Commit f8e03ef5 authored by Luc Maisonobe's avatar Luc Maisonobe

Merge branch 'master' into release-candidate

parents 77ce5652 b13f6c3c
......@@ -33,7 +33,7 @@ import org.orekit.utils.PVCoordinatesProvider;
* <li>a celestial body towards which some satellite axis is exactly aimed</li>
* <li>a phasing reference defining the rotation around the pointing axis</li>
* </ul>
* </p>
*
* <p>
* The celestial body implicitly defines two of the three degrees of freedom
* and the phasing reference defines the remaining degree of freedom. This definition
......
......@@ -72,6 +72,7 @@ public class OneAxisEllipsoid extends Ellipsoid implements BodyShape {
/** Simple constructor.
* <p>Standard values for Earth models can be found in the {@link org.orekit.utils.Constants Constants} class:</p>
* <table border="1" cellpadding="5">
* <caption>Ellipsoid Models</caption>
* <tr bgcolor="#ccccff"><th>model</th><th>a<sub>e</sub> (m)</th> <th>f</th></tr>
* <tr><td bgcolor="#eeeeff">GRS 80</td>
* <td>{@link org.orekit.utils.Constants#GRS80_EARTH_EQUATORIAL_RADIUS Constants.GRS80_EARTH_EQUATORIAL_RADIUS}</td>
......
......@@ -37,9 +37,8 @@ import org.orekit.errors.OrekitMessages;
* This class is the single point of access for all data loading features. It
* is used for example to load Earth Orientation Parameters used by IERS frames,
* to load UTC leap seconds used by time scales, to load planetary ephemerides ...
* <p>
*
* </p>
* <p>
* It is user-customizable: users can add their own data providers at will. This
* allows them for example to use a database or an existing data loading library
* in order to embed an Orekit enabled application in a global system with its
......
......@@ -59,7 +59,7 @@ import org.orekit.errors.OrekitException;
* System.setProperty("http.nonProxyHosts", "localhost|*.your.domain.com");
* Authenticator.setDefault(new AuthenticatorDialog());
* </pre>
* </p>
*
* <p>
* Gzip-compressed files are supported.
* </p>
......
......@@ -20,14 +20,14 @@ import org.orekit.errors.OrekitException;
import org.orekit.utils.ParameterDriver;
/** Interface representing a scalar function depending on a {@link ParameterDriver}.
* @see EstimationUtils#differentiate(ParameterFunction ParameterDriver, int, double)
* @see EstimationUtils#differentiate(ParameterFunction, ParameterDriver, int, double)
* @author Luc Maisonobe
* @since 8.0
*/
public interface ParameterFunction {
/** Evaluate the function.
* @param parameterDriver friver for the parameter.
* @param parameterDriver driver for the parameter.
* @return scalar value of the function
* @throws OrekitException if evaluation cannot be performed
*/
......
......@@ -261,7 +261,7 @@ public class BatchLSEstimator {
* the scale is often small (typically about 1 m for orbital positions
* for example), then the threshold should not be too small. A value
* of 10⁻³ is often quite accurate.
* </>
*
* @param parametersConvergenceThreshold convergence threshold on
* normalized parameters (dimensionless, related to parameters scales)
* @see EvaluationRmsChecker
......
......@@ -36,7 +36,7 @@ import org.orekit.utils.ParameterDriver;
* <li>ground station displacements due to tidal effects</li>
* <li>...</li>
* </ul>
* </p>
*
* @param <T> the type of the measurement
* @author Luc Maisonobe
* @since 8.0
......
......@@ -32,7 +32,7 @@ import org.orekit.utils.ParameterDriver;
* <li>estimate the theoretical value of a measurement,</li>
* <li>compute the corresponding partial derivatives (with respect to state and parameters)</li>
* </ul>
* </p>
*
* <p>
* The estimated theoretical values can be modified by registering one or several {@link
* EstimationModifier EstimationModifier} objects. These objects will manage notions
......
