Examples with DateComponents org.orekit.time.DateComponents used on opensource projects

Example 66 with DateComponents

use of org.orekit.time.DateComponents in project Orekit by CS-SI.

the class FixedRateTest method doTestNonZeroRate.

private <T extends RealFieldElement<T>> void doTestNonZeroRate(final Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 3, 2), new TimeComponents(13, 17, 7.865), TimeScalesFactory.getUTC());
    final T rate = zero.add(2 * FastMath.PI / (12 * 60));
    final Frame frame = FramesFactory.getEME2000();
    FixedRate law = new FixedRate(new Attitude(date.toAbsoluteDate(), frame, new Rotation(0.48, 0.64, 0.36, 0.48, false), new Vector3D(rate.getReal(), Vector3D.PLUS_K), Vector3D.ZERO));
    FieldPVCoordinates<T> pv = new FieldPVCoordinates<>(field.getOne(), new PVCoordinates(new Vector3D(28812595.32012577, 5948437.4640250085, 0), new Vector3D(0, 0, 3680.853673522056)));
    FieldOrbit<T> orbit = new FieldKeplerianOrbit<>(pv, FramesFactory.getEME2000(), date, 3.986004415e14);
    FieldRotation<T> attitude0 = law.getAttitude(orbit, date, frame).getRotation();
    Assert.assertEquals(0, Rotation.distance(attitude0.toRotation(), law.getReferenceAttitude().getRotation()), 1.0e-10);
    FieldRotation<T> attitude1 = law.getAttitude(orbit.shiftedBy(zero.add(10.0)), date.shiftedBy(10.0), frame).getRotation();
    Assert.assertEquals(10 * rate.getReal(), Rotation.distance(attitude1.toRotation(), law.getReferenceAttitude().getRotation()), 1.0e-10);
    FieldRotation<T> attitude2 = law.getAttitude(orbit.shiftedBy(zero.add(-20.0)), date.shiftedBy(-20.0), frame).getRotation();
    Assert.assertEquals(20 * rate.getReal(), Rotation.distance(attitude2.toRotation(), law.getReferenceAttitude().getRotation()), 1.0e-10);
    Assert.assertEquals(30 * rate.getReal(), Rotation.distance(attitude2.toRotation(), attitude1.toRotation()), 1.0e-10);
    FieldRotation<T> attitude3 = law.getAttitude(orbit.shiftedBy(zero.add(0.0)), date, frame).getRotation();
    Assert.assertEquals(0, Rotation.distance(attitude3.toRotation(), law.getReferenceAttitude().getRotation()), 1.0e-10);
}

Example 67 with DateComponents

use of org.orekit.time.DateComponents in project Orekit by CS-SI.

the class FixedRateTest method doTestZeroRate.

private <T extends RealFieldElement<T>> void doTestZeroRate(final Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 3, 2), new TimeComponents(13, 17, 7.865), TimeScalesFactory.getUTC());
    final Frame frame = FramesFactory.getEME2000();
    FixedRate law = new FixedRate(new Attitude(date.toAbsoluteDate(), frame, new Rotation(0.48, 0.64, 0.36, 0.48, false), Vector3D.ZERO, Vector3D.ZERO));
    FieldPVCoordinates<T> pv = new FieldPVCoordinates<>(field.getOne(), new PVCoordinates(new Vector3D(28812595.32012577, 5948437.4640250085, 0), new Vector3D(0, 0, 3680.853673522056)));
    FieldOrbit<T> orbit = new FieldKeplerianOrbit<>(pv, frame, date, 3.986004415e14);
    FieldRotation<T> attitude0 = law.getAttitude(orbit, date, frame).getRotation();
    Assert.assertEquals(0, Rotation.distance(attitude0.toRotation(), law.getReferenceAttitude().getRotation()), 1.0e-10);
    FieldRotation<T> attitude1 = law.getAttitude(orbit.shiftedBy(zero.add(10.0)), date.shiftedBy(10.0), frame).getRotation();
    Assert.assertEquals(0, Rotation.distance(attitude1.toRotation(), law.getReferenceAttitude().getRotation()), 1.0e-10);
    FieldRotation<T> attitude2 = law.getAttitude(orbit.shiftedBy(zero.add(20.0)), date.shiftedBy(20.0), frame).getRotation();
    Assert.assertEquals(0, Rotation.distance(attitude2.toRotation(), law.getReferenceAttitude().getRotation()), 1.0e-10);
}

Example 68 with DateComponents

use of org.orekit.time.DateComponents in project Orekit by CS-SI.

the class FixedRateTest method doTestSpin.

