use of org.orekit.estimation.measurements.modifiers.RangeRateIonosphericDelayModifier in project Orekit by CS-SI.
the class IonoModifierTest method testRangeRateIonoModifier.
@Test
public void testRangeRateIonoModifier() throws OrekitException {
Context context = EstimationTestUtils.eccentricContext("regular-data:potential:tides");
final NumericalPropagatorBuilder propagatorBuilder = context.createBuilder(OrbitType.KEPLERIAN, PositionAngle.TRUE, true, 1.0e-6, 60.0, 0.001);
// create perfect range measurements
for (final GroundStation station : context.stations) {
station.getEastOffsetDriver().setSelected(true);
station.getNorthOffsetDriver().setSelected(true);
station.getZenithOffsetDriver().setSelected(true);
}
final Propagator propagator = EstimationTestUtils.createPropagator(context.initialOrbit, propagatorBuilder);
final List<ObservedMeasurement<?>> measurements = EstimationTestUtils.createMeasurements(propagator, new RangeRateMeasurementCreator(context, false), 1.0, 3.0, 300.0);
propagator.setSlaveMode();
final RangeRateIonosphericDelayModifier modifier = new RangeRateIonosphericDelayModifier(model, true);
for (final ObservedMeasurement<?> measurement : measurements) {
final AbsoluteDate date = measurement.getDate();
final SpacecraftState refstate = propagator.propagate(date);
RangeRate rangeRate = (RangeRate) measurement;
EstimatedMeasurement<RangeRate> evalNoMod = rangeRate.estimate(0, 0, new SpacecraftState[] { refstate });
// add modifier
rangeRate.addModifier(modifier);
//
EstimatedMeasurement<RangeRate> eval = rangeRate.estimate(0, 0, new SpacecraftState[] { refstate });
final double diffMetersSec = eval.getEstimatedValue()[0] - evalNoMod.getEstimatedValue()[0];
// TODO: check threshold
Assert.assertEquals(0.0, diffMetersSec, 0.016);
}
}
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