......@@ -154,7 +154,7 @@ public enum Keyword {
MAN_EPOCH_IGNITION,
/** Maneuver duration (If = 0, impulsive maneuver). */
MAN_DURATION,
/** Mass change during maneuver (value is < 0). */
/** Mass change during maneuver (value is &lt; 0). */
MAN_DELTA_MASS,
/** Coordinate system for velocity increment vector. Its value can either be RSW, RTN (both
* indicating "Radial, Transverse, Normal") or TNW. */
......
......@@ -16,14 +16,6 @@
*/
package org.orekit.files.ccsds;
import java.io.FileInputStream;
import java.io.FileNotFoundException;
import java.io.IOException;
import java.io.InputStream;
import java.util.List;
import java.util.regex.Matcher;
import java.util.regex.Pattern;
import org.hipparchus.util.FastMath;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitInternalError;
......@@ -35,17 +27,26 @@ import org.orekit.time.TimeScalesFactory;
import org.orekit.utils.Constants;
import org.orekit.utils.IERSConventions;
/** Base class for all CCSDS Orbit Data Message parsers.
* <p>
* This base class is immutable, and hence thread safe. When parts
* must be changed, such as reference date for Mission Elapsed Time or
* Mission Relative Time time systems, or the gravitational coefficient or
* the IERS conventions, the various {@code withXxx} methods must be called,
* which create a new immutable instance with the new parameters. This
* is a combination of the <a href="">builder design pattern</a> and
* a <a href="http://en.wikipedia.org/wiki/Fluent_interface">fluent
import java.io.FileInputStream;
import java.io.FileNotFoundException;
import java.io.IOException;
import java.io.InputStream;
import java.util.List;
import java.util.regex.Matcher;
import java.util.regex.Pattern;
/**
* Base class for all CCSDS Orbit Data Message parsers.
*
* <p> This base class is immutable, and hence thread safe. When parts must be
* changed, such as reference date for Mission Elapsed Time or Mission Relative
* Time time systems, or the gravitational coefficient or the IERS conventions,
* the various {@code withXxx} methods must be called, which create a new
* immutable instance with the new parameters. This is a combination of the <a
* href="https://en.wikipedia.org/wiki/Builder_pattern">builder design
* pattern</a> and a <a href="http://en.wikipedia.org/wiki/Fluent_interface">fluent
* interface</a>.
* </p>
*
* @author Luc Maisonobe
* @since 6.1
*/
......
......@@ -52,8 +52,10 @@ public class OEMParser extends ODMParser implements OrbitFileParser {
* Mission Relative Time time systems, or the gravitational coefficient or
* the IERS conventions, the various {@code withXxx} methods must be called,
* which create a new immutable instance with the new parameters. This
* is a combination of the <a href="">builder design pattern</a> and
* a <a href="http://en.wikipedia.org/wiki/Fluent_interface">fluent
* is a combination of the
* <a href="https://en.wikipedia.org/wiki/Builder_pattern">builder design
* pattern</a> and a
* <a href="http://en.wikipedia.org/wiki/Fluent_interface">fluent
* interface</a>.
* </p>
* <p>
......
......@@ -44,8 +44,10 @@ public class OMMParser extends ODMParser implements OrbitFileParser {
* Mission Relative Time time systems, or the gravitational coefficient or
* the IERS conventions, the various {@code withXxx} methods must be called,
* which create a new immutable instance with the new parameters. This
* is a combination of the <a href="">builder design pattern</a> and
* a <a href="http://en.wikipedia.org/wiki/Fluent_interface">fluent
* is a combination of the
* <a href="https://en.wikipedia.org/wiki/Builder_pattern">builder design
* pattern</a> and a
* <a href="http://en.wikipedia.org/wiki/Fluent_interface">fluent
* interface</a>.
* </p>
* <p>
......
