 @@ def test_set_frame_plots_same_colors():
 
 
 def test_redraw_keeps_trajectories():
-    # See https://github.com/hapsira/hapsira/issues/518
+    # See https://github.com/poliastro/poliastro/issues/518
     op = OrbitPlotter()
     trajectory = churi.sample()
     op.plot_body_orbit(Mars, J2000_TDB, label="Mars")

tests/tests_twobody/test_orbit.py

@@ -419,7 +419,7 @@ def test_sample_numpoints():
 
 
 def test_sample_big_orbits():
-    # See https://github.com/hapsira/hapsira/issues/265
+    # See https://github.com/poliastro/poliastro/issues/265
     ss = Orbit.from_vectors(
         Sun,
         [-9_018_878.6, -94_116_055, 22_619_059] * u.km,
@@ -1199,14 +1199,14 @@ def test_time_to_anomaly(expected_nu):
     # In some corner cases the resulting anomaly goes out of range,
     # and rather than trying to fix it right now
     # we will wait until we remove the round tripping,
-    # see https://github.com/hapsira/hapsira/issues/921
+    # see https://github.com/poliastro/poliastro/issues/921
     # FIXME: Add test that verifies that `orbit.nu` is always within range
     assert_quantity_allclose(iss_propagated.nu, expected_nu, atol=1e-12 * u.rad)
 
 
 @pytest.mark.xfail
 def test_can_set_iss_attractor_to_earth():
-    # See https://github.com/hapsira/hapsira/issues/798
+    # See https://github.com/poliastro/poliastro/issues/798
     epoch = Time("2019-11-10 12:00:00")
     ephem = Ephem.from_horizons(
         "International Space Station",
@@ -1235,7 +1235,7 @@ def test_issue_916(mock_query):
 
 
 def test_near_parabolic_M_does_not_hang(near_parabolic):
-    # See https://github.com/hapsira/hapsira/issues/907
+    # See https://github.com/poliastro/poliastro/issues/907
     expected_nu = -168.65 * u.deg
     orb = near_parabolic.propagate_to_anomaly(expected_nu)
 
@@ -1253,7 +1253,7 @@ def test_propagation_near_parabolic_orbits_zero_seconds_gives_same_anomaly(
 
 
 def test_propagation_near_parabolic_orbits_does_not_hang(near_parabolic):
-    # See https://github.com/hapsira/hapsira/issues/475
+    # See https://github.com/poliastro/poliastro/issues/475
     orb_final = near_parabolic.propagate(near_parabolic.period)
 
     # Smoke test

tests/tests_twobody/test_propagation.py

@@ -347,7 +347,7 @@ def test_propagate_to_date_has_proper_epoch():
 )
 def test_propagate_long_times_keeps_geometry(method):
     # TODO: Extend to other propagators?
-    # See https://github.com/hapsira/hapsira/issues/265
+    # See https://github.com/poliastro/poliastro/issues/265
     time_of_flight = 100 * u.year
 
     res = iss.propagate(time_of_flight, method=method)
@@ -436,7 +436,7 @@ def test_propagation_sets_proper_epoch():
 
 
 def test_sample_around_moon_works():
-    # See https://github.com/hapsira/hapsira/issues/649
+    # See https://github.com/poliastro/poliastro/issues/649
     orbit = Orbit.circular(Moon, 100 << u.km)
 
     coords = orbit.sample(10)
@@ -446,7 +446,7 @@ def test_sample_around_moon_works():
 
 
 def test_propagate_around_moon_works():
-    # See https://github.com/hapsira/hapsira/issues/649
+    # See https://github.com/poliastro/poliastro/issues/649
     orbit = Orbit.circular(Moon, 100 << u.km)
     new_orbit = orbit.propagate(1 << u.h)