Commit 795ea3b3 authored by Pascal Parraud's avatar Pascal Parraud

Fixed Javadoc

parent acc74621
......@@ -56,13 +56,12 @@ import org.orekit.utils.TimeStampedFieldAngularCoordinates;
* to different activation patterns depending on which events are triggered first. An example
* of this feature is handling switches to safe mode if some contingency condition is met, in
* addition to the nominal switches that correspond to proper operations. Another example
* is handling of maneuver mode.<p>
* is handling of maneuver mode.
* <p>
* Note that this attitude provider is stateful, it keeps in memory the sequence of active
* underlying providers with their switch dates and the transitions from one provider to
* the other. This implies that this provider should <em>not</em> be shared among different
* propagators at the same time, each propagator should use its own instance of this provider.
* </p>
* <p>
* The sequence kept in memory is reset when {@link #resetActiveProvider(AttitudeProvider)}
* is called, and only the specify provider is kept. The sequence is also partially
......
......@@ -407,7 +407,6 @@ public class OneAxisEllipsoid extends Ellipsoid implements BodyShape {
* <li>in order to handle properly corner cases near the equatorial plane, even far inside the ellipsoid</li>
* <li>in order to handle very flat ellipsoids</li>
* </ul>
* </p>
*/
public GeodeticPoint transform(final Vector3D point, final Frame frame, final AbsoluteDate date) {
......@@ -527,7 +526,6 @@ public class OneAxisEllipsoid extends Ellipsoid implements BodyShape {
* <li>in order to handle properly corner cases near the equatorial plane, even far inside the ellipsoid</li>
* <li>in order to handle very flat ellipsoids</li>
* </ul>
* </p>
*/
public <T extends RealFieldElement<T>> FieldGeodeticPoint<T> transform(final FieldVector3D<T> point,
final Frame frame,
......
......@@ -194,11 +194,12 @@ public class PV extends AbstractMeasurement<PV> {
}
/** Get the correlation coefficients matrix.
* <br>This is the 6x6 matrix M such that:</br>
* <br>Mij = Pij/(σi.σj)</br>
* <br>Where: <ul>
* <li> P is the covariance matrix
* <li> σi is the i-th standard deviation (σi² = Pii)
* <p>This is the 6x6 matrix M such that:
* <p>Mij = Pij/(σi.σj)
* <p>Where:
* <ul>
* <li>P is the covariance matrix
* <li>σi is the i-th standard deviation (σi² = Pii)
* </ul>
* @return the correlation coefficient matrix (6x6)
*/
......
......@@ -127,11 +127,12 @@ public class Position extends AbstractMeasurement<Position> {
}
/** Get the correlation coefficients matrix.
* <br>This is the 3x3 matrix M such that:</br>
* <br>Mij = Pij/(σi.σj)</br>
* <br>Where: <ul>
* <li> P is the covariance matrix
* <li> σi is the i-th standard deviation (σi² = Pii)
* <p>This is the 3x3 matrix M such that:
* <p>Mij = Pij/(σi.σj)
* <p>Where:
* <ul>
* <li>P is the covariance matrix
* <li>σi is the i-th standard deviation (σi² = Pii)
* </ul>
* @return the correlation coefficient matrix (3x3)
*/
......
......@@ -54,7 +54,6 @@ import org.orekit.utils.ParameterDriversList.DelegatingDriver;
* <li><b>Measurements parameters</b>: Parameters related to measurements (station biases, positions etc...).<br>
* They are passed down to the filter in its constructor.</li>
* </ol>
* </p>
* <p>
* The total number of estimated parameters is m, the size of the state vector.
* </p>
......
......@@ -62,7 +62,7 @@ import org.orekit.utils.TimeStampedPVCoordinates;
* be overridden for a particular segment using the {@code metadata} argument to {@link
* #newSegment(Frame, Map)}.
*
* <table>
* <table summary="OEM metada">
* <thead>
* <tr>
* <th>Keyword
......