......@@ -304,15 +304,15 @@ public class OPMFile extends OGMFile {
this.duration = duration;
}
/** Get mass change during maneuver (value is < 0).
* @return mass change during maneuver (value is < 0)
/** Get mass change during maneuver (value is &lt; 0).
* @return mass change during maneuver (value is &lt; 0)
*/
public double getDeltaMass() {
return deltaMass;
}
/** Set mass change during maneuver (value is < 0).
* @param deltaMass mass change during maneuver (value is < 0)
/** Set mass change during maneuver (value is &lt; 0).
* @param deltaMass mass change during maneuver (value is &lt; 0)
*/
public void setDeltaMass(final double deltaMass) {
this.deltaMass = deltaMass;
......
......@@ -44,8 +44,10 @@ public class OPMParser extends ODMParser implements OrbitFileParser {
* Mission Relative Time time systems, or the gravitational coefficient or
* the IERS conventions, the various {@code withXxx} methods must be called,
* which create a new immutable instance with the new parameters. This
* is a combination of the <a href="">builder design pattern</a> and
* a <a href="http://en.wikipedia.org/wiki/Fluent_interface">fluent
* is a combination of the
* <a href="https://en.wikipedia.org/wiki/Builder_pattern">builder design
* pattern</a> and a
* <a href="http://en.wikipedia.org/wiki/Fluent_interface">fluent
* interface</a>.
* </p>
* <p>
......
......@@ -35,7 +35,7 @@ import org.orekit.utils.ParameterDriver;
* Objects implementing this interface are intended to be added to a
* {@link org.orekit.propagation.numerical.NumericalPropagator numerical propagator}
* before the propagation is started.
* <p>
*
* <p>
* The propagator will call at each step the {@link #addContribution(SpacecraftState,
* TimeDerivativesEquations)} method. The force model instance will extract all the
......
......@@ -60,7 +60,7 @@ import org.orekit.utils.PVCoordinatesProvider;
* {@link org.orekit.forces.drag.DragForce drag force model}
* computation.</li>
* </ul>
*</p>
*
*<p>
* This model provides dense output for altitudes beyond 120 km. Computed data are:
* <ul>
......@@ -72,7 +72,7 @@ import org.orekit.utils.PVCoordinatesProvider;
* <li>Partial densities in (kg/m³) : hydrogen, helium, atomic oxygen,
* molecular nitrogen, molecular oxygen, atomic nitrogen</li>
* </ul>
* </p>
*
* <p>
* The model needs geographical and time information to compute general values,
* but also needs space weather data : mean and instantaneous solar flux and
......@@ -83,8 +83,8 @@ import org.orekit.utils.PVCoordinatesProvider;
* flux can be set to the mean value if the data is not available. Geomagnetic
* activity is represented by the Kp indice, which goes from 1 (very low activity) to
* 9 (high activity).
*
* <p>
* </p>
* All these data can be found on the <a href="http://sec.noaa.gov/Data/index.html">
* NOAA (National Oceanic and Atmospheric Administration) website.</a>
* </p>
......@@ -202,12 +202,12 @@ public class DTM2000 implements Atmosphere {
private double[] cachedFbar = new double[3];
/** Kp coefficients.
* <p><ul>
* <ul>
* <li>akp[1] = 3-hourly kp</li>
* <li>akp[2] = 0 (not used)</li>
* <li>akp[3] = mean kp of last 24 hours</li>
* <li>akp[4] = 0 (not used)</li>
* </ul></p>
* </ul>
*/
private double[] akp = new double[5];
......
......@@ -135,7 +135,7 @@ public class HarrisPriester implements Atmosphere {
/** Simple constructor for Modified Harris-Priester atmosphere model.
