The methods renewed more order implemented also the magnetic field.

OrekitJava/.classpath

@@ -8,7 +8,7 @@
 	<classpathentry kind="src" path="lib/orekit-7.0/src/test/resources"/>
 	<classpathentry kind="src" path="lib/orekit-7.0/src/main/java"/>
 	<classpathentry kind="src" path="lib/orekit-7.0/src/tutorials/resources"/>
-	<classpathentry kind="con" path="org.eclipse.jdt.launching.JRE_CONTAINER/org.eclipse.jdt.internal.debug.ui.launcher.StandardVMType/JavaSE-1.8"/>
+	<classpathentry kind="con" path="org.eclipse.jdt.launching.JRE_CONTAINER/org.eclipse.jdt.internal.debug.ui.launcher.StandardVMType/JavaSE-1.7"/>
 	<classpathentry kind="lib" path="lib/commons-math3-3.4.1-javadoc.jar"/>
 	<classpathentry kind="lib" path="lib/commons-math3-3.4.1.jar"/>
 	<classpathentry kind="lib" path="lib/commons-net-3.3.jar"/>

OrekitJava/.settings/org.eclipse.jdt.core.prefs

@@ -1,11 +1,11 @@
 eclipse.preferences.version=1
 org.eclipse.jdt.core.compiler.codegen.inlineJsrBytecode=enabled
-org.eclipse.jdt.core.compiler.codegen.targetPlatform=1.8
+org.eclipse.jdt.core.compiler.codegen.targetPlatform=1.7
 org.eclipse.jdt.core.compiler.codegen.unusedLocal=preserve
-org.eclipse.jdt.core.compiler.compliance=1.8
+org.eclipse.jdt.core.compiler.compliance=1.7
 org.eclipse.jdt.core.compiler.debug.lineNumber=generate
 org.eclipse.jdt.core.compiler.debug.localVariable=generate
 org.eclipse.jdt.core.compiler.debug.sourceFile=generate
 org.eclipse.jdt.core.compiler.problem.assertIdentifier=error
 org.eclipse.jdt.core.compiler.problem.enumIdentifier=error
-org.eclipse.jdt.core.compiler.source=1.8
+org.eclipse.jdt.core.compiler.source=1.7

OrekitJava/test/de/netsat/orekit/matlab/MagenticFieldTest.java

@@ -1,24 +1,49 @@
 package de.netsat.orekit.matlab;
 
+import org.apache.commons.math3.geometry.euclidean.threed.Vector3D;
 import org.apache.commons.math3.ode.nonstiff.AdaptiveStepsizeIntegrator;
 import org.apache.commons.math3.ode.nonstiff.DormandPrince853Integrator;
+import org.orekit.attitudes.Attitude;
+import org.orekit.bodies.GeodeticPoint;
+import org.orekit.bodies.OneAxisEllipsoid;
 import org.orekit.errors.OrekitException;
+import org.orekit.frames.Frame;
+import org.orekit.frames.FramesFactory;
+import org.orekit.models.earth.GeoMagneticElements;
+import org.orekit.models.earth.GeoMagneticField;
 import org.orekit.orbits.KeplerianOrbit;
 import org.orekit.orbits.OrbitType;
 
+import de.netsat.orekit.NetSatConfiguration;
 import de.netsat.orekit.matlab.loadScripts;
+import de.netsat.orekit.matlab.MatlabPushHandler;
+
 import org.orekit.propagation.SpacecraftState;
 import org.orekit.propagation.numerical.NumericalPropagator;
+import org.orekit.time.AbsoluteDate;
+import org.orekit.utils.IERSConventions;
+import org.orekit.utils.PVCoordinates;
+import org.orekit.utils.TimeStampedAngularCoordinates;
 
 import matlabcontrol.MatlabConnectionException;
 import matlabcontrol.MatlabInvocationException;
 import matlabcontrol.MatlabProxy;
 
 public class MagenticFieldTest {
+
+	/**
+	 * 
+	 * @param mi
+	 * @return
+	 * @throws MatlabInvocationException
+	 * @throws OrekitException
+	 */
 	public static SpacecraftState runNumericalPropagatorlocal(MatlabInterface mi)
 			throws MatlabInvocationException, OrekitException
 