......@@ -40,20 +40,19 @@ public interface EphemerisFileParser {
/**
* Parse an ephemeris file from a file on the local file system.
*
* <p> For Implementors: Most subclasses should implement this method as follows, but
* <p>For Implementors: Most subclasses should implement this method as follows, but
* there is no default implementation because most subclasses should use a specialized
* return type.
*
* <code><pre>
* <pre>
* try (BufferedReader reader = Files.newBufferedReader(Paths.get(fileName))) {
* return parse(reader, fileName);
* }
* </pre></code>
* </pre>
*
* @param fileName path to the ephemeris file.
* @return parsed ephemeris file.
* @throws IOException if one is thrown while opening or reading from {@code
* fileName}.
* @throws IOException if one is thrown while opening or reading from {@code fileName}
*/
EphemerisFile parse(String fileName) throws IOException;
......
......@@ -29,17 +29,17 @@
*
* <p> For example to create a propagator from an OEM file one can use:
*
* <code><pre>
* <pre>
* EphemerisFileParser parser = new OEMParser()
* .withConventions(IERSConventions.IERS_2010);
* EphemerisFile file = parser.parse("my/ephemeris/file.oem");
* BoundedPropagator propagator = file.getPropagator();
* </pre></code>
* </pre>
*
* <p> The parsed ephemeris file also provides access to the individual data records in
* the file.
*
* <code><pre>
* <pre>
* // ... continued from previous example
* // get a satellite by ID string
* SatelliteEphemeris sat = file.getSatellites().get("satellite ID");
......@@ -47,7 +47,7 @@
* EphemerisSegment segment = sat.getSegments().get(0)
* // get first state vector in segment
* TimeStampedPVCoordinate pv = segment.getCoordinates().get(0);
* </pre></code>
* </pre>
*
* @author T. Neidhart
* @author Evan Ward
......
......@@ -140,7 +140,7 @@ public interface ForceModel {
* @param s current state information: date, kinematics, attitude
* @param parameters values of the force model parameters
* @return acceleration in same frame as state
* @since 9.0
* @since 9.0
*/
Vector3D acceleration(SpacecraftState s, double[] parameters);
......@@ -149,7 +149,7 @@ public interface ForceModel {
* @param parameters values of the force model parameters
* @return acceleration in same frame as state
* @param <T> type of the elements
* @since 9.0
* @since 9.0
*/
<T extends RealFieldElement<T>> FieldVector3D<T> acceleration(FieldSpacecraftState<T> s, T[] parameters);
......@@ -160,7 +160,7 @@ public interface ForceModel {
/** Get the discrete events related to the model.
* @param field field to which the state belongs
* @param <T> extends RealFieldElement<T>
* @param <T> extends RealFieldElement&lt;T&gt;
* @return stream of events detectors
*/
<T extends RealFieldElement<T>> Stream<FieldEventDetector<T>> getFieldEventsDetectors(Field<T> field);
......