* <p>The cosine exponent value is set to 4 by default.</p>
* <p>The default embedded density table is the one given in the referenced
* book from Montenbruck & Gill. It is given for mean solar activity and
* book from Montenbruck &amp; Gill. It is given for mean solar activity and
* spreads over 100 to 1000 km.</p>
* @param sun the sun position
* @param earth the earth body shape
......@@ -149,7 +149,7 @@ public class HarrisPriester implements Atmosphere {
* <p>Recommanded values for the cosine exponent spread over the range
* 2, for low inclination orbits, to 6, for polar orbits.</p>
* <p> The default embedded density table is the one given in the referenced
* book from Montenbruck & Gill. It is given for mean solar activity and
* book from Montenbruck &amp; Gill. It is given for mean solar activity and
* spreads over 100 to 1000 km. </p>
* @param sun the sun position
* @param earth the earth body shape
......@@ -168,9 +168,9 @@ public class HarrisPriester implements Atmosphere {
* <li>tabAltRho[][1] = min density (kg/m³)</li>
* <li>tabAltRho[][2] = max density (kg/m³)</li>
* </ul>
* The altitude must be increasing without limitation in range.<br>
* The internal density table is a copy of the provided one.
* </p>
* <p> The altitude must be increasing without limitation in range. The
* internal density table is a copy of the provided one.
*
* <p>The cosine exponent value is set to 4 by default.</p>
* @param sun the sun position
* @param earth the earth body shape
......@@ -191,9 +191,9 @@ public class HarrisPriester implements Atmosphere {
* <li>tabAltRho[][1] = min density (kg/m³)</li>
* <li>tabAltRho[][2] = max density (kg/m³)</li>
* </ul>
* The altitude must be increasing without limitation in range.<br>
* The internal density table is a copy of the provided one.
* </p>
* <p> The altitude must be increasing without limitation in range. The
* internal density table is a copy of the provided one.
*
* @param sun the sun position
* @param earth the earth body shape
* @param tabAltRho the density table
......@@ -238,8 +238,8 @@ public class HarrisPriester implements Atmosphere {
* <li>tabAltRho[][1] = min density (kg/m³)</li>
* <li>tabAltRho[][2] = max density (kg/m³)</li>
* </ul>
* The altitude must be increasing without limitation in range.
* </p>
* <p> The altitude must be increasing without limitation in range.
*
* <p>
* The returned density table is a copy of the current one.
* </p>
......
......@@ -49,7 +49,7 @@ import org.orekit.utils.PVCoordinatesProvider;
* {@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>
......@@ -57,7 +57,7 @@ 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 threw
......@@ -183,10 +183,10 @@ public class JB2006 implements Atmosphere {
};
/** Temperatures.
* <p><ul>
* <ul>
* <li>TEMP(1): Exospheric Temperature above Input Position (deg K)</li>
* <li>TEMP(2): Temperature at Input Position (deg K)</li>
* </ul></p>
* </ul>
*/
private double[] temp = new double[3];
......
......@@ -303,6 +303,7 @@ public class MarshallSolarActivityFutureEstimation implements DTM2000InputParame
* 5 is 5 and 5+ is 5 1/3. The ap (equivalent range) index is derived from
* the Kp index as follows:</p>
* <table border="1">
* <caption>Kp / Ap Conversion Table</caption>
* <tbody>
* <tr>
* <td>Kp</td><td>0o</td><td>0+</td><td>1-</td><td>1o</td><td>1+</td><td>2-</td><td>2o</td><td>2+</td><td>3-</td><td>3o</td><td>3+</td><td>4-</td><td>4o</td><td>4+</td>
......
......@@ -59,12 +59,10 @@ import org.orekit.utils.ParameterObserver;
* Holmes-Featherstone model} rather than this class.
* </p>
* <p>
* As this class uses finite differences to compute derivatives, the steps for
* finite differences <strong>must</strong> be initialized by calling {@link
* #setSteps(double, double)} prior to use derivatives, otherwise an exception
* will be thrown by {@link #accelerationDerivatives(AbsoluteDate, Frame, FieldVector3D,
* FieldVector3D, FieldRotation, DerivativeStructure)} and by {@link
* #accelerationDerivatives(SpacecraftState, String)}.
