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Commit f255c874 authored by Luc Maisonobe's avatar Luc Maisonobe
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Added orbit normalization feature.

parent c558fd1a
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src/changes/changes.xml
View file @ f255c874
......@@ -21,6 +21,9 @@
</properties>
<body>
<release version="11.1" date="TBD" description="TBD">
<action dev="luc" type="add">
Added an orbit normalization feature.
</action>
<action dev="luc" type="fix" issue="849">
Added detector to FieldEventHandler.init arguments list.
</action>
......
src/main/java/org/orekit/orbits/OrbitType.java
View file @ f255c874
......@@ -22,6 +22,7 @@ import org.hipparchus.CalculusFieldElement;
import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.hipparchus.util.FastMath;
import org.hipparchus.util.MathUtils;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
import org.orekit.frames.Frame;
......@@ -166,6 +167,20 @@ public enum OrbitType {
return drivers;
}
/** {@inheritDoc} */
@Override
public CartesianOrbit normalize(final Orbit orbit, final Orbit reference) {
// no angular parameters need normalization
return convertType(orbit);
}
/** {@inheritDoc} */
@Override
public <T extends CalculusFieldElement<T>> FieldCartesianOrbit<T> normalize(final FieldOrbit<T> orbit, final FieldOrbit<T> reference) {
// no angular parameters need normalization
return convertType(orbit);
}
},
/** Type for propagation in {@link CircularOrbit circular parameters}. */
......@@ -302,6 +317,88 @@ public enum OrbitType {
return drivers;
}
/** {@inheritDoc} */
@Override
public CircularOrbit normalize(final Orbit orbit, final Orbit reference) {
// convert input to proper type
final CircularOrbit cO = convertType(orbit);
final CircularOrbit cR = convertType(reference);
// perform normalization
if (cO.hasDerivatives()) {
return new CircularOrbit(cO.getA(),
cO.getCircularEx(),
cO.getCircularEy(),
cO.getI(),
MathUtils.normalizeAngle(cO.getRightAscensionOfAscendingNode(), cR.getRightAscensionOfAscendingNode()),
MathUtils.normalizeAngle(cO.getAlphaV(), cR.getAlphaV()),
cO.getADot(),
cO.getCircularExDot(),
cO.getCircularEyDot(),
cO.getIDot(),
cO.getRightAscensionOfAscendingNodeDot(),
cO.getAlphaVDot(),
PositionAngle.TRUE,
cO.getFrame(),
cO.getDate(),
cO.getMu());
} else {
return new CircularOrbit(cO.getA(),
cO.getCircularEx(),
cO.getCircularEy(),
cO.getI(),
MathUtils.normalizeAngle(cO.getRightAscensionOfAscendingNode(), cR.getRightAscensionOfAscendingNode()),
MathUtils.normalizeAngle(cO.getAlphaV(), cR.getAlphaV()),
PositionAngle.TRUE,
cO.getFrame(),
cO.getDate(),
cO.getMu());
}
}
/** {@inheritDoc} */
@Override
public <T extends CalculusFieldElement<T>> FieldCircularOrbit<T> normalize(final FieldOrbit<T> orbit, final FieldOrbit<T> reference) {
// convert input to proper type
final FieldCircularOrbit<T> cO = convertType(orbit);
final FieldCircularOrbit<T> cR = convertType(reference);
// perform normalization
if (cO.hasDerivatives()) {