......@@ -68,15 +68,15 @@ import org.orekit.utils.TimeStampedPVCoordinates;
*
* <p> The transform to apply then is defined as follows :
*
* <pre><code>
* <pre>
* Vector3D translation = new Vector3D(-1, 0, 0);
* Vector3D velocity = new Vector3D(-2, 0, 0);
* Vector3D acceleration = new Vector3D(-3, 0, 0);
*
* Transform R1toR2 = new Transform(date, translation, velocity, acceleration);
*
* PVB = R1toR2.transformPVCoordinates<T>(PVA);
* </code></pre>
* PVB = R1toR2.transformPVCoordinate(PVA);
* </pre>
*
* <h2> Example of rotation from R<sub>A</sub> to R<sub>B</sub> </h2>
* <p> We want to transform the {@link FieldPVCoordinates} PV<sub>A</sub> to
......@@ -87,14 +87,14 @@ import org.orekit.utils.TimeStampedPVCoordinates;
*
* <p> The transform to apply then is defined as follows :
*
* <pre><code>
* <pre>
* Rotation rotation = new Rotation(Vector3D.PLUS_K, FastMath.PI / 2);
* Vector3D rotationRate = new Vector3D(0, 0, -2);
*
* Transform R1toR2 = new Transform(rotation, rotationRate);
*
* PVB = R1toR2.transformPVCoordinates<T>(PVA);
* </code></pre>
* PVB = R1toR2.transformPVCoordinates(PVA);
* </pre>
*
* @author Luc Maisonobe
* @author Fabien Maussion
......@@ -728,14 +728,10 @@ public class FieldTransform<T extends RealFieldElement<T>>
* </p>
* <p>
* This definition implies that if we define position-velocity coordinates
* <pre>
* PV₁ = transform.transformPVCoordinates<T>(PV₀), then
* </pre>
* <p> their differentials dPV₁ and dPV₀ will obey the following relation
* <pre>PV₁ = transform.transformPVCoordinates(PV₀)</pre>
* then their differentials dPV₁ and dPV₀ will obey the following relation
* where J is the matrix computed by this method:
* <pre>
* dPV₁ = J &times; dPV₀
* </pre>
* <pre>dPV₁ = J &times; dPV₀</pre>
*
* @param selector selector specifying the size of the upper left corner that must be filled
* (either 3x3 for positions only, 6x6 for positions and velocities, 9x9 for positions,
......
......@@ -325,7 +325,7 @@ public class HarrisPriester implements Atmosphere {
* @param sunInEarth position of the Sun in Earth frame (m)
* @param posInEarth target position in Earth frame (m)
* @return the local density (kg/m³)
* @param <T> instance of RealFieldElement<T>
* @param <T> instance of RealFieldElement&lt;T&gt;
*/
public <T extends RealFieldElement<T>> T getDensity(final Vector3D sunInEarth, final FieldVector3D<T> posInEarth) {
final T zero = posInEarth.getX().getField().getZero();
......
......@@ -50,7 +50,6 @@ import org.orekit.utils.PVCoordinatesProvider;
* <li>one compliant with OREKIT Atmosphere interface, necessary to the
* {@link org.orekit.forces.drag.DragForce drag force model} computation.</li>
* </ul>
* </p>
* <p>
* This model provides dense output for all altitudes and positions. Output data are :
* <ul>
......@@ -58,7 +57,6 @@ import org.orekit.utils.PVCoordinatesProvider;
* <li>Temperature at Input Position (deg K)</li>
* <li>Total Mass-Density at Input Position (kg/m³)</li>
* </ul>
* </p>
* <p>
* The model needs geographical and time information to compute general values,
* but also needs space weather data : mean and daily solar flux, retrieved through
......
......@@ -64,7 +64,6 @@ import org.orekit.utils.PVCoordinatesProvider;
* </ul>
* </li>
* </ul>
* </p>
* <p>
* The model needs geographical and time information to compute general values,
* but also needs space weather data:
......@@ -72,7 +71,6 @@ import org.orekit.utils.PVCoordinatesProvider;
* <li>mean and daily solar flux,</li>
* <li>geomagnetic indices.</li>
* </ul>
* </p>
* <p>
* Switches can be used to turn on and off particular variations:<br>
* 0 is off, 1 is on, and 2 is main effects off but cross terms on.<br>
......@@ -108,7 +106,6 @@ import org.orekit.utils.PVCoordinatesProvider;
* <li>set to 1, the daily Ap only is used (first element of ap array),</li>
* <li>set to -1, the entire array of ap is used, including 3 hr ap indices.</li>
* </ul>
* </p>
* <p>
* The NRLMSISE-00 model was developed by Mike Picone, Alan Hedin, and Doug Drob.<br>
* They also wrote a NRLMSISE-00 distribution package in FORTRAN available at:<br>
......@@ -116,7 +113,6 @@ import org.orekit.utils.PVCoordinatesProvider;
* <br>
* Dominik Brodowski implemented a C version of the NRLMSISE-00 model available at:<br>
* http://www.brodo.de/space/nrlmsise/index.html
* </p>
* <p>
* Instances of this class are immutable.