* This class uses finite differences to compute derivatives and the steps for
* finite differences are initialized in the {@link
* #CunninghamAttractionModel(Frame, UnnormalizedSphericalHarmonicsProvider,
* double) constructor}.
* </p>
*
* @see HolmesFeatherstoneAttractionModel
......
......@@ -56,12 +56,10 @@ import org.orekit.utils.ParameterObserver;
* Holmes-Featherstone model} rather than this class.
* </p>
* <p>
* As this class uses finite differences to compute derivatives, the steps for
* finite differences <strong>must</strong> be initialized by calling {@link
* #setSteps(double, double)} prior to use derivatives, otherwise an exception
* will be thrown by {@link #accelerationDerivatives(AbsoluteDate, Frame, FieldVector3D,
* FieldVector3D, FieldRotation, DerivativeStructure)} and by {@link
* #accelerationDerivatives(SpacecraftState, String)}.
* This class uses finite differences to compute derivatives and the steps for
* finite differences are initialized in the {@link
* #DrozinerAttractionModel(Frame, UnnormalizedSphericalHarmonicsProvider,
* double) constructor}
* </p>
*
* @see HolmesFeatherstoneAttractionModel
......
......@@ -20,7 +20,7 @@ import org.orekit.time.AbsoluteDate;
/**
* Interface used to provide spherical harmonics coefficients.
* <p/>
* <p>
* Two interfaces are provided to distinguish between normalized and un-normalized
* coefficients: {@link NormalizedSphericalHarmonicsProvider} and {@link
* UnnormalizedSphericalHarmonicsProvider}. To account for gravity pertubations all
......
......@@ -39,14 +39,14 @@ import org.orekit.utils.Constants;
* <p>These effect are computed analytically using two Jacobian matrices:
* <ol>
* <li>J₀: Jacobian of Keplerian or equinoctial elements with respect
* to cartesian parameters at date t₀</li> allows to compute
* maneuver effect as a change in orbital elements at maneuver date t₀,
* to cartesian parameters at date t₀ allows to compute
* maneuver effect as a change in orbital elements at maneuver date t₀,</li>
* <li>J<sub>1/0</sub>: Jacobian of Keplerian or equinoctial elements
* at date t₁ with respect to Keplerian or equinoctial elements
* at date t₀</li> allows to propagate the change in orbital elements
* to final date t₁.
* at date t₀ allows to propagate the change in orbital elements
* to final date t₁.</li>
* </ol>
* </p>
*
* <p>
* The second Jacobian, J<sub>1/0</sub>, is computed using a simple Keplerian
* model, i.e. it is the identity except for the mean motion row which also includes
......
......@@ -31,6 +31,7 @@ import org.orekit.utils.ParameterDriver;
import org.orekit.utils.ParameterObserver;
/** This class represents the features of a simplified spacecraft.
*
* <p>This model uses the coefficients described in the collective
* book edited by CNES in 1995: Spaceflight Dynamics (part I), in
* section 5.2.2.1.3.1 (page 296 of the English edition). The absorption
......@@ -40,12 +41,12 @@ import org.orekit.utils.ParameterObserver;
* Some authors prefer to express thermo-optical properties for surfaces
* using the following coefficients: Ka = α, Ks = (1-α)τ, Kd = (1-α)(1-τ)
* </pre>
* Ka is the same absorption coefficient, and Ks is also called specular
* <p> Ka is the same absorption coefficient, and Ks is also called specular
* reflection coefficient, which leads to a confusion. In fact, as the Ka,
* Ks and Kd coefficients are the most frequently used ones (using the
* names Ca, Cs and Cd), when speaking about reflection coefficients, it
* is more often Cd that is considered rather than τ.