return new FieldCircularOrbit<>(cO.getA(),
cO.getCircularEx(),
cO.getCircularEy(),
cO.getI(),
MathUtils.normalizeAngle(cO.getRightAscensionOfAscendingNode(), cR.getRightAscensionOfAscendingNode()),
MathUtils.normalizeAngle(cO.getAlphaV(), cR.getAlphaV()),
cO.getADot(),
cO.getCircularExDot(),
cO.getCircularEyDot(),
cO.getIDot(),
cO.getRightAscensionOfAscendingNodeDot(),
cO.getAlphaVDot(),
PositionAngle.TRUE,
cO.getFrame(),
cO.getDate(),
cO.getMu());
} else {
return new FieldCircularOrbit<>(cO.getA(),
cO.getCircularEx(),
cO.getCircularEy(),
cO.getI(),
MathUtils.normalizeAngle(cO.getRightAscensionOfAscendingNode(), cR.getRightAscensionOfAscendingNode()),
MathUtils.normalizeAngle(cO.getAlphaV(), cR.getAlphaV()),
PositionAngle.TRUE,
cO.getFrame(),
cO.getDate(),
cO.getMu());
}
}
},
/** Type for propagation in {@link EquinoctialOrbit equinoctial parameters}. */
......@@ -441,6 +538,87 @@ public enum OrbitType {
return drivers;
}
/** {@inheritDoc} */
@Override
public EquinoctialOrbit normalize(final Orbit orbit, final Orbit reference) {
// convert input to proper type
final EquinoctialOrbit eO = convertType(orbit);
final EquinoctialOrbit eR = convertType(reference);
// perform normalization
if (eO.hasDerivatives()) {
return new EquinoctialOrbit(eO.getA(),
eO.getEquinoctialEx(),
eO.getEquinoctialEy(),
eO.getHx(),
eO.getHy(),
MathUtils.normalizeAngle(eO.getLv(), eR.getLv()),
eO.getADot(),
eO.getEquinoctialExDot(),
eO.getEquinoctialEyDot(),
eO.getHxDot(),
eO.getHyDot(),
eO.getLvDot(),
PositionAngle.TRUE,
eO.getFrame(),
eO.getDate(),
eO.getMu());
} else {
return new EquinoctialOrbit(eO.getA(),
eO.getEquinoctialEx(),
eO.getEquinoctialEy(),
eO.getHx(),
eO.getHy(),
MathUtils.normalizeAngle(eO.getLv(), eR.getLv()),
PositionAngle.TRUE,
eO.getFrame(),
eO.getDate(),
eO.getMu());
}
}
/** {@inheritDoc} */
@Override
public <T extends CalculusFieldElement<T>> FieldEquinoctialOrbit<T> normalize(final FieldOrbit<T> orbit, final FieldOrbit<T> reference) {
// convert input to proper type
final FieldEquinoctialOrbit<T> eO = convertType(orbit);
final FieldEquinoctialOrbit<T> eR = convertType(reference);
// perform normalization
if (eO.hasDerivatives()) {
return new FieldEquinoctialOrbit<>(eO.getA(),
eO.getEquinoctialEx(),
eO.getEquinoctialEy(),
eO.getHx(),
eO.getHy(),
MathUtils.normalizeAngle(eO.getLv(), eR.getLv()),
eO.getADot(),
eO.getEquinoctialExDot(),
eO.getEquinoctialEyDot(),
eO.getHxDot(),
eO.getHyDot(),
eO.getLvDot(),
PositionAngle.TRUE,
eO.getFrame(),
eO.getDate(),
eO.getMu());
} else {
return new FieldEquinoctialOrbit<>(eO.getA(),
eO.getEquinoctialEx(),
eO.getEquinoctialEy(),
eO.getHx(),
eO.getHy(),
MathUtils.normalizeAngle(eO.getLv(), eR.getLv()),
PositionAngle.TRUE,
eO.getFrame(),
eO.getDate(),
eO.getMu());
}
}
},
......@@ -580,6 +758,88 @@ public enum OrbitType {
return drivers;
}
/** {@inheritDoc} */
@Override
public KeplerianOrbit normalize(final Orbit orbit, final Orbit reference) {
// convert input to proper type
final KeplerianOrbit kO = convertType(orbit);