* </p>
......@@ -2630,13 +2626,13 @@ public class NRLMSISE00 implements Atmosphere {
* of the mass densities of all species in this model, INCLUDING anomalous oxygen.</li>
* </ul>
* O, H, and N are set to zero below 72.5 km.
* </p>
* <p>
* Temperatures are provided as an array t such as:
* <ul>
* <li>t[0] = exospheric temperature (K)</li>
* <li>t[1] = temperature at altitude (K)</li>
* </ul>
* <p>
* t[0] is set to global average for altitudes below 120 km.<br>
* The 120 km gradient is left at global average value for altitudes below 72 km.
* </p>
......
......@@ -25,7 +25,6 @@ import org.orekit.time.AbsoluteDate;
* <p>
* This model needs daily and average F10.7 solar fluxes and
* A<sub>p</sub> geomagnetic indices to compute the local density.
* </p>
*
* @author Pascal Parraud
*/
......@@ -67,7 +66,6 @@ public interface NRLMSISE00InputParameters extends Serializable {
* <li>6 → Average of eight 3 hr A<sub>p</sub> indices from 36 to 57 hrs
* prior to current time</li>
* </ul>
* </p>
* @param date the current date
* @return the array of A<sub>p</sub> indices
*/
......
......@@ -25,10 +25,9 @@ import org.orekit.time.FieldAbsoluteDate;
* <p>
* Models that implement this interface split the delay into hydrostatic
* and non-hydrostatic part:
* </p>
* <pre>
* <p>
* δ = δ<sub>h</sub> + δ<sub>nh</sub>
* </pre>
* <p>
* With:
* <ul>
* <li> δ<sub>h</sub> = hydrostatic delay </li>
......
......@@ -28,9 +28,9 @@ import org.orekit.time.FieldAbsoluteDate;
import org.orekit.utils.ParameterDriver;
/** An estimated tropospheric model. The tropospheric delay is computed according to the formula:
* <pre>
* <p>
* δ = δ<sub>h</sub> * m<sub>h</sub> + (δ<sub>t</sub> - δ<sub>h</sub>) * m<sub>w</sub>
* </pre>
* <p>
* With:
* <ul>
* <li>δ<sub>h</sub>: Tropospheric zenith hydro-static delay.</li>
......
......@@ -219,22 +219,16 @@ public class MendesPavlisModel implements DiscreteTroposphericModel {
/** With the Mendes Pavlis tropospheric model, the mapping
* function is not split into hydrostatic and wet component.
* <p>
* Therefore, the two components of the resulting array are
* equals.
* Therefore, the two components of the resulting array are equals.
* <ul>
* <li>double[0] = m(e) → total mapping function
* <li>double[1] = m(e) → total mapping function
* </ul>
* </p><p>
* The total delay will thus be computed as this:
* <pre>
* δ = D<sub>hz</sub> * m(e) + D<sub>wz</sub> * m(e)
* </pre>
* <pre>
* <p>
* The total delay will thus be computed as:<br>
* δ = D<sub>hz</sub> * m(e) + D<sub>wz</sub> * m(e)<br>
* δ = (D<sub>hz</sub> + D<sub>wz</sub>) * m(e) = δ<sub>z</sub> * m(e)
* </pre>
* </p>
* */
*/
@Override
public double[] mappingFactors(final double elevation, final double height,
final double[] parameters, final AbsoluteDate date) {
......
......@@ -29,7 +29,7 @@
* and non-hydrostatic parts</li>
* <li>Estimation of the total zenith delay</li>
* </ul>
* </p>
*
* @author Bryan Cazabonne
*
*/
......