* </p>
*
* <p>
* The classical set of coefficients Ca, Cs, and Cd are implemented in the
* sister class {@link IsotropicRadiationClassicalConvention}, which should
......
......@@ -35,7 +35,7 @@ import org.orekit.time.TimeFunction;
* It <strong>must</strong> be used with the Earth Rotation Angle (REA) defined by
* Capitaine's model and <strong>not</strong> IAU-82 sidereal
* time which is consistent with the older models only.</p>
* <p>Its parent frame is the GCRF frame.<p>
* <p>Its parent frame is the GCRF frame.
*/
class CIRFProvider implements EOPBasedTransformProvider {
......
......@@ -26,7 +26,7 @@ import org.orekit.utils.Constants;
/** EME2000 frame : mean equator at J2000.0.
* <p>This frame was the standard inertial reference prior to GCRF. It was defined
* using Lieske precession-nutation model for Earth. This frame has been superseded
* by GCRF which is implicitly defined from a few hundred quasars coordinates.<p>
* by GCRF which is implicitly defined from a few hundred quasars coordinates.
* <p>The transformation between GCRF and EME2000 is a constant rotation bias.</p>
* @author Luc Maisonobe
*/
......
......@@ -26,7 +26,7 @@ import org.orekit.time.AbsoluteDate;
/** Tridimensional references frames class.
*
* <h5> Frame Presentation </h5>
* <h1> Frame Presentation </h1>
* <p>This class is the base class for all frames in OREKIT. The frames are
* linked together in a tree with some specific frame chosen as the root of the tree.
* Each frame is defined by {@link Transform transforms} combining any number
......
......@@ -37,7 +37,7 @@ import org.orekit.utils.OrekitConfiguration;
/** Factory for predefined reference frames.
*
* <h5> FramesFactory Presentation </h5>
* <h1> FramesFactory Presentation </h1>
* <p>
* Several predefined reference {@link Frame frames} are implemented in OREKIT.
* They are linked together in a tree with the <i>Geocentric
......@@ -50,7 +50,7 @@ import org.orekit.utils.OrekitConfiguration;
* <li>set up interpolation/caching features for some frames that may induce costly computation</li>
* <li>streamline the {@link EOPHistory Earth Orientation Parameters} history loading.</li>
* </ul>
* <h5> Reference Frames </h5>
* <h2> Reference Frames </h2>
* <p>
* The user can retrieve those reference frames using various static methods, the most
* important ones being: {@link #getFrame(Predefined)}, {@link #getGCRF()},
......@@ -60,7 +60,7 @@ import org.orekit.utils.OrekitConfiguration;
* {@link #getGTOD(IERSConventions, boolean)}, {@link #getITRFEquinox(IERSConventions, boolean)},
* {@link #getTEME()} and {@link #getVeis1950()}.
* </p>
* <h5> International Terrestrial Reference Frame</h5>
* <h2> International Terrestrial Reference Frame</h2>
* <p>
* This frame is the current (as of 2013) reference realization of
* the International Terrestrial Reference System produced by IERS.
......@@ -96,14 +96,14 @@ import org.orekit.utils.OrekitConfiguration;
* choice of IERS conventions (i.e. the choice of precession/nutation models) can
* be made independently by user, Orekit provides all alternatives.
* </p>
* <h5>Intermediate frames</h5>
* <h2>Intermediate frames</h2>
* <p>
* Orekit also provides all the intermediate frames that are needed to transform
* between GCRF and ITRF, along the two paths: ITRF/TIRF/CIRF/GCRF for the
* non-rotating origin paradigm and ITRF/GTOD/TOD/MOD/EME2000/GCRF for the equinox
* paradigm.
* </p>
* <h5> Earth Orientation Parameters </h5>
* <h2> Earth Orientation Parameters </h2>
* <p>
* This factory also handles loading of Earth Orientation Parameters (EOP) needed
* for accurate transformations between inertial and Earth fixed frames, using
......
......@@ -35