use of org.orekit.frames.Frame 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();
}
}
}
use of org.orekit.frames.Frame 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();
}
}
}
use of org.orekit.frames.Frame in project Orekit by CS-SI.
the class BoxAndSolarArraySpacecraftTest method testLiftVsNoLift.
@Test
public void testLiftVsNoLift() throws OrekitException, NoSuchFieldException, SecurityException, IllegalArgumentException, IllegalAccessException {
CelestialBody sun = CelestialBodyFactory.getSun();
// older implementation did not consider lift, so it really worked
// only for symmetrical shapes. For testing purposes, we will use a
// basic cubic shape without solar arrays and a relative atmosphere
// velocity either *exactly* facing a side or *exactly* along a main diagonal
BoxAndSolarArraySpacecraft.Facet[] facets = new BoxAndSolarArraySpacecraft.Facet[] { new BoxAndSolarArraySpacecraft.Facet(Vector3D.MINUS_I, 3.0), new BoxAndSolarArraySpacecraft.Facet(Vector3D.PLUS_I, 3.0), new BoxAndSolarArraySpacecraft.Facet(Vector3D.MINUS_J, 3.0), new BoxAndSolarArraySpacecraft.Facet(Vector3D.PLUS_J, 3.0), new BoxAndSolarArraySpacecraft.Facet(Vector3D.MINUS_K, 3.0), new BoxAndSolarArraySpacecraft.Facet(Vector3D.PLUS_K, 3.0) };
BoxAndSolarArraySpacecraft cube = new BoxAndSolarArraySpacecraft(facets, sun, 0.0, Vector3D.PLUS_J, 1.0, 1.0, 1.0, 0.0);
AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
Frame frame = FramesFactory.getEME2000();
Vector3D position = new Vector3D(1234567.8, 9876543.21, 121212.3434);
double mass = 1000.0;
double density = 0.001;
Rotation rotation = Rotation.IDENTITY;
// head-on, there acceleration with lift should be twice acceleration without lift
Vector3D headOnVelocity = new Vector3D(2000, 0.0, 0.0);
Vector3D newHeadOnDrag = cube.dragAcceleration(date, frame, position, rotation, mass, density, headOnVelocity, getDragParameters(cube));
Vector3D oldHeadOnDrag = oldDragAcceleration(cube, date, frame, position, rotation, mass, density, headOnVelocity);
Assert.assertThat(newHeadOnDrag, OrekitMatchers.vectorCloseTo(oldHeadOnDrag.scalarMultiply(2), 1));
// on an angle, the no lift implementation applies drag to the velocity direction
// instead of to the facet normal direction. In the symmetrical case, this implies
// it applied a single cos(θ) coefficient (projected surface reduction) instead
// of using cos²(θ) (projected surface reduction *and* normal component projection)
// and since molecule is reflected backward with the same velocity, this implies a
// factor 2 in linear momentum differences
Vector3D diagonalVelocity = new Vector3D(2000, 2000, 2000);
Vector3D newDiagDrag = cube.dragAcceleration(date, frame, position, rotation, mass, density, diagonalVelocity, getDragParameters(cube));
Vector3D oldDiagDrag = oldDragAcceleration(cube, date, frame, position, rotation, mass, density, diagonalVelocity);
double oldMissingCoeff = 2.0 / FastMath.sqrt(3.0);
Vector3D fixedOldDrag = new Vector3D(oldMissingCoeff, oldDiagDrag);
Assert.assertThat(newDiagDrag, OrekitMatchers.vectorCloseTo(fixedOldDrag, 1));
}
use of org.orekit.frames.Frame in project Orekit by CS-SI.
the class DragForceTest method RealFieldExpectErrorTest.
/**
*Same test as the previous one but not adding the ForceModel to the NumericalPropagator
* it is a test to validate the previous test.
