some type hints

test/SpacecraftStateInterpolatorTest.py

@@ -48,7 +48,7 @@ from org.orekit.files.ccsds.definitions import CelestialBodyFrame
 from org.orekit.files.ccsds.ndm import ParsedUnitsBehavior, ParserBuilder, WriterBuilder
 from org.orekit.files.ccsds.ndm.odm import CartesianCovariance, KeplerianElements, SpacecraftParameters
 from org.orekit.files.ccsds.utils.generation import Generator, KvnGenerator
-from org.orekit.frames import Frame, FramesFactory, LOFType
+from org.orekit.frames import FactoryManagedFrame, Frame, FramesFactory, LOFType
 from org.orekit.orbits import KeplerianOrbit, PositionAngleType
 from org.orekit.time import AbsoluteDate, AbstractTimeInterpolator, DateComponents, TimeComponents, TimeScalesFactory
 from org.orekit.utils import AbsolutePVCoordinates, AngularDerivativesFilter, CartesianDerivativesFilter, Constants, IERSConventions, PVCoordinates, TimeStampedPVCoordinates
@@ -80,7 +80,7 @@ from java.util import ArrayList, HashMap
 from java.io import File
 from org.orekit.propagation import SpacecraftState, SpacecraftStateInterpolator
 from org.orekit.forces.gravity import HolmesFeatherstoneAttractionModel, SingleBodyAbsoluteAttraction
-from org.orekit.forces.gravity.potential import GravityFieldFactory
+from org.orekit.forces.gravity.potential import GravityFieldFactory, NormalizedSphericalHarmonicsProvider
 from org.orekit.propagation.numerical import NumericalPropagator
 from org.hipparchus.ode.nonstiff import DormandPrince853Integrator
 
@@ -107,7 +107,7 @@ class SpacecraftStateInterpolatorTest(unittest.TestCase):
             date = AbsoluteDate(DateComponents(2004, 1, 1),
                                 TimeComponents.H00,
                                 TimeScalesFactory.getUTC())
-            frame = FramesFactory.getEME2000()
+            frame: FactoryManagedFrame = FramesFactory.getEME2000()
             self.orbit = KeplerianOrbit(a, e, i, omega, OMEGA, lv, PositionAngleType.TRUE, frame, date, mu)
             earth = OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
                                      Constants.WGS84_EARTH_FLATTENING,
@@ -119,7 +119,7 @@ class SpacecraftStateInterpolatorTest(unittest.TestCase):
             self.orbitPropagator = EcksteinHechlerPropagator(self.orbit, self.attitudeLaw, self.mass,
                                                              ae, mu, c20, c30, c40, c50, c60)
 
-            self.absPVPropagator = self.setUpNumericalPropagator()
+            self.absPVPropagator: NumericalPropagator = self.setUpNumericalPropagator()
 
         except OrekitException as oe:
             self.fail(oe.getLocalizedMessage())
@@ -129,8 +129,8 @@ class SpacecraftStateInterpolatorTest(unittest.TestCase):
         self.orbit = None
         self.attitudeLaw = None
         
-    def setUpNumericalPropagator(self):
-        integrator = self.setUpIntegrator()
+    def setUpNumericalPropagator(self) -> NumericalPropagator:
+        integrator: DormandPrince853Integrator = self.setUpIntegrator()
 
         propagator = NumericalPropagator(integrator)
 
@@ -138,8 +138,8 @@ class SpacecraftStateInterpolatorTest(unittest.TestCase):
         propagator.setOrbitType(None)
 
         # Add force models
-        itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, True)
-        provider = GravityFieldFactory.getNormalizedProvider(6, 6)
+        itrf: FactoryManagedFrame = FramesFactory.getITRF(IERSConventions.IERS_2010, True)
+        provider: NormalizedSphericalHarmonicsProvider = GravityFieldFactory.getNormalizedProvider(6, 6)
         potential = HolmesFeatherstoneAttractionModel(itrf, provider)
 
         propagator.addForceModel(potential)
@@ -165,7 +165,7 @@ class SpacecraftStateInterpolatorTest(unittest.TestCase):
         return DormandPrince853Integrator(minStep, maxStep, tolerances[0], tolerances[1])
 
     def checkAbsPVInterpolationError(self, n, expectedErrorP, expectedErrorV, expectedErrorA, expectedErrorM, interpolator):
-        centerDate = self.absPV.getDate().shiftedBy(100.0)
+        centerDate: AbsoluteDate = self.absPV.getDate().shiftedBy(100.0)
         sample = []
         for i in range(n):
             dt = i * 900.0 / (n - 1)