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Costa-Dyakiw/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java
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package jat.examples.ThreeBodyExample; | |
import jat.core.cm.TwoBodyAPL; | |
import jat.core.plot.plot.FrameView; | |
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; | |
import javax.swing.JFrame; | |
import org.apache.commons.lang3.ArrayUtils; | |
import org.apache.commons.math3.linear.ArrayRealVector; | |
import org.apache.commons.math3.linear.RealVectorFormat; | |
import org.apache.commons.math3.ode.FirstOrderIntegrator; | |
import org.apache.commons.math3.ode.nonstiff.DormandPrince853Integrator; | |
/* | |
* We modified the ThreeBodyProblem by emulating the two body problem, and expanding it to ThreeBody | |
* Elements of two body, such as the orbit calculations, were not as heavily focused on | |
* We acknowledge that some of our calculations may be a bit inaccurate because some of the math got a bit over our heads | |
* | |
* @author Maegan and John | |
*/ | |
public class ThreeBodyExample { | |
public ThreeBodyExample() { | |
} | |
public static void main(String[] args) { | |
// Class that solves a three body problem and plots it | |
ThreeBodyExample x = new ThreeBodyExample(); | |
//initialize variables | |
double totalEnergy = 0; | |
// set the final time = one orbit period | |
double tf = 1.0; | |
// create a ThreeBody orbit using three masses and gravitational con | |
ThreeBodyAPL sat = new ThreeBodyAPL(9.87, 0.3, 1.0, 2.0); | |
//initialize VectorN elements | |
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(tf, y); | |
// set the initial time to zero | |
double t0 = 0.0; | |
// obtain center of mass | |
VectorN cm = sat.center_of_mass(y); | |
// obtain current energy | |
totalEnergy = sat.Energy(y); | |
/* | |
* Notes about the calculations: | |
* Dormand Prince is a type of Runge-Kutta diff eq. (another method of checking diff eq) | |
* Errors are calculated looking at 4th and 5th level differential equations | |
* These were most likely chosen by the original creator of the project because they take the error into account fairly accurately | |
* In relation to physics, this calculates the relative orbits for the bodies | |
* The step handler is another type of analyzing the algorithms for each body | |
* These provide fairly accurate results | |
* | |
* In general, these equations went over our heads, but refer to the NASA site as well as | |
* look into other resources to get more information on 3-Body calculations | |
* | |
*/ | |
// 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); | |
// test outputs | |
// output derivatives | |
for (int i = 0; i< derivs.length; i++) | |
{ | |
System.out.println(derivs[i]); | |
} | |
// output center of mass | |
System.out.println(cm); | |
// output total energy of the system | |
System.out.println(totalEnergy); | |
new FrameView(p).setDefaultCloseOperation(JFrame.EXIT_ON_CLOSE); | |
System.out.println("end"); | |
} | |
} |