private <T extends RealFieldElement<T>> void doTestSpin(final Field<T> field) throws OrekitException {
    final T zero = field.getZero();
    FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(1970, 01, 01), new TimeComponents(3, 25, 45.6789), TimeScalesFactory.getUTC());
    final T rate = zero.add(2 * FastMath.PI / (12 * 60));
    AttitudeProvider law = new FixedRate(new Attitude(date.toAbsoluteDate(), FramesFactory.getEME2000(), new Rotation(0.48, 0.64, 0.36, 0.48, false), new Vector3D(rate.getReal(), Vector3D.PLUS_K), Vector3D.ZERO));
    FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(zero.add(7178000.0), zero.add(1.e-4), zero.add(FastMath.toRadians(50.)), zero.add(FastMath.toRadians(10.)), zero.add(FastMath.toRadians(20.)), zero.add(FastMath.toRadians(30.)), PositionAngle.MEAN, FramesFactory.getEME2000(), date, 3.986004415e14);
    FieldPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit, law);
    T h = zero.add(0.01);
    FieldSpacecraftState<T> sMinus = propagator.propagate(date.shiftedBy(h.negate()));
    FieldSpacecraftState<T> s0 = propagator.propagate(date);
    FieldSpacecraftState<T> sPlus = propagator.propagate(date.shiftedBy(h));
    // check spin is consistent with attitude evolution
    double errorAngleMinus = FieldRotation.distance(sMinus.shiftedBy(h).getAttitude().getRotation(), s0.getAttitude().getRotation()).getReal();
    double evolutionAngleMinus = FieldRotation.distance(sMinus.getAttitude().getRotation(), s0.getAttitude().getRotation()).getReal();
    Assert.assertEquals(0.0, errorAngleMinus, 1.0e-6 * evolutionAngleMinus);
    double errorAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.shiftedBy(h.negate()).getAttitude().getRotation()).getReal();
    double evolutionAnglePlus = FieldRotation.distance(s0.getAttitude().getRotation(), sPlus.getAttitude().getRotation()).getReal();
    Assert.assertEquals(0.0, errorAnglePlus, 1.0e-6 * evolutionAnglePlus);
    FieldVector3D<T> spin0 = s0.getAttitude().getSpin();
    FieldVector3D<T> reference = FieldAngularCoordinates.estimateRate(sMinus.getAttitude().getRotation(), sPlus.getAttitude().getRotation(), h.multiply(2));
    Assert.assertEquals(0.0, spin0.subtract(reference).getNorm().getReal(), 1.0e-14);
}

Example 69 with DateComponents

use of org.orekit.time.DateComponents in project SpriteOrbits by ProjectPersephone.

the class SpriteProp method main.

/**
 * @param args
 */
public static void main(String[] args) {
    PrintStream out = null;
    try {
        // set up orekit data
        // for this to work, the orekit-data.zip file avaiable at the following URL
        // must be put in the current working directory
        // URL:     https://www.orekit.org/forge/projects/orekit/files
        File userDir = new File(System.getProperty("user.dir"));
        File orekitZip = new File(userDir, "orekit-data.zip");
        DataProvidersManager.getInstance().addProvider(new ZipJarCrawler(orekitZip));
        // reference models
        // this is the frame labeled J2K in the NASA page
        final Frame eme2000 = FramesFactory.getEME2000();
        final Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
        final TimeScale utc = TimeScalesFactory.getUTC();
        // central attraction coefficient MU
        final double mu = Constants.EIGEN5C_EARTH_MU;
        // set up some data, ideally, this should be provided as input to the program
        // ISS orbit is from http://spaceflight.nasa.gov/realdata/sightings/SSapplications/Post/JavaSSOP/orbit/ISS/SVPOST.html
        // 
        // Coasting Arc #15 (Orbit 3386)
        // ---------------------------------------
        // 
        // Vector Time (GMT): 2014/055/16:27:06.921
        // Vector Time (MET): N/A
        // Weight (LBS)     : 911651.1
        // 
        // ...
        // 
        // J2K Cartesian
        // --------------------------------
        // X    =         2998767.75
        // Y    =        -6097451.56  meter
        // ...              Z    =         -141448.92
        // XDOT =        4323.077242
        // YDOT =        1994.291706  meter/sec
        // ZDOT =        6000.774574
        // we start small, we can increase this later
        final int numberOfSprites = 12;
        // (m/s)
        final double relativeReleaseVelocity = 1.0;
        final AbsoluteDate releaseDate = new // year, month, day
        AbsoluteDate(// year, month, day
        2014, // year, month, day
        3, // year, month, day
        1, // hours, minutes, seconds
        12, // hours, minutes, seconds
        0, // hours, minutes, seconds
        0.0, utc);
        final CartesianOrbit kickSatOrbit = new CartesianOrbit(new // position (m)
        PVCoordinates(// position (m)
        new Vector3D(2998767.75, -6097451.56, -141448.92), // velocity (m/s)
        new Vector3D(4323.077242, 1994.291706, 6000.774574)), eme2000, new // year, day in year as NASA page above
        AbsoluteDate(// year, day in year as NASA page above
        new DateComponents(2014, 55), // hour in day
        new TimeComponents(16, 27, 6.921), utc), mu);
        // kg
        final double kickSatMass = 10.0;
        // m^2
        final double kickSatCrossSection = 0.03;
        // no units
        final double kickSatDragCoeff = 2.2;
        // kg
        final double spriteMass = 0.01;
        // m^2
        final double spriteCrossSection = 2.5e-3;
        // no units
        final double spriteDragCoeff = 2.2;
        SpriteProp spriteProp = new SpriteProp(numberOfSprites, kickSatOrbit, kickSatMass, kickSatCrossSection, kickSatDragCoeff, spriteMass, spriteCrossSection, spriteDragCoeff, relativeReleaseVelocity, releaseDate, itrf);
        // days after release
        final double propagationDuration = 0.2;
        // seconds
        final double step = 60.0;
        // out = new PrintStream(new File(userDir, "sprites-prop.txt"));
        out = new PrintStream(new File(userDir, "orbits.json"));
        out.format(Locale.US, "[");
        spriteProp.run(out, propagationDuration, step, utc);
        out.format(Locale.US, "]");
    } catch (IOException e) {
        e.printStackTrace();
    } catch (IllegalArgumentException e) {
        e.printStackTrace();
    } catch (OrekitException e) {
        e.printStackTrace();
    } finally {
        if (out != null) {
            out.close();
        }
    }
}