final KeplerianOrbit kR = convertType(reference);
// perform normalization
if (kO.hasDerivatives()) {
return new KeplerianOrbit(kO.getA(),
kO.getE(),
kO.getI(),
MathUtils.normalizeAngle(kO.getPerigeeArgument(), kR.getPerigeeArgument()),
MathUtils.normalizeAngle(kO.getRightAscensionOfAscendingNode(), kR.getRightAscensionOfAscendingNode()),
MathUtils.normalizeAngle(kO.getTrueAnomaly(), kR.getTrueAnomaly()),
kO.getADot(),
kO.getEDot(),
kO.getIDot(),
kO.getPerigeeArgumentDot(),
kO.getRightAscensionOfAscendingNodeDot(),
kO.getTrueAnomalyDot(),
PositionAngle.TRUE,
kO.getFrame(),
kO.getDate(),
kO.getMu());
} else {
return new KeplerianOrbit(kO.getA(),
kO.getE(),
kO.getI(),
MathUtils.normalizeAngle(kO.getPerigeeArgument(), kR.getPerigeeArgument()),
MathUtils.normalizeAngle(kO.getRightAscensionOfAscendingNode(), kR.getRightAscensionOfAscendingNode()),
MathUtils.normalizeAngle(kO.getTrueAnomaly(), kR.getTrueAnomaly()),
PositionAngle.TRUE,
kO.getFrame(),
kO.getDate(),
kO.getMu());
}
}
/** {@inheritDoc} */
@Override
public <T extends CalculusFieldElement<T>> FieldKeplerianOrbit<T> normalize(final FieldOrbit<T> orbit, final FieldOrbit<T> reference) {
// convert input to proper type
final FieldKeplerianOrbit<T> kO = convertType(orbit);
final FieldKeplerianOrbit<T> kR = convertType(reference);
// perform normalization
if (kO.hasDerivatives()) {
return new FieldKeplerianOrbit<>(kO.getA(),
kO.getE(),
kO.getI(),
MathUtils.normalizeAngle(kO.getPerigeeArgument(), kR.getPerigeeArgument()),
MathUtils.normalizeAngle(kO.getRightAscensionOfAscendingNode(), kR.getRightAscensionOfAscendingNode()),
MathUtils.normalizeAngle(kO.getTrueAnomaly(), kR.getTrueAnomaly()),
kO.getADot(),
kO.getEDot(),
kO.getIDot(),
kO.getPerigeeArgumentDot(),
kO.getRightAscensionOfAscendingNodeDot(),
kO.getTrueAnomalyDot(),
PositionAngle.TRUE,
kO.getFrame(),
kO.getDate(),
kO.getMu());
} else {
return new FieldKeplerianOrbit<>(kO.getA(),
kO.getE(),
kO.getI(),
MathUtils.normalizeAngle(kO.getPerigeeArgument(), kR.getPerigeeArgument()),
MathUtils.normalizeAngle(kO.getRightAscensionOfAscendingNode(), kR.getRightAscensionOfAscendingNode()),
MathUtils.normalizeAngle(kO.getTrueAnomaly(), kR.getTrueAnomaly()),
PositionAngle.TRUE,
kO.getFrame(),
kO.getDate(),
kO.getMu());
}
}
};
/** Name for position along X. */
......@@ -750,10 +1010,10 @@ public enum OrbitType {
* @return orbit corresponding to the flat array as a space dynamics object
*/
public abstract <T extends CalculusFieldElement<T>> FieldOrbit<T> mapArrayToOrbit(T[] array,
T[] arrayDot,
PositionAngle type,
FieldAbsoluteDate<T> date,
T mu, Frame frame);
T[] arrayDot,
PositionAngle type,
FieldAbsoluteDate<T> date,
T mu, Frame frame);
/** Get parameters drivers initialized from a reference orbit.
* @param dP user specified position error
......@@ -764,6 +1024,41 @@ public enum OrbitType {
public abstract ParameterDriversList getDrivers(double dP, Orbit orbit,
PositionAngle type);
/** Normalize one orbit with respect to a reference one.
