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fix: adapt python bindings for tabulated orbit model (#102)
* fix: adapt python bindings for tabulated * feat: add some more tests * chore: clean up test * feat: missed a spot --------- Co-authored-by: Remy Derollez <remy@loftorbital.com> Co-authored-by: vishwa shah <vishwa@loftorbital.com>
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| Original file line number | Diff line number | Diff line change |
|---|---|---|
| @@ -1,99 +1,79 @@ | ||
| # Apache License 2.0 | ||
| # Apache License 2.0 | ||
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| import pytest | ||
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| import numpy | ||
| from ostk.physics import Environment | ||
| from ostk.physics.units import Length, Angle | ||
| from ostk.physics.time import Scale, Instant, DateTime | ||
|
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| import ostk.physics as physics | ||
| from ostk.astrodynamics.trajectory import Orbit, State | ||
| from ostk.astrodynamics.trajectory.orbit.models import SGP4 | ||
| from ostk.astrodynamics.trajectory.orbit.models.sgp4 import TLE | ||
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| import ostk.astrodynamics as astrodynamics | ||
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| Length = physics.units.Length | ||
| Angle = physics.units.Angle | ||
| Scale = physics.time.Scale | ||
| Instant = physics.time.Instant | ||
| Interval = physics.time.Interval | ||
| DateTime = physics.time.DateTime | ||
| Position = physics.coordinate.Position | ||
| Velocity = physics.coordinate.Velocity | ||
| Frame = physics.coordinate.Frame | ||
| Environment = physics.Environment | ||
| @pytest.fixture | ||
| def earth(): | ||
| return Environment.default().access_celestial_object_with_name("Earth") | ||
|
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| Trajectory = astrodynamics.Trajectory | ||
| Model = astrodynamics.trajectory.Model | ||
| Orbit = astrodynamics.trajectory.Orbit | ||
| Pass = astrodynamics.trajectory.orbit.Pass | ||
| Kepler = astrodynamics.trajectory.orbit.models.Kepler | ||
| COE = astrodynamics.trajectory.orbit.models.kepler.COE | ||
| SGP4 = astrodynamics.trajectory.orbit.models.SGP4 | ||
| TLE = astrodynamics.trajectory.orbit.models.sgp4.TLE | ||
| State = astrodynamics.trajectory.State | ||
| Access = astrodynamics.Access | ||
|
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| earth = Environment.default().access_celestial_object_with_name("Earth") | ||
| class TestOrbit: | ||
| def test_trajectory_orbit_constructors(self, earth): | ||
| # Construct Two-Line Element set | ||
| tle = TLE( | ||
| "1 25544U 98067A 18231.17878740 .00000187 00000-0 10196-4 0 9994", | ||
| "2 25544 51.6447 64.7824 0005971 73.1467 36.4366 15.53848234128316", | ||
| ) | ||
|
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| # Construct orbit using SGP4 model | ||
| orbit = Orbit(SGP4(tle), earth) | ||
|
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| def test_trajectory_orbit_constructors(): | ||
| # Construct Two-Line Element set | ||
| tle = TLE( | ||
| "1 25544U 98067A 18231.17878740 .00000187 00000-0 10196-4 0 9994", | ||
| "2 25544 51.6447 64.7824 0005971 73.1467 36.4366 15.53848234128316", | ||
| ) | ||
| assert orbit is not None | ||
| assert isinstance(orbit, Orbit) | ||
| assert orbit.is_defined() | ||
|
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| # Construct orbit using SGP4 model | ||
| orbit = Orbit(SGP4(tle), earth) | ||
| # Construct get state at current epoch | ||
| state: State = orbit.get_state_at(Instant.now()) | ||
|
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| assert orbit is not None | ||
| assert isinstance(orbit, Orbit) | ||
| assert orbit.is_defined() | ||
| assert state is not None | ||
| assert isinstance(state, State) | ||
|
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| # Construct get state at current epoch | ||
