diff --git a/src/jat/examples/ThreeBodyExample/ThreeBodyAPL.java b/src/jat/examples/ThreeBodyExample/ThreeBodyAPL.java
index 28104e0..f3265db 100644
--- a/src/jat/examples/ThreeBodyExample/ThreeBodyAPL.java
+++ b/src/jat/examples/ThreeBodyExample/ThreeBodyAPL.java
@@ -1,14 +1,22 @@
 package jat.examples.ThreeBodyExample;
 
+import java.util.ArrayList;
+
 import org.apache.commons.math3.ode.FirstOrderDifferentialEquations;
 
 import jat.coreNOSA.cm.ThreeBody;
 import jat.coreNOSA.math.MatrixVector.data.VectorN;
 
 public class ThreeBodyAPL extends ThreeBody implements FirstOrderDifferentialEquations{
+	double initial_ta;
+	public ArrayList<Double> time = new ArrayList<Double>();
+	public ArrayList<Double> xsol = new ArrayList<Double>();
+	public ArrayList<Double> ysol = new ArrayList<Double>();
+	public ArrayList<Double> zsol = new ArrayList<Double>();
 
-	public ThreeBodyAPL(double G, double m1, double m2, double m3) {
-		super(G, m1, m2, m3);
+	public ThreeBodyAPL(double mu, VectorN r, VectorN v) {
+		super(mu, r, v);
+		initial_ta = ta;
 	}
 
 	@Override
diff --git a/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java b/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java
index 485a326..339acb3 100644
--- a/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java
+++ b/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java
@@ -5,8 +5,6 @@
 import jat.core.plot.plot.Plot2DPanel;
 import jat.core.plot.plot.PlotPanel;
 import jat.core.plot.plot.plots.ScatterPlot;
-import jat.coreNOSA.math.MatrixVector.data.VectorN;
-import jat.examples.TwoBodyExample.TwoBodyExample;
 
 import java.awt.Color;
 import java.text.DecimalFormat;
@@ -20,29 +18,30 @@
 import org.apache.commons.math3.ode.nonstiff.DormandPrince853Integrator;
 
 public class ThreeBodyExample {
+
 	public ThreeBodyExample() {
 	}
-	
+
 	public static void main(String[] args) {
-		// TODO Auto-generated method stub
+
 		ThreeBodyExample x = new ThreeBodyExample();
 
-		// create a ThreeBody orbit using three masses and gravitational con
-		ThreeBodyAPL sat = new ThreeBodyAPL(10, 0.3, 1.0, 2.0);
-		//initialize VectorN elements
+		// create a TwoBody orbit using orbit elements
+		ThreeBodyAPL sat = new ThreeBodyAPL(7000.0, 0.3, 0.0, 0.0, 0.0, 0.0);
+
 		double[] y = sat.randv();
-		
+
 		ArrayRealVector v = new ArrayRealVector(y);
 
 		DecimalFormat df2 = new DecimalFormat("#,###,###,##0.00");
 		RealVectorFormat format = new RealVectorFormat(df2);
 		System.out.println(format.format(v));
 
-		// find out the derivs of the problem
-		double[] derivs = sat.derivs(2.0, y);
+		// find out the period of the orbit
+		double period = sat.period();
 
 		// set the final time = one orbit period
-		double tf = 2.0;
+		double tf = period;
 
 		// set the initial time to zero
 		double t0 = 0.0;
@@ -92,5 +91,4 @@ public static void main(String[] args) {
 		System.out.println("end");
 
 	}
-
 }