 	{
+		String[] options = { "velocity" };
+		NetSatConfiguration.init();
 		int sat_nr = 1;
 		Object[] returningObject;
 		returningObject = mi.returningEval("setNumericalPropagatorSettings()", 5);
@@ -28,27 +53,90 @@ public static SpacecraftState runNumericalPropagatorlocal(MatlabInterface mi)
 		double maxstep = ((double[]) returningObject[2])[0];
 		double duration = ((double[]) returningObject[3])[0];
 		double outputStepSize = ((double[]) returningObject[4])[0];
+
 		final OrbitType propagationType = OrbitType.KEPLERIAN;
 		final double[][] tolerances = NumericalPropagator.tolerances(positionTolerance, keplerOrbit, propagationType);
 		AdaptiveStepsizeIntegrator integrator = new DormandPrince853Integrator(minStep, maxstep, tolerances[0],
 				tolerances[1]);
-        NumericalPropagator numericPropagator = new NumericalPropagator(integrator);
-		numericPropagator.setOrbitType(propagationType);
-        SpacecraftState finalState = numericPropagator.propagate(keplerOrbit.getDate().shiftedBy(duration));
-
-        return finalState;
-
 
+		SpacecraftState initialState = new SpacecraftState(keplerOrbit,
+				new Attitude(FramesFactory.getEME2000(),
+						new TimeStampedAngularCoordinates(keplerOrbit.getDate(),
+								new PVCoordinates(new Vector3D(10, 10), new Vector3D(1, 2)),
+								new PVCoordinates(new Vector3D(15, 3), new Vector3D(1, 2)))),
+				1.0);
+
+		NumericalPropagator numericPropagator = new NumericalPropagator(integrator);
+		numericPropagator.setInitialState(initialState);
+		// new matlabPushStepHandler(mi);
+		numericPropagator.setMasterMode(outputStepSize, new MatlabPushHandler(mi, options));
+		SpacecraftState finalState = numericPropagator.propagate(keplerOrbit.getDate().shiftedBy(duration));
+
+		return finalState;
+
+	}
+
+	/**
+	 * Set the variable in matltab (the variable should be the type double or
+	 * could be casted to double.
+	 * 
+	 * @param mi
+	 * @param name
+	 * @param value
+	 * @throws MatlabInvocationException
+	 */
+	public void setVariableInMatlab(MatlabInterface mi, String name, double value) throws MatlabInvocationException {
+
+		mi.getProxy().setVariable(name, value);
+	}
+
+	/**
+	 * Converts the ECI Coordinates (R;V) to Latitude, Longitude, Altitude
+	 * (L;L;A). The point it uses the ITRF (Inertial Terrestrial reference frame
+	 * for the frame.
+	 * 
+	 * @param ECICoordinates
+	 * @param oae
+	 * @param date
+	 * @return
+	 * @throws OrekitException
+	 */
+	public static GeodeticPoint getLLA(Vector3D ECICoordinates, OneAxisEllipsoid oae, AbsoluteDate date)
+			throws OrekitException {
+		return oae.transform(ECICoordinates, FramesFactory.getITRF(IERSConventions.IERS_2010, true), date);
+	}
+
+	/**
+	 * Calculates the magnetic field in a given ECI points.
+	 * 
+	 * @param ECICoordinates
+	 * @param oae
+	 * @param date
+	 * @param model
+	 * @return
+	 * @throws OrekitException
+	 */
+	public static Vector3D calculateMagenticField(Vector3D ECICoordinates, OneAxisEllipsoid oae, AbsoluteDate date,
+			GeoMagneticField model) throws OrekitException {
+		GeodeticPoint geop = getLLA(ECICoordinates, oae, date);
+		// The altitude which is delivered by the getLLA function is in m it
+		// should be converted to KM.
+		double altitude = geop.getAltitude() / 1000;
+		double latitude = geop.getLatitude();
+		double longtitude = geop.getLongitude();
+		GeoMagneticElements geome = model.calculateField(Math.toDegrees(latitude), Math.toDegrees(longtitude),
+				altitude);
+		return geome.getFieldVector();
 	}
 
 	public static void main(String[] args)
 			throws OrekitException, MatlabConnectionException, MatlabInvocationException {
-		//Object[] obj = null;
+		// Object[] obj = null;
 		MatlabInterface mi;
 		mi = new MatlabInterface(MatlabInterface.MATLAB_PATH, null);
-		//obj = runNumericalPropagatorlocal(mi);
+		SpacecraftState obj = runNumericalPropagatorlocal(mi);
 
-		//System.out.println(((double[]) obj[1])[0]);
+		// System.out.println(((double[]) obj[1])[0]);
 	}
 
 }

OrekitJava/test/de/netsat/orekit/matlab/Maneuvers.java

@@ -69,7 +69,7 @@ public SpacecraftState resetState(final ApsideDetector detector, final Spacecraf
 
     }
 
-	private static class matlabPushStepHandler implements OrekitFixedStepHandler {
+	public static class matlabPushStepHandler implements OrekitFixedStepHandler {
 		MatlabInterface mi;
 		Vector3D[] position_history;