* (to test if the ForceModel it's actually
* doing something in the Propagator and the FieldPropagator)
*/
@Test
public void RealFieldExpectErrorTest() throws OrekitException {
DSFactory factory = new DSFactory(6, 5);
DerivativeStructure a_0 = factory.variable(0, 7e6);
DerivativeStructure e_0 = factory.variable(1, 0.01);
DerivativeStructure i_0 = factory.variable(2, 85 * FastMath.PI / 180);
DerivativeStructure R_0 = factory.variable(3, 0.7);
DerivativeStructure O_0 = factory.variable(4, 0.5);
DerivativeStructure n_0 = factory.variable(5, 0.1);
Field<DerivativeStructure> field = a_0.getField();
DerivativeStructure zero = field.getZero();
FieldAbsoluteDate<DerivativeStructure> J2000 = new FieldAbsoluteDate<>(field);
Frame EME = FramesFactory.getEME2000();
FieldKeplerianOrbit<DerivativeStructure> FKO = new FieldKeplerianOrbit<>(a_0, e_0, i_0, R_0, O_0, n_0, PositionAngle.MEAN, EME, J2000, Constants.EIGEN5C_EARTH_MU);
FieldSpacecraftState<DerivativeStructure> initialState = new FieldSpacecraftState<>(FKO);
SpacecraftState iSR = initialState.toSpacecraftState();
OrbitType type = OrbitType.KEPLERIAN;
double[][] tolerance = NumericalPropagator.tolerances(10.0, FKO.toOrbit(), type);
AdaptiveStepsizeFieldIntegrator<DerivativeStructure> integrator = new DormandPrince853FieldIntegrator<>(field, 0.001, 200, tolerance[0], tolerance[1]);
integrator.setInitialStepSize(zero.add(60));
AdaptiveStepsizeIntegrator RIntegrator = new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
RIntegrator.setInitialStepSize(60);
FieldNumericalPropagator<DerivativeStructure> FNP = new FieldNumericalPropagator<>(field, integrator);
FNP.setOrbitType(type);
FNP.setInitialState(initialState);
NumericalPropagator NP = new NumericalPropagator(RIntegrator);
NP.setOrbitType(type);
NP.setInitialState(iSR);
final DragForce forceModel = new DragForce(new HarrisPriester(CelestialBodyFactory.getSun(), new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true))), new BoxAndSolarArraySpacecraft(1.5, 2.0, 1.8, CelestialBodyFactory.getSun(), 20.0, Vector3D.PLUS_J, 1.2, 0.7, 0.2));
FNP.addForceModel(forceModel);
// NOT ADDING THE FORCE MODEL TO THE NUMERICAL PROPAGATOR NP.addForceModel(forceModel);
FieldAbsoluteDate<DerivativeStructure> target = J2000.shiftedBy(1000.);
FieldSpacecraftState<DerivativeStructure> finalState_DS = FNP.propagate(target);
SpacecraftState finalState_R = NP.propagate(target.toAbsoluteDate());
FieldPVCoordinates<DerivativeStructure> finPVC_DS = finalState_DS.getPVCoordinates();
PVCoordinates finPVC_R = finalState_R.getPVCoordinates();
Assert.assertFalse(FastMath.abs(finPVC_DS.toPVCoordinates().getPosition().getX() - finPVC_R.getPosition().getX()) < FastMath.abs(finPVC_R.getPosition().getX()) * 1e-11);
Assert.assertFalse(FastMath.abs(finPVC_DS.toPVCoordinates().getPosition().getY() - finPVC_R.getPosition().getY()) < FastMath.abs(finPVC_R.getPosition().getY()) * 1e-11);
Assert.assertFalse(FastMath.abs(finPVC_DS.toPVCoordinates().getPosition().getZ() - finPVC_R.getPosition().getZ()) < FastMath.abs(finPVC_R.getPosition().getZ()) * 1e-11);
}
use of org.orekit.frames.Frame in project Orekit by CS-SI.
the class DragForceTest method RealFieldTest.
/**
*Testing if the propagation between the FieldPropagation and the propagation
* is equivalent.
* Also testing if propagating X+dX with the propagation is equivalent to
* propagation X with the FieldPropagation and then applying the taylor
* expansion of dX to the result.
*/
@Test
public void RealFieldTest() throws OrekitException {
DSFactory factory = new DSFactory(6, 4);
DerivativeStructure a_0 = factory.variable(0, 7e6);
DerivativeStructure e_0 = factory.variable(1, 0.01);
DerivativeStructure i_0 = factory.variable(2, 1.2);
DerivativeStructure R_0 = factory.variable(3, 0.7);
DerivativeStructure O_0 = factory.variable(4, 0.5);
DerivativeStructure n_0 = factory.variable(5, 0.1);
Field<DerivativeStructure> field = a_0.getField();
DerivativeStructure zero = field.getZero();
FieldAbsoluteDate<DerivativeStructure> J2000 = new FieldAbsoluteDate<>(field);
Frame EME = FramesFactory.getEME2000();
FieldKeplerianOrbit<DerivativeStructure> FKO = new FieldKeplerianOrbit<>(a_0, e_0, i_0, R_0, O_0, n_0, PositionAngle.MEAN, EME, J2000, Constants.EIGEN5C_EARTH_MU);
FieldSpacecraftState<DerivativeStructure> initialState = new FieldSpacecraftState<>(FKO);
SpacecraftState iSR = initialState.toSpacecraftState();
ClassicalRungeKuttaFieldIntegrator<DerivativeStructure> integrator = new ClassicalRungeKuttaFieldIntegrator<>(field, zero.add(6));
ClassicalRungeKuttaIntegrator RIntegrator = new ClassicalRungeKuttaIntegrator(6);
OrbitType type = OrbitType.EQUINOCTIAL;
FieldNumericalPropagator<DerivativeStructure> FNP = new FieldNumericalPropagator<>(field, integrator);
