/* Copyright 2002-2017 CS Systèmes d'Information
* Licensed to CS Systèmes d'Information (CS) under one or more
* contributor license agreements. See the NOTICE file distributed with
* this work for additional information regarding copyright ownership.
* CS licenses this file to You under the Apache License, Version 2.0
* (the "License"); you may not use this file except in compliance with
* the License. You may obtain a copy of the License at
*
* http://www.apache.org/licenses/LICENSE-2.0
*
* Unless required by applicable law or agreed to in writing, software
* distributed under the License is distributed on an "AS IS" BASIS,
* WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
* See the License for the specific language governing permissions and
* limitations under the License.
*/
package org.orekit.propagation.events;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.hipparchus.util.FastMath;
import org.junit.Assert;
import org.junit.Before;
import org.junit.Test;
import org.orekit.Utils;
import org.orekit.bodies.GeodeticPoint;
import org.orekit.bodies.OneAxisEllipsoid;
import org.orekit.errors.OrekitException;
import org.orekit.frames.FramesFactory;
import org.orekit.orbits.EquinoctialOrbit;
import org.orekit.orbits.KeplerianOrbit;
import org.orekit.orbits.Orbit;
import org.orekit.orbits.PositionAngle;
import org.orekit.propagation.Propagator;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.analytical.EcksteinHechlerPropagator;
import org.orekit.propagation.analytical.KeplerianPropagator;
import org.orekit.propagation.events.handlers.ContinueOnEvent;
import org.orekit.time.AbsoluteDate;
import org.orekit.time.TimeScale;
import org.orekit.time.TimeScalesFactory;
import org.orekit.utils.Constants;
import org.orekit.utils.IERSConventions;
import org.orekit.utils.PVCoordinates;
public class LongitudeExtremumDetectorTest {
@Test
public void testNoCrossing() throws OrekitException {
final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true));
LongitudeExtremumDetector d =
new LongitudeExtremumDetector(earth).
withMaxCheck(60).
withThreshold(1.e-6).
withHandler(new ContinueOnEvent<LongitudeExtremumDetector>());
Assert.assertEquals(60.0, d.getMaxCheckInterval(), 1.0e-15);
Assert.assertEquals(1.0e-6, d.getThreshold(), 1.0e-15);
Assert.assertEquals(AbstractDetector.DEFAULT_MAX_ITER, d.getMaxIterationCount());
Assert.assertSame(earth, d.getBody());
final TimeScale utc = TimeScalesFactory.getUTC();
final Vector3D position = new Vector3D(-6142438.668, 3492467.56, -25767.257);
final Vector3D velocity = new Vector3D(505.848, 942.781, 7435.922);
final AbsoluteDate date = new AbsoluteDate(2003, 9, 16, utc);
final Orbit orbit = new EquinoctialOrbit(new PVCoordinates(position, velocity),
FramesFactory.getEME2000(), date,
Constants.EIGEN5C_EARTH_MU);
Propagator propagator =
new EcksteinHechlerPropagator(orbit,
Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS,
Constants.EIGEN5C_EARTH_MU,
Constants.EIGEN5C_EARTH_C20,
Constants.EIGEN5C_EARTH_C30,
Constants.EIGEN5C_EARTH_C40,
Constants.EIGEN5C_EARTH_C50,
Constants.EIGEN5C_EARTH_C60);
EventsLogger logger = new EventsLogger();
propagator.addEventDetector(logger.monitorDetector(d));
propagator.propagate(date.shiftedBy(Constants.JULIAN_DAY));
Assert.assertEquals(0, logger.getLoggedEvents().size());
}
@Test
public void testZigZag() throws OrekitException {
final OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true));
LongitudeExtremumDetector d =
new LongitudeExtremumDetector(600.0, 1.e-6, earth).
withHandler(new ContinueOnEvent<LongitudeExtremumDetector>());
Assert.assertEquals(600.0, d.getMaxCheckInterval(), 1.0e-15);
Assert.assertEquals(1.0e-6, d.getThreshold(), 1.0e-15);
Assert.assertEquals(AbstractDetector.DEFAULT_MAX_ITER, d.getMaxIterationCount());
KeplerianOrbit orbit =
new KeplerianOrbit(24464560.0, 0.7311, 0.122138, 3.10686, 1.00681,
0.048363, PositionAngle.MEAN,
FramesFactory.getEME2000(),
AbsoluteDate.J2000_EPOCH,
Constants.EIGEN5C_EARTH_MU);
Propagator propagator = new KeplerianPropagator(orbit);
EventsLogger logger = new EventsLogger();
propagator.addEventDetector(logger.monitorDetector(d));
propagator.propagate(orbit.getDate().shiftedBy(Constants.JULIAN_DAY));
double[] expectedLongitudes = new double[] {
74.85115958654778, 39.51032449280883, -84.25729072475329, -119.598124966418, 116.63425894645886
};
double[] expectedLatitudes = new double[] {
-3.8404256460679336, 3.4237236065561536, -3.840419828222964, 3.4237214483413734, -3.840413360572555
};
Assert.assertEquals(5, logger.getLoggedEvents().size());
for (int i = 0; i < 5; ++i) {
SpacecraftState state = logger.getLoggedEvents().get(i).getState();
GeodeticPoint gp = earth.transform(state.getPVCoordinates(earth.getBodyFrame()).getPosition(),
earth.getBodyFrame(), null);
Assert.assertEquals(expectedLongitudes[i], FastMath.toDegrees(gp.getLongitude()), 1.0e-10);
Assert.assertEquals(expectedLatitudes[i], FastMath.toDegrees(gp.getLatitude()), 1.0e-10);
}
}
@Before
public void setUp() {
Utils.setDataRoot("regular-data");
}
}