......@@ -24,7 +24,7 @@
* <li>Pressure</li>
* <li>Temperature</li>
* </ul>
*
* <p>
* These parameters can be used as input parameters for the models that required
* the values of the pressure and the temperature.
* </p>
......
......@@ -57,7 +57,6 @@ import org.orekit.utils.TimeStampedFieldPVCoordinates;
* <li>zDot</li>
* </ul>
* contained in {@link PVCoordinates}.
* </p>
* <p>
* Note that the implementation of this class delegates all non-Cartesian related
......
......@@ -55,7 +55,6 @@ import org.orekit.utils.TimeStampedFieldPVCoordinates;
* </ul>
* where Ω stands for the Right Ascension of the Ascending Node and
* α<sub>v</sub> stands for the true latitude argument
* </p>
* <p>
* The conversion equations from and to Keplerian elements given above hold only
* when both sides are unambiguously defined, i.e. when orbit is neither equatorial
......@@ -1342,9 +1341,9 @@ public class FieldCircularOrbit<T extends RealFieldElement<T>>
* Normalize an angle in a 2&pi; wide interval around a center value.
* <p>This method has three main uses:</p>
* <ul>
* <li>normalize an angle between 0 and 2&pi;:<br/>
* <li>normalize an angle between 0 and 2&pi;:<br>
* {@code a = MathUtils.normalizeAngle(a, FastMath.PI);}</li>
* <li>normalize an angle between -&pi; and +&pi;<br/>
* <li>normalize an angle between -&pi; and +&pi;<br>
* {@code a = MathUtils.normalizeAngle(a, 0.0);}</li>
* <li>compute the angle between two defining angular positions:<br>
* {@code angle = MathUtils.normalizeAngle(end, start) - start;}</li>
......
......@@ -55,7 +55,6 @@ import org.orekit.utils.TimeStampedFieldPVCoordinates;
* </pre>
* where ω stands for the Perigee Argument and Ω stands for the
* Right Ascension of the Ascending Node.
* </p>
* <p>
* The conversion equations from and to Keplerian elements given above hold only
* when both sides are unambiguously defined, i.e. when orbit is neither equatorial
......@@ -1100,9 +1099,9 @@ public class FieldEquinoctialOrbit<T extends RealFieldElement<T>> extends FieldO
* Normalize an angle in a 2&pi; wide interval around a center value.
* <p>This method has three main uses:</p>
* <ul>
* <li>normalize an angle between 0 and 2&pi;:<br/>
* <li>normalize an angle between 0 and 2&pi;:<br>
* {@code a = MathUtils.normalizeAngle(a, FastMath.PI);}</li>
* <li>normalize an angle between -&pi; and +&pi;<br/>
* <li>normalize an angle between -&pi; and +&pi;<br>
* {@code a = MathUtils.normalizeAngle(a, 0.0);}</li>
* <li>compute the angle between two defining angular positions:<br>
* {@code angle = MathUtils.normalizeAngle(end, start) - start;}</li>
......
......@@ -57,7 +57,6 @@ import org.orekit.utils.TimeStampedFieldPVCoordinates;
* </pre>
* where ω stands for the Perigee Argument, Ω stands for the
* Right Ascension of the Ascending Node and v stands for the true anomaly.
* </p>
* <p>
* This class supports hyperbolic orbits, using the convention that semi major
* axis is negative for such orbits (and of course eccentricity is greater than 1).
......@@ -1730,9 +1729,9 @@ public class FieldKeplerianOrbit<T extends RealFieldElement<T>> extends FieldOrb
* Normalize an angle in a 2&pi; wide interval around a center value.