FNP.setOrbitType(type);
FNP.setInitialState(initialState);
NumericalPropagator NP = new NumericalPropagator(RIntegrator);
NP.setOrbitType(type);
NP.setInitialState(iSR);
final DragForce forceModel = new DragForce(new HarrisPriester(CelestialBodyFactory.getSun(), new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true))), new BoxAndSolarArraySpacecraft(1.5, 2.0, 1.8, CelestialBodyFactory.getSun(), 20.0, Vector3D.PLUS_J, 1.2, 0.7, 0.2));
FNP.addForceModel(forceModel);
NP.addForceModel(forceModel);
FieldAbsoluteDate<DerivativeStructure> target = J2000.shiftedBy(1000.);
FieldSpacecraftState<DerivativeStructure> finalState_DS = FNP.propagate(target);
SpacecraftState finalState_R = NP.propagate(target.toAbsoluteDate());
FieldPVCoordinates<DerivativeStructure> finPVC_DS = finalState_DS.getPVCoordinates();
PVCoordinates finPVC_R = finalState_R.getPVCoordinates();
Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getX(), finPVC_R.getPosition().getX(), FastMath.abs(finPVC_R.getPosition().getX()) * 1e-11);
Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getY(), finPVC_R.getPosition().getY(), FastMath.abs(finPVC_R.getPosition().getY()) * 1e-11);
Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getZ(), finPVC_R.getPosition().getZ(), FastMath.abs(finPVC_R.getPosition().getZ()) * 1e-11);
long number = 23091991;
RandomGenerator RG = new Well19937a(number);
GaussianRandomGenerator NGG = new GaussianRandomGenerator(RG);
UncorrelatedRandomVectorGenerator URVG = new UncorrelatedRandomVectorGenerator(new double[] { 0.0, 0.0, 0.0, 0.0, 0.0, 0.0 }, new double[] { 1e3, 0.005, 0.005, 0.01, 0.01, 0.01 }, NGG);
double a_R = a_0.getReal();
double e_R = e_0.getReal();
double i_R = i_0.getReal();
double R_R = R_0.getReal();
double O_R = O_0.getReal();
double n_R = n_0.getReal();
for (int ii = 0; ii < 1; ii++) {
double[] rand_next = URVG.nextVector();
double a_shift = a_R + rand_next[0];
double e_shift = e_R + rand_next[1];
double i_shift = i_R + rand_next[2];
double R_shift = R_R + rand_next[3];
double O_shift = O_R + rand_next[4];
double n_shift = n_R + rand_next[5];
KeplerianOrbit shiftedOrb = new KeplerianOrbit(a_shift, e_shift, i_shift, R_shift, O_shift, n_shift, PositionAngle.MEAN, EME, J2000.toAbsoluteDate(), Constants.EIGEN5C_EARTH_MU);
SpacecraftState shift_iSR = new SpacecraftState(shiftedOrb);
NumericalPropagator shift_NP = new NumericalPropagator(RIntegrator);
shift_NP.setInitialState(shift_iSR);
shift_NP.addForceModel(forceModel);
SpacecraftState finalState_shift = shift_NP.propagate(target.toAbsoluteDate());
PVCoordinates finPVC_shift = finalState_shift.getPVCoordinates();
// position check
FieldVector3D<DerivativeStructure> pos_DS = finPVC_DS.getPosition();
double x_DS = pos_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
double y_DS = pos_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
double z_DS = pos_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
// System.out.println(pos_DS.getX().getPartialDerivative(1));
double x = finPVC_shift.getPosition().getX();
double y = finPVC_shift.getPosition().getY();
double z = finPVC_shift.getPosition().getZ();
Assert.assertEquals(x_DS, x, FastMath.abs(x - pos_DS.getX().getReal()) * 1e-5);
Assert.assertEquals(y_DS, y, FastMath.abs(y - pos_DS.getY().getReal()) * 1e-5);
Assert.assertEquals(z_DS, z, FastMath.abs(z - pos_DS.getZ().getReal()) * 1e-5);
// velocity check
FieldVector3D<DerivativeStructure> vel_DS = finPVC_DS.getVelocity();
double vx_DS = vel_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
double vy_DS = vel_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
double vz_DS = vel_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
double vx = finPVC_shift.getVelocity().getX();
double vy = finPVC_shift.getVelocity().getY();
double vz = finPVC_shift.getVelocity().getZ();
Assert.assertEquals(vx_DS, vx, FastMath.abs(vx) * 1e-7);
Assert.assertEquals(vy_DS, vy, FastMath.abs(vy) * 1e-7);
Assert.assertEquals(vz_DS, vz, FastMath.abs(vz) * 1e-7);
// acceleration check
FieldVector3D<DerivativeStructure> acc_DS = finPVC_DS.getAcceleration();
double ax_DS = acc_DS.getX().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
double ay_DS = acc_DS.getY().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
double az_DS = acc_DS.getZ().taylor(rand_next[0], rand_next[1], rand_next[2], rand_next[3], rand_next[4], rand_next[5]);
double ax = finPVC_shift.getAcceleration().getX();
double ay = finPVC_shift.getAcceleration().getY();
double az = finPVC_shift.getAcceleration().getZ();
Assert.assertEquals(ax_DS, ax, FastMath.abs(ax) * 1e-5);
Assert.assertEquals(ay_DS, ay, FastMath.abs(ay) * 1e-5);
Assert.assertEquals(az_DS, az, FastMath.abs(az) * 1e-5);
}
}
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