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2015JAT/JAT/src/jat/application/DE405Propagator/DE405PropagatorPlot.java
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/* JAT: Java Astrodynamics Toolkit | |
* | |
Copyright 2012 Tobias Berthold | |
Licensed 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 jat.application.DE405Propagator; | |
import jat.core.astronomy.SolarSystemBodies; | |
import jat.core.ephemeris.DE405Body.body; | |
import jat.core.ephemeris.DE405Plus; | |
import jat.core.ephemeris.EphemerisPlotData; | |
import jat.core.plot.plot.Plot3DPanel; | |
import jat.core.plot.plot.PlotPanel; | |
import jat.core.plot.plot.plots.LinePlot; | |
import jat.coreNOSA.math.MatrixVector.data.VectorN; | |
import java.awt.Color; | |
import java.io.IOException; | |
import java.util.ArrayList; | |
import javax.swing.JPanel; | |
import org.apache.commons.lang3.ArrayUtils; | |
import org.apache.commons.math3.ode.FirstOrderDifferentialEquations; | |
import org.apache.commons.math3.ode.FirstOrderIntegrator; | |
import org.apache.commons.math3.ode.nonstiff.DormandPrince853Integrator; | |
public class DE405PropagatorPlot extends JPanel { | |
private static final long serialVersionUID = 4814672707864836820L; | |
Plot3DPanel plot; | |
int steps = 200; | |
double[][] XYZ = new double[steps][3]; | |
double[][] points = new double[1][3]; | |
int step; | |
DE405PropagatorMain dpMain; | |
DE405Plus Eph; | |
static boolean print = false; | |
double plotBounds; | |
SolarSystemBodies sb = new SolarSystemBodies(); | |
public DE405PropagatorPlot(DE405PropagatorMain dpMain) { | |
this.dpMain = dpMain; | |
this.Eph = dpMain.dpGlobals.Eph; | |
} | |
public void make_plot() { | |
// create your PlotPanel (you can use it as a JPanel) with a legend at | |
// SOUTH | |
plot = new Plot3DPanel("SOUTH"); | |
// add grid plot to the PlotPanel | |
add_scene(); | |
} | |
public void add_scene() { | |
// Update Ephemeris to current user parameters | |
for (body b : body.values()) { | |
Eph.bodyGravOnOff[b.ordinal()] = dpMain.dpParam.bodyGravOnOff[b.ordinal()]; | |
} | |
Eph.setIntegrationStartTime(dpMain.dpParam.simulationDate); | |
try { | |
Eph.setEarthMoonPlaneNormal(dpMain.dpParam.simulationDate); | |
} catch (IOException e1) { | |
e1.printStackTrace(); | |
} | |
Eph.setFrame(dpMain.dpParam.Frame); | |
Eph.reset(); | |
// Spacecraft Trajectory | |
FirstOrderIntegrator dp853 = new DormandPrince853Integrator(1.0e-8, dpMain.dpParam.tf, 1.0e-10, 1.0e-10); | |
dp853.addStepHandler(Eph.stepHandler); | |
FirstOrderDifferentialEquations ode = Eph; | |
double[] y = new double[6]; | |
dp853.integrate(ode, 0.0, dpMain.dpParam.y0, dpMain.dpParam.tf, y); | |
if (print) { | |
String nf = "%10.3f "; | |
String format = nf + nf + nf + nf + nf; | |
System.out.printf(format, dpMain.dpParam.tf, y[0], y[1], y[2], Eph.energy(dpMain.dpParam.tf, y)); | |
System.out.println(); | |
} | |
LinePlot l1 = new LinePlot("spacecraft", Color.RED, getXYZforPlot(Eph.xsol, Eph.ysol, Eph.zsol)); | |
l1.closed_curve = false; | |
plot.addPlot(l1); | |
addBodies(); | |
// Vector3D y0v=new Vector3D(dpParam.y0[0],dpParam.y0[1],dpParam.y0[2]); | |
// double plotBounds = 2*y0v.getNorm(); | |
plot.setFixedBounds(0, -plotBounds, plotBounds); | |
plot.setFixedBounds(1, -plotBounds, plotBounds); | |
plot.setFixedBounds(2, -plotBounds, plotBounds); | |
plot.setLegendOrientation(PlotPanel.SOUTH); | |
} | |
void addBodies() { | |
int bodyNumber; | |
// int x, y, z; | |
VectorN BodyPos; | |
EphemerisPlotData epd; | |
LinePlot l; | |
// central body gets as sphere | |
switch (Eph.ephFrame) { | |
case ICRF: | |
plot.addSpherePlot("Sun", java.awt.Color.ORANGE, sb.Bodies[body.SUN.ordinal()].radius); | |