| state: State = orbit.get_state_at(Instant.now()) | ||
| def test_trajectory_orbit_circular(self, earth): | ||
| epoch = Instant.date_time(DateTime(2018, 1, 1, 0, 0, 0), Scale.UTC) | ||
| altitude = Length.kilometers(500.0) | ||
| inclination = Angle.degrees(45.0) | ||
|
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| assert state is not None | ||
| assert isinstance(state, State) | ||
| orbit: Orbit = Orbit.circular(epoch, altitude, inclination, earth) | ||
|
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| @pytest.mark.skip | ||
| def test_trajectory_orbit_equatorial(self, earth): | ||
| epoch = Instant.date_time(DateTime(2018, 1, 1, 0, 0, 0), Scale.UTC) | ||
| altitude = Length.kilometers(500.0) | ||
| eccentricity = 0.1 | ||
|
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| def test_trajectory_orbit_circular(): | ||
| epoch = Instant.date_time(DateTime(2018, 1, 1, 0, 0, 0), Scale.UTC) | ||
| altitude = Length.kilometers(500.0) | ||
| inclination = Angle.degrees(45.0) | ||
| orbit: Orbit = Orbit.equatorial(epoch, altitude, eccentricity, earth) | ||
|
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| orbit: Orbit = Orbit.circular(epoch, altitude, inclination, earth) | ||
| assert orbit is not None | ||
| assert isinstance(orbit, Orbit) | ||
| assert orbit.is_defined() | ||
|
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| @pytest.mark.skip | ||
| def test_trajectory_orbit_circular_equatorial(self, earth): | ||
| epoch = Instant.date_time(DateTime(2018, 1, 1, 0, 0, 0), Scale.UTC) | ||
| altitude = Length.kilometers(500.0) | ||
|
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| @pytest.mark.skip | ||
| def test_trajectory_orbit_equatorial(): | ||
| epoch = Instant.date_time(DateTime(2018, 1, 1, 0, 0, 0), Scale.UTC) | ||
| altitude = Length.kilometers(500.0) | ||
| eccentricity = 0.1 | ||
| orbit: Orbit = Orbit.circular_equatorial(epoch, altitude, earth) | ||
|
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| orbit: Orbit = Orbit.equatorial(epoch, altitude, eccentricity, earth) | ||
| assert orbit is not None | ||
| assert isinstance(orbit, Orbit) | ||
| assert orbit.is_defined() | ||
|
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| assert orbit is not None | ||
| assert isinstance(orbit, Orbit) | ||
| assert orbit.is_defined() | ||
| @pytest.mark.skip | ||
| def test_trajectory_orbit_sun_synchronous(self, earth): | ||
| epoch = Instant.date_time(DateTime(2018, 1, 1, 0, 0, 0), Scale.UTC) | ||
| altitude = Length.kilometers(500.0) | ||
|
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| orbit: Orbit = Orbit.sun_synchronous(epoch, altitude, earth) | ||
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| @pytest.mark.skip | ||
| def test_trajectory_orbit_circular_equatorial(): | ||
| epoch = Instant.date_time(DateTime(2018, 1, 1, 0, 0, 0), Scale.UTC) | ||
| altitude = Length.kilometers(500.0) | ||
|
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| orbit: Orbit = Orbit.circular_equatorial(epoch, altitude, earth) | ||
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| assert orbit is not None | ||
| assert isinstance(orbit, Orbit) | ||
| assert orbit.is_defined() | ||
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| @pytest.mark.skip | ||
| def test_trajectory_orbit_sun_synchronous(): | ||
| epoch = Instant.date_time(DateTime(2018, 1, 1, 0, 0, 0), Scale.UTC) | ||
| altitude = Length.kilometers(500.0) | ||
|
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| orbit: Orbit = Orbit.sun_synchronous(epoch, altitude, earth) | ||
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| assert orbit is not None | ||
| assert isinstance(orbit, Orbit) | ||
| assert orbit.is_defined() | ||
| assert orbit is not None | ||
| assert isinstance(orbit, Orbit) | ||
| assert orbit.is_defined() |
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