* <p>This method has three main uses:</p>
* <ul>
* <li>normalize an angle between 0 and 2&pi;:<br/>
* <li>normalize an angle between 0 and 2&pi;:<br>
* {@code a = MathUtils.normalizeAngle(a, FastMath.PI);}</li>
* <li>normalize an angle between -&pi; and +&pi;<br/>
* <li>normalize an angle between -&pi; and +&pi;<br>
* {@code a = MathUtils.normalizeAngle(a, 0.0);}</li>
* <li>compute the angle between two defining angular positions:<br>
* {@code angle = MathUtils.normalizeAngle(end, start) - start;}</li>
......
......@@ -73,9 +73,9 @@ public interface FieldPropagator<T extends RealFieldElement<T>> extends FieldPVC
/** Set the propagator to slave mode.
* <p>This mode is used when the user needs only the final orbit at the target time.
* The (slave) propagator computes this result and return it to the calling
* (master) application, without any intermediate feedback.<p>
* <p>This is the default mode.</p>
* The (slave) propagator computes this result and return it to the calling
* (master) application, without any intermediate feedback.
* <p>This is the default mode.
* @see #setMasterMode(RealFieldElement, FieldOrekitFixedStepHandler)
* @see #setMasterMode(FieldOrekitStepHandler)
* @see #setEphemerisMode()
......
......@@ -107,7 +107,7 @@ public class FieldSpacecraftState <T extends RealFieldElement<T>>
private final Map<String, T[]> additional;
/** Build a spacecraft state from orbit only.
* <p>FieldAttitude<T> and mass are set to unspecified non-null arbitrary values.</p>
* <p>FieldAttitude and mass are set to unspecified non-null arbitrary values.</p>
* @param orbit the orbit
*/
public FieldSpacecraftState(final FieldOrbit<T> orbit) {
......@@ -129,7 +129,7 @@ public class FieldSpacecraftState <T extends RealFieldElement<T>>
}
/** Create a new instance from orbit and mass.
* <p>FieldAttitude<T> law is set to an unspecified default attitude.</p>
* <p>FieldAttitude law is set to an unspecified default attitude.</p>
* @param orbit the orbit
* @param mass the mass (kg)
*/
......@@ -152,7 +152,7 @@ public class FieldSpacecraftState <T extends RealFieldElement<T>>
}
/** Build a spacecraft state from orbit only.
* <p>FieldAttitude<T> and mass are set to unspecified non-null arbitrary values.</p>
* <p>FieldAttitude and mass are set to unspecified non-null arbitrary values.</p>
* @param orbit the orbit
* @param additional additional states
*/
......@@ -176,7 +176,7 @@ public class FieldSpacecraftState <T extends RealFieldElement<T>>
}
/** Create a new instance from orbit and mass.
* <p>FieldAttitude<T> law is set to an unspecified default attitude.</p>
* <p>FieldAttitude law is set to an unspecified default attitude.</p>
* @param orbit the orbit
* @param mass the mass (kg)
* @param additional additional states
......
......@@ -34,7 +34,7 @@ import org.orekit.time.FieldAbsoluteDate;
* method is called. This class can be used to add a global logging
* feature registering all events with their corresponding states in
* a chronological sequence (or reverse-chronological if propagation
* occurs backward).<p>
* occurs backward).
* <p>This class works by wrapping user-provided {@link FieldEventDetector
* events detectors} before they are registered to the propagator. The
* wrapper monitor the calls to {@link
......@@ -69,7 +69,7 @@ public class FieldEventsLogger<T extends RealFieldElement<T>> {
* <pre>
* Propagator propagator = new XyzPropagator(...);
* EventsLogger logger = new EventsLogger();
* FieldEventDetector<T> detector = new UvwDetector(...);
* FieldEventDetector&lt;T&gt; detector = new UvwDetector(...);
* propagator.addEventDetector(logger.monitorDetector(detector));
* </pre>
* <p>
......
......@@ -28,11 +28,11 @@ import org.orekit.propagation.events.handlers.EventHandler;
*
* <p>For example, to create a simple date detector use:
*
* <code><pre>
* <pre>
* FunctionalDetector d = new FunctionalDetector()
* .withGFunction((s) -&gt; s.getDate().durationFrom(triggerDate))
* .withMaxCheck(1e10);
* </pre></code>
* </pre>
*
* @author Evan Ward
* @since 9.2
......