* <p>
* Given a, angular component ζ of an orbit and the corresponding
* angular component ζᵣ in the reference orbit, the angular component
* ζₙ of the normalized orbit will be ζₙ = ζ + 2kπ
* where k is chosen such that ζᵣ - π ≤ ζₙ ≤ ζᵣ + π. This is intended
* to avoid too large discontinuities and is particularly useful
* for normalizing the orbit after an impulsive maneuver with respect
* to the reference picked up before the maneuver.
* </p>
* @param <T> CalculusFieldElement used
* @param orbit orbit to normalize
* @param reference reference orbit
* @return normalized orbit (the type is guaranteed to match {@link OrbitType})
* @since 11.1
*/
public abstract <T extends CalculusFieldElement<T>> FieldOrbit<T> normalize(FieldOrbit<T> orbit, FieldOrbit<T> reference);
/** Normalize one orbit with respect to a reference one.
* <p>
* Given a, angular component ζ of an orbit and the corresponding
* angular component ζᵣ in the reference orbit, the angular component
* ζₙ of the normalized orbit will be ζₙ = ζ + 2kπ
* where k is chosen such that ζᵣ - π ≤ ζₙ ≤ ζᵣ + π. This is intended
* to avoid too large discontinuities and is particularly useful
* for normalizing the orbit after an impulsive maneuver with respect
* to the reference picked up before the maneuver.
* </p>
* @param orbit orbit to normalize
* @param reference reference orbit
* @return normalized orbit (the type is guaranteed to match {@link OrbitType})
* @since 11.1
*/
public abstract Orbit normalize(Orbit orbit, Orbit reference);
/** Compute scaling factor for parameters drivers.
* <p>
* The scales are estimated from partial derivatives properties of orbits,
......
src/test/java/org/orekit/orbits/CartesianOrbitTest.java
View file @ f255c874
......@@ -741,6 +741,15 @@ public class CartesianOrbitTest {
}
@Test
public void testNormalize() {
final Vector3D position = new Vector3D(42164140, 0, 0);
final PVCoordinates pv = new PVCoordinates(position,
new Vector3D(0, FastMath.sqrt(mu / position.getNorm()), 0));
final Orbit orbit = new CartesianOrbit(pv, FramesFactory.getEME2000(), date, mu);
Assert.assertSame(orbit, orbit.getType().normalize(orbit, null));
}
@Before
public void setUp() {
......
src/test/java/org/orekit/orbits/CircularOrbitTest.java
View file @ f255c874
......@@ -73,7 +73,7 @@ public class CircularOrbitTest {
// elliptic orbit
CircularOrbit circ =
new CircularOrbit(42166.712, 0.5, -0.5, i, raan,
new CircularOrbit(42166712.0, 0.5, -0.5, i, raan,
5.300 - raan, PositionAngle.MEAN,
FramesFactory.getEME2000(), date, mu);
Vector3D pos = circ.getPVCoordinates().getPosition();
......@@ -101,7 +101,7 @@ public class CircularOrbitTest {
// circular orbit
EquinoctialOrbit circCir =
new EquinoctialOrbit(42166.712, 0.1e-10, -0.1e-10, i, raan,
new EquinoctialOrbit(42166712.0, 0.1e-10, -0.1e-10, i, raan,
5.300 - raan, PositionAngle.MEAN,
FramesFactory.getEME2000(), date, mu);
Vector3D posCir = circCir.getPVCoordinates().getPosition();
......@@ -134,7 +134,7 @@ public class CircularOrbitTest {
