From 18f63b34a5a7176048b01c6bc31257749b8e9e9c Mon Sep 17 00:00:00 2001
From: jic13003 <jic13003@ITESTA09.ad.engr.uconn.edu>
Date: Fri, 4 Dec 2015 18:19:12 -0500
Subject: [PATCH] test for branching

---
 .../ThreeBodyExample/ThreeBodyExample.java    | 60 +++----------------
 1 file changed, 8 insertions(+), 52 deletions(-)

diff --git a/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java b/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java
index 485a326..683506c 100644
--- a/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java
+++ b/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java
@@ -24,9 +24,12 @@ public ThreeBodyExample() {
 	}
 	
 	public static void main(String[] args) {
-		// TODO Auto-generated method stub
+		// Class that solves a three body problem and plots it
 		ThreeBodyExample x = new ThreeBodyExample();
-
+		
+		// set the final time = one orbit period
+		double tf = 2.0;
+		
 		// create a ThreeBody orbit using three masses and gravitational con
 		ThreeBodyAPL sat = new ThreeBodyAPL(10, 0.3, 1.0, 2.0);
 		//initialize VectorN elements
@@ -39,58 +42,11 @@ public static void main(String[] args) {
 		System.out.println(format.format(v));
 
 		// find out the derivs of the problem
-		double[] derivs = sat.derivs(2.0, y);
-
-		// set the final time = one orbit period
-		double tf = 2.0;
-
+		double[] derivs = sat.derivs(tf, y);
+		
 		// set the initial time to zero
 		double t0 = 0.0;
-
-		// propagate the orbit
-		FirstOrderIntegrator dp853 = new DormandPrince853Integrator(1.0e-8, 100.0, 1.0e-10, 1.0e-10);
-		dp853.addStepHandler(sat.stepHandler);
-		// double[] y = new double[] { 7000.0, 0, 0, .0, 8, 0 }; // initial
-		// state
-
-		dp853.integrate(sat, 0.0, y, 8000, y); // now y contains final state at
-												// tf
-
-		Double[] objArray = sat.time.toArray(new Double[sat.time.size()]);
-		double[] timeArray = ArrayUtils.toPrimitive(objArray);
-		double[] xsolArray = ArrayUtils.toPrimitive(sat.xsol.toArray(new Double[sat.time.size()]));
-		double[] ysolArray = ArrayUtils.toPrimitive(sat.ysol.toArray(new Double[sat.time.size()]));
-
-		double[][] XY = new double[timeArray.length][2];
-
-		// int a=0;
-		// System.arraycopy(timeArray,0,XY[a],0,timeArray.length);
-		// System.arraycopy(ysolArray,0,XY[1],0,ysolArray.length);
-
-		for (int i = 0; i < timeArray.length; i++) {
-			XY[i][0] = xsolArray[i];
-			XY[i][1] = ysolArray[i];
-		}
-
-		Plot2DPanel p = new Plot2DPanel();
-
-		// Plot2DPanel p = new Plot2DPanel(min, max, axesScales, axesLabels);
-
-		ScatterPlot s = new ScatterPlot("orbit", Color.RED, XY);
-		// LinePlot l = new LinePlot("sin", Color.RED, XY);
-		// l.closed_curve = false;
-		// l.draw_dot = true;
-		p.addPlot(s);
-		p.setLegendOrientation(PlotPanel.SOUTH);
-		double plotSize = 10000.;
-		double[] min = { -plotSize, -plotSize };
-		double[] max = { plotSize, plotSize };
-		p.setFixedBounds(min, max);
-
-		new FrameView(p).setDefaultCloseOperation(JFrame.EXIT_ON_CLOSE);
-
-		System.out.println("end");
-
+		
 	}
 
 }