added test for impulse maneuver

src/test/java/org/orekit/forces/maneuvers/ImpulseManeuverTest.java

+/* Copyright 2002-2008 CS Communication & Systèmes
+ * Licensed to CS Communication & Systèmes (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.forces.maneuvers;
+
+import junit.framework.Test;
+import junit.framework.TestCase;
+import junit.framework.TestSuite;
+
+import org.apache.commons.math.geometry.Vector3D;
+import org.orekit.attitudes.LofOffset;
+import org.orekit.errors.OrekitException;
+import org.orekit.frames.Frame;
+import org.orekit.iers.IERSDirectoryCrawler;
+import org.orekit.orbits.KeplerianOrbit;
+import org.orekit.orbits.Orbit;
+import org.orekit.propagation.SpacecraftState;
+import org.orekit.propagation.analytical.KeplerianPropagator;
+import org.orekit.propagation.events.NodeDetector;
+import org.orekit.time.AbsoluteDate;
+import org.orekit.time.ChunkedDate;
+import org.orekit.time.ChunkedTime;
+import org.orekit.time.UTCScale;
+
+public class ImpulseManeuverTest extends TestCase {
+
+    public void testInclinationManeuver() throws OrekitException {
+        final Orbit initialOrbit =
+            new KeplerianOrbit(24532000.0, 0.72, 0.3, Math.PI, 0.4, 2.0,
+                               KeplerianOrbit.MEAN_ANOMALY,
+                               Frame.getJ2000(),
+                               new AbsoluteDate(new ChunkedDate(2008, 06, 23),
+                                                new ChunkedTime(14, 18, 37),
+                                                UTCScale.getInstance()),
+                               3.986004415e14);
+        final double a  = initialOrbit.getA();
+        final double e  = initialOrbit.getE();
+        final double i  = initialOrbit.getI();
+        final double mu = initialOrbit.getMu();
+        final double vApo = Math.sqrt(mu * (1 - e) / (a * (1 + e)));
+        double dv = 0.99 * Math.tan(i) * vApo;
+        KeplerianPropagator propagator = new KeplerianPropagator(initialOrbit, LofOffset.LOF_ALIGNED);
+        propagator.addEventDetector(new ImpulseManeuver(new NodeDetector(initialOrbit, Frame.getJ2000()),
+                                                        new Vector3D(dv, Vector3D.PLUS_J), 400.0));
+        SpacecraftState propagated = propagator.propagate(new AbsoluteDate(initialOrbit.getDate(), 8000));
+        assertEquals(0.0028257, propagated.getI(), 1.0e-6);
+    }
+
+    public void setUp() {
+        System.setProperty(IERSDirectoryCrawler.IERS_ROOT_DIRECTORY, "regular-data");
+    }
+
+    public static Test suite() {
+        return new TestSuite(ImpulseManeuverTest.class);
+    }
+
+}