double ey = eyTilde * cosRaan - exTilde * sinRaan;
CircularOrbit circ=
new CircularOrbit(42166.712, ex, ey, i, raan,
new CircularOrbit(42166712.0, ex, ey, i, raan,
5.300 - raan, PositionAngle.MEAN,
FramesFactory.getEME2000(), date, mu);
Vector3D pos = circ.getPVCoordinates().getPosition();
......@@ -145,13 +145,13 @@ public class CircularOrbitTest {
double v = vel.getNorm();
Assert.assertEquals(2 / r - v * v / mu, 1 / circ.getA(), 1.0e-7);
Assert.assertEquals( 0.233745668678733e+05, pos.getX(), Utils.epsilonTest * r);
Assert.assertEquals(-0.350998914352669e+05, pos.getY(), Utils.epsilonTest * r);
Assert.assertEquals(-0.150053723123334e+01, pos.getZ(), Utils.epsilonTest * r);
Assert.assertEquals( 0.233745668678733e+08, pos.getX(), Utils.epsilonTest * r);
Assert.assertEquals(-0.350998914352669e+08, pos.getY(), Utils.epsilonTest * r);
Assert.assertEquals(-0.150053723123334e+04, pos.getZ(), Utils.epsilonTest * r);
Assert.assertEquals(0.809135038364960e+05, vel.getX(), Utils.epsilonTest * v);
Assert.assertEquals(0.538902268252598e+05, vel.getY(), Utils.epsilonTest * v);
Assert.assertEquals(0.158527938296630e+02, vel.getZ(), Utils.epsilonTest * v);
Assert.assertEquals(2558.7096558809967, vel.getX(), Utils.epsilonTest * v);
Assert.assertEquals(1704.1586039092576, vel.getY(), Utils.epsilonTest * v);
Assert.assertEquals( 0.5013093577879, vel.getZ(), Utils.epsilonTest * v);
}
......@@ -170,12 +170,12 @@ public class CircularOrbitTest {
double ey = eyTilde * cosRaan - exTilde * sinRaan;
CircularOrbit circ=
new CircularOrbit(42166.712, ex, ey, i, raan,
new CircularOrbit(42166712.0, ex, ey, i, raan,
5.300 - raan, PositionAngle.MEAN,
FramesFactory.getEME2000(), date, mu);
KeplerianOrbit kep = new KeplerianOrbit(circ);
Assert.assertEquals(42166.71200, circ.getA(), Utils.epsilonTest * kep.getA());
Assert.assertEquals(42166712.000, circ.getA(), Utils.epsilonTest * kep.getA());
Assert.assertEquals(0.110283316961361e-03, kep.getE(), Utils.epsilonE * FastMath.abs(kep.getE()));
Assert.assertEquals(0.166901168553917e-03, kep.getI(),
Utils.epsilonAngle * FastMath.abs(kep.getI()));
......@@ -194,7 +194,7 @@ public class CircularOrbitTest {
@Test
public void testHyperbolic1() {
try {
new CircularOrbit(42166.712, 0.9, 0.5, 0.01, -0.02, 5.300,
new CircularOrbit(42166712.0, 0.9, 0.5, 0.01, -0.02, 5.300,
PositionAngle.MEAN, FramesFactory.getEME2000(), date, mu);
} catch (OrekitIllegalArgumentException oe) {
Assert.assertEquals(OrekitMessages.HYPERBOLIC_ORBIT_NOT_HANDLED_AS, oe.getSpecifier());
......@@ -203,7 +203,7 @@ public class CircularOrbitTest {
@Test
public void testHyperbolic2() {
Orbit orbit = new KeplerianOrbit(42166.712, 0.9, 0.5, 0.01, -0.02, 5.300,
Orbit orbit = new KeplerianOrbit(42166712.0, 0.9, 0.5, 0.01, -0.02, 5.300,
PositionAngle.MEAN, FramesFactory.getEME2000(), date, mu);
try {
new CircularOrbit(orbit.getPVCoordinates(), orbit.getFrame(), orbit.getMu());
......@@ -320,7 +320,7 @@ public class CircularOrbitTest {