Example 70 with DateComponents

use of org.orekit.time.DateComponents in project SpriteOrbits by ProjectPersephone.

the class SpritePropOrig method main.

/**
 * @param args
 */
public static void main(String[] args) {
    PrintStream out = null;
    try {
        // set up orekit data
        // for this to work, the orekit-data.zip file avaiable at the following URL
        // must be put in the current working directory
        // URL:     https://www.orekit.org/forge/projects/orekit/files
        File userDir = new File(System.getProperty("user.dir"));
        File orekitZip = new File(userDir, "orekit-data.zip");
        DataProvidersManager.getInstance().addProvider(new ZipJarCrawler(orekitZip));
        // reference models
        // this is the frame labeled J2K in the NASA page
        final Frame eme2000 = FramesFactory.getEME2000();
        final Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
        final TimeScale utc = TimeScalesFactory.getUTC();
        // central attraction coefficient MU
        final double mu = Constants.EIGEN5C_EARTH_MU;
        // set up some data, ideally, this should be provided as input to the program
        // ISS orbit is from http://spaceflight.nasa.gov/realdata/sightings/SSapplications/Post/JavaSSOP/orbit/ISS/SVPOST.html
        // 
        // Coasting Arc #15 (Orbit 3386)
        // ---------------------------------------
        // 
        // Vector Time (GMT): 2014/055/16:27:06.921
        // Vector Time (MET): N/A
        // Weight (LBS)     : 911651.1
        // 
        // ...
        // 
        // J2K Cartesian
        // --------------------------------
        // X    =         2998767.75
        // Y    =        -6097451.56  meter
        // ...              Z    =         -141448.92
        // XDOT =        4323.077242
        // YDOT =        1994.291706  meter/sec
        // ZDOT =        6000.774574
        // we start small, we can increase this later
        final int numberOfSprites = 12;
        // (m/s)
        final double relativeReleaseVelocity = 1.0;
        final AbsoluteDate releaseDate = new // year, month, day
        AbsoluteDate(// year, month, day
        2014, // year, month, day
        3, // year, month, day
        1, // hours, minutes, seconds
        12, // hours, minutes, seconds
        0, // hours, minutes, seconds
        0.0, utc);
        final CartesianOrbit kickSatOrbit = new CartesianOrbit(new // position (m)
        PVCoordinates(// position (m)
        new Vector3D(2998767.75, -6097451.56, -141448.92), // velocity (m/s)
        new Vector3D(4323.077242, 1994.291706, 6000.774574)), eme2000, new // year, day in year as NASA page above
        AbsoluteDate(// year, day in year as NASA page above
        new DateComponents(2014, 55), // hour in day
        new TimeComponents(16, 27, 6.921), utc), mu);
        // kg
        final double kickSatMass = 10.0;
        // m^2
        final double kickSatCrossSection = 0.03;
        // no units
        final double kickSatDragCoeff = 2.2;
        // kg
        final double spriteMass = 0.01;
        // m^2
        final double spriteCrossSection = 2.5e-3;
        // no units
        final double spriteDragCoeff = 2.2;
        SpritePropOrig spriteProp = new SpritePropOrig(numberOfSprites, kickSatOrbit, kickSatMass, kickSatCrossSection, kickSatDragCoeff, spriteMass, spriteCrossSection, spriteDragCoeff, relativeReleaseVelocity, releaseDate, itrf);
        // days after release
        final double propagationDuration = 0.2;
        // seconds
        final double step = 60.0;
        out = new PrintStream(new File(userDir, "sprites-prop.txt"));
        spriteProp.run(out, propagationDuration, step, utc);
    } catch (IOException e) {
        e.printStackTrace();
    } catch (IllegalArgumentException e) {
        e.printStackTrace();
    } catch (OrekitException e) {
        e.printStackTrace();
    } finally {
        if (out != null) {
            out.close();
        }
    }
}