......@@ -112,7 +112,6 @@ import org.orekit.utils.TimeStampedFieldPVCoordinates;
* v<sub>y</sub>, v<sub>z</sub>) in meters and meters per seconds.
* </ul>
* The last element is the mass in kilograms.
* </p>
* <p>The following code snippet shows a typical setting for Low Earth Orbit propagation in
* equinoctial parameters and true longitude argument:</p>
* <pre>
......@@ -572,7 +571,6 @@ public class FieldNumericalPropagator<T extends RealFieldElement<T>> extends Fie
* So we deduce a scalar velocity error consistent with the position error.
* From here, we apply orbits Jacobians matrices to get consistent errors
* on orbital parameters.
* </p>
* <p>
* The tolerances are only <em>orders of magnitude</em>, and integrator tolerances
* are only local estimates, not global ones. So some care must be taken when using
......
......@@ -178,9 +178,9 @@ public class FieldAuxiliaryElements<T extends RealFieldElement<T>> {
* Normalize an angle in a 2&pi; wide interval around a center value.
* <p>This method has three main uses:</p>
* <ul>
* <li>normalize an angle between 0 and 2&pi;:<br/>
* <li>normalize an angle between 0 and 2&pi;:<br>
* {@code a = MathUtils.normalizeAngle(a, FastMath.PI);}</li>
* <li>normalize an angle between -&pi; and +&pi;<br/>
* <li>normalize an angle between -&pi; and +&pi;<br>
* {@code a = MathUtils.normalizeAngle(a, 0.0);}</li>
* <li>compute the angle between two defining angular positions:<br>
* {@code angle = MathUtils.normalizeAngle(end, start) - start;}</li>
......
......@@ -42,12 +42,12 @@ import org.hipparchus.util.FastMath;
* <p> Internally, the Modified Newcomb Operators are stored as an array of
* {@link PolynomialFunction} :
*
* <p> Y<sub>ρ,σ</sub><sup>n,s</sup> = P<sub>k₀</sub> + P<sub>k₁</sub>n + ... +
* P<sub>k<sub>j</sub></sub>n<sup>j</sup>
* <p> Y<sub>ρ,σ</sub><sup>n,s</sup> = P<sub>k0</sub> + P<sub>k1</sub>n + ... +
* P<sub>kj</sub>n<sup>j</sup>
*
* <p> where the P<sub>k<sub>j</sub></sub> are given by
* <p> where the P<sub>kj</sub> are given by
*
* <p> P<sub>k<sub>j</sub></sub> = ∑<sub>j=0;ρ</sub> a<sub>j</sub>s<sup>j</sup>
* <p> P<sub>kj</sub> = ∑<sub>j=0;ρ</sub> a<sub>j</sub>s<sup>j</sup>
*
* @author Romain Di Costanzo
* @author Pascal Parraud
......
......@@ -60,8 +60,8 @@ import org.orekit.utils.Constants;
* #AbsoluteDate(int, int, int, int, int, double, TimeScale)}, {@link
* #AbsoluteDate(int, int, int, TimeScale)}, {@link #AbsoluteDate(Date,
* TimeScale)}, {@link #parseCCSDSCalendarSegmentedTimeCode(byte, byte[])},
* toString(){@link #toDate(TimeScale)}, {@link #toString(TimeScale)
* toString(timeScale)}, {@link #toString()}, and {@link #timeScalesOffset}.</p>
* {@link #toDate(TimeScale)}, {@link #toString(TimeScale) toString(timeScale)},
* {@link #toString()}, and {@link #timeScalesOffset}.</p>
* </li>
* <li><p>offset view (mainly for physical computation)</p>
* <p>offsets represent either the flow of time between two events
......
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