double i = 2 * FastMath.atan(FastMath.sqrt(hx * hx + hy * hy));
double raan = FastMath.atan2(hy, hx);
CircularOrbit p =
new CircularOrbit(42166.712, 0.5, -0.5, i, raan,
new CircularOrbit(42166712.0, 0.5, -0.5, i, raan,
0.67 - raan, PositionAngle.TRUE,
FramesFactory.getEME2000(), date, mu);
......@@ -377,7 +377,7 @@ public class CircularOrbitTest {
double i = 2 * FastMath.atan(FastMath.sqrt(hx * hx + hy * hy));
double raan = FastMath.atan2(hy, hx);
CircularOrbit pCirEqua =
new CircularOrbit(42166.712, 0.1e-8, 0.1e-8, i, raan,
new CircularOrbit(42166712.0, 0.1e-8, 0.1e-8, i, raan,
0.67 - raan, PositionAngle.TRUE,
FramesFactory.getEME2000(), date, mu);
......@@ -408,7 +408,7 @@ public class CircularOrbitTest {
double i = 2 * FastMath.atan(FastMath.sqrt(hx * hx + hy * hy));
double raan = FastMath.atan2(hy, hx);
CircularOrbit p =
new CircularOrbit(42166.712, 0.5, -0.5, i, raan,
new CircularOrbit(42166712.0, 0.5, -0.5, i, raan,
0.67 - raan, PositionAngle.TRUE,
FramesFactory.getEME2000(), date, mu);
......@@ -452,7 +452,7 @@ public class CircularOrbitTest {
double i = 2 * FastMath.atan(FastMath.sqrt(hx * hx + hy * hy));
double raan = FastMath.atan2(hy, hx);
CircularOrbit pCirEqua =
new CircularOrbit(42166.712, 0.1e-8, 0.1e-8, i, raan,
new CircularOrbit(42166712.0, 0.1e-8, 0.1e-8, i, raan,
0.67 - raan, PositionAngle.TRUE,
FramesFactory.getEME2000(), date, mu);
......@@ -1199,6 +1199,57 @@ public class CircularOrbitTest {
}
@Test
public void testNormalize() {
CircularOrbit withoutDerivatives =
new CircularOrbit(42166712.0, 0.005, -0.025, 1.6,
1.25, 0.4, PositionAngle.MEAN,
FramesFactory.getEME2000(), date, mu);
CircularOrbit ref =
new CircularOrbit(24000000.0, -0.012, 0.01, 0.2,
-6.28, 6.28, PositionAngle.MEAN,
FramesFactory.getEME2000(), date, mu);
CircularOrbit normalized1 = (CircularOrbit) OrbitType.CIRCULAR.normalize(withoutDerivatives, ref);
Assert.assertFalse(normalized1.hasDerivatives());
Assert.assertEquals(0.0, normalized1.getA() - withoutDerivatives.getA(), 1.0e-6);
Assert.assertEquals(0.0, normalized1.getCircularEx() - withoutDerivatives.getCircularEx(), 1.0e-10);
Assert.assertEquals(0.0, normalized1.getCircularEy() - withoutDerivatives.getCircularEy(), 1.0e-10);
Assert.assertEquals(0.0, normalized1.getI() - withoutDerivatives.getI(), 1.0e-10);
Assert.assertEquals(-MathUtils.TWO_PI, normalized1.getRightAscensionOfAscendingNode() - withoutDerivatives.getRightAscensionOfAscendingNode(), 1.0e-10);
Assert.assertEquals(+MathUtils.TWO_PI, normalized1.getAlphaV() - withoutDerivatives.getAlphaV(), 1.0e-10);
Assert.assertTrue(Double.isNaN(normalized1.getADot()));
Assert.assertTrue(Double.isNaN(normalized1.getCircularExDot()));
Assert.assertTrue(Double.isNaN(normalized1.getCircularEyDot()));
Assert.assertTrue(Double.isNaN(normalized1.getIDot()));
Assert.assertTrue(Double.isNaN(normalized1.getRightAscensionOfAscendingNodeDot()));
Assert.assertTrue(Double.isNaN(normalized1.getAlphaVDot()));
double[] p = new double[6];
OrbitType.CIRCULAR.mapOrbitToArray(withoutDerivatives, PositionAngle.TRUE, p, null);
CircularOrbit withDerivatives = (CircularOrbit) OrbitType.CIRCULAR.mapArrayToOrbit(p,
new double[] { 1.0, 2.0, 3.0, 4.0, 5.0, 6.0 },
PositionAngle.TRUE,
withoutDerivatives.getDate(),
withoutDerivatives.getMu(),
withoutDerivatives.getFrame());
CircularOrbit normalized2 = (CircularOrbit) OrbitType.CIRCULAR.normalize(withDerivatives, ref);
Assert.assertTrue(normalized2.hasDerivatives());
Assert.assertEquals(0.0, normalized2.getA() - withDerivatives.getA(), 1.0e-6);
Assert.assertEquals(0.0, normalized2.getCircularEx() - withDerivatives.getCircularEx(), 1.0e-10);
Assert.assertEquals(0.0, normalized2.getCircularEy() - withDerivatives.getCircularEy(), 1.0e-10);
Assert.assertEquals(0.0, normalized2.getI() - withDerivatives.getI(), 1.0e-10);
Assert.assertEquals(-MathUtils.TWO_PI, normalized2.getRightAscensionOfAscendingNode() - withDerivatives.getRightAscensionOfAscendingNode(), 1.0e-10);
Assert.assertEquals(+MathUtils.TWO_PI, normalized2.getAlphaV() - withDerivatives.getAlphaV(), 1.0e-10);
Assert.assertEquals(0.0, normalized2.getADot() - withDerivatives.getADot(), 1.0e-10);
Assert.assertEquals(0.0, normalized2.getCircularExDot() - withDerivatives.getCircularExDot(), 1.0e-10);
Assert.assertEquals(0.0, normalized2.getCircularEyDot() - withDerivatives.getCircularEyDot(), 1.0e-10);
Assert.assertEquals(0.0, normalized2.getIDot() - withDerivatives.getIDot(), 1.0e-10);
Assert.assertEquals(0.0, normalized2.getRightAscensionOfAscendingNodeDot() - withDerivatives.getRightAscensionOfAscendingNodeDot(), 1.0e-10);
Assert.assertEquals(0.0, normalized2.getAlphaVDot() - withDerivatives.getAlphaVDot(), 1.0e-10);
}
@Before
public void setUp() {
......
src/test/java/org/orekit/orbits/EquinoctialOrbitTest.java
View file @ f255c874
......@@ -72,7 +72,7 @@ public class EquinoctialOrbitTest {
// elliptic orbit
EquinoctialOrbit equi =
new EquinoctialOrbit(42166.712, 0.5, -0.5, hx, hy,
new EquinoctialOrbit(42166712.0, 0.5, -0.5, hx, hy,
5.300, PositionAngle.MEAN,
FramesFactory.getEME2000(), date, mu);
Vector3D pos = equi.getPVCoordinates().getPosition();
......@@ -106,7 +106,7 @@ public class EquinoctialOrbitTest {
// circular orbit
EquinoctialOrbit equiCir =
new EquinoctialOrbit(42166.712, 0.1e-10, -0.1e-10, hx, hy,
new EquinoctialOrbit(42166712.0, 0.1e-10, -0.1e-10, hx, hy,
5.300, PositionAngle.MEAN,
FramesFactory.getEME2000(), date, mu);
Vector3D posCir = equiCir.getPVCoordinates().getPosition();
......@@ -141,7 +141,7 @@ public class EquinoctialOrbitTest {
double hy = FastMath.tan(inc / 2.) * iy / (2 * FastMath.sin(inc / 2.));
EquinoctialOrbit equi =
new EquinoctialOrbit(42166.712, -7.900e-06, 1.100e-04, hx, hy,
new EquinoctialOrbit(42166712.0, -7.900e-06, 1.100e-04, hx, hy,
5.300, PositionAngle.MEAN,
FramesFactory.getEME2000(), date, mu);
Vector3D pos = equi.getPVCoordinates().getPosition();
......@@ -151,19 +151,13 @@ public class EquinoctialOrbitTest {
double oneovera = (2. / pos.getNorm()) - vit.getNorm() * vit.getNorm() / mu;