break; | |
case HEE: | |
plot.addSpherePlot("Sun", java.awt.Color.ORANGE, sb.Bodies[body.SUN.ordinal()].radius); | |
break; | |
case ECI: | |
plot.addSpherePlot("Earth", java.awt.Color.BLUE, sb.Bodies[body.EARTH.ordinal()].radius); | |
break; | |
case MEOP: | |
plot.addSpherePlot("Earth", java.awt.Color.BLUE, sb.Bodies[body.EARTH.ordinal()].radius); | |
break; | |
default: | |
break; | |
} | |
// other bodies get a point | |
for (body b : body.values()) { | |
bodyNumber = b.ordinal(); | |
if (Eph.bodyGravOnOff[bodyNumber] == true) { | |
try { | |
BodyPos = Eph.get_planet_pos(b, dpMain.dpParam.simulationDate); | |
addPoint(plot, body.name[bodyNumber], sb.Bodies[bodyNumber].color, BodyPos.x[0], BodyPos.x[1], | |
BodyPos.x[2]); | |
epd = new EphemerisPlotData(Eph, b, dpMain.dpParam.simulationDate, dpMain.dpParam.tf, 100); | |
l = new LinePlot(body.name[bodyNumber], sb.Bodies[bodyNumber].color, epd.XYZ); | |
l.closed_curve = false; | |
plot.addPlot(l); | |
} catch (IOException e) { | |
e.printStackTrace(); | |
} | |
} | |
} | |
// VectorN EarthPos = null; | |
// VectorN MoonPost0 = null; | |
// VectorN MoonPostf = null; | |
// VectorN SunPos = null; | |
// try { | |
// SunPos = Eph.get_planet_pos(body.SUN, dpMain.dpParam.simulationDate); | |
// EarthPos = Eph.get_planet_pos(body.EARTH, | |
// dpMain.dpParam.simulationDate); | |
// MoonPost0 = Eph.get_planet_pos(body.MOON, | |
// dpMain.dpParam.simulationDate); | |
// MoonPostf = Eph.get_planet_pos(body.MOON, | |
// dpMain.dpParam.simulationDate.plus(dpMain.dpParam.tf)); | |
// } catch (IOException e) { | |
// e.printStackTrace(); | |
// } | |
// addPoint(plot, "Sun", java.awt.Color.ORANGE, SunPos.x[0], | |
// SunPos.x[1], SunPos.x[2]); | |
// addPoint(plot, "Moon t0", java.awt.Color.GRAY, MoonPost0.x[0], | |
// MoonPost0.x[1], MoonPost0.x[2]); | |
// addPoint(plot, "Moon tf", java.awt.Color.GRAY, MoonPostf.x[0], | |
// MoonPostf.x[1], MoonPostf.x[2]); | |
// addPoint(plot, "Earth", java.awt.Color.MAGENTA, EarthPos.x[0], | |
// EarthPos.x[1], EarthPos.x[2]); | |
// EphemerisPlotData epd = new EphemerisPlotData(Eph, body.MOON, dpMain.dpParam.simulationDate, dpMain.dpParam.tf, | |
// 100); | |
// LinePlot lMoon = new LinePlot("Moon", Color.green, epd.XYZ); | |
// lMoon.closed_curve = false; | |
// plot.addPlot(lMoon); | |
} | |
double[][] getXYZforPlot(ArrayList<Double> xsol, ArrayList<Double> ysol, ArrayList<Double> zsol) { | |
int arraySize = xsol.size(); | |
double[] xsolArray = ArrayUtils.toPrimitive(xsol.toArray(new Double[arraySize])); | |
double[] ysolArray = ArrayUtils.toPrimitive(ysol.toArray(new Double[arraySize])); | |
double[] zsolArray = ArrayUtils.toPrimitive(zsol.toArray(new Double[arraySize])); | |
double[][] XYZ = new double[arraySize][3]; | |
plotBounds = 0.; | |
for (int i = 0; i < arraySize; i++) { | |
XYZ[i][0] = xsolArray[i]; | |
XYZ[i][1] = ysolArray[i]; | |
XYZ[i][2] = zsolArray[i]; | |
plotBounds = Math.max(plotBounds, Math.abs(XYZ[i][0])); | |
plotBounds = Math.max(plotBounds, Math.abs(XYZ[i][1])); | |
plotBounds = Math.max(plotBounds, Math.abs(XYZ[i][2])); | |
} | |
plotBounds /= 1.5; | |
return XYZ; | |
} | |
void addPoint(Plot3DPanel p, String s, Color c, double x, double y, double z) { | |
double[][] points = new double[1][3]; | |
points[0][0] = x; | |
points[0][1] = y; | |
points[0][2] = z; | |
p.addScatterPlot(s, c, points); | |
} | |
} | |
// VectorN v = Eph.EarthMoonPlaneNormal.times(100000); | |
// addPoint(plot, "Moon-Earth normal", java.awt.Color.pink, v.x[0], | |
// v.x[1], v.x[2]); | |
// | |
// VectorN vr = Eph.rotationAxis.times(100000); | |
// addPoint(plot, "rot axis", java.awt.Color.MAGENTA, vr.x[0], vr.x[1], | |
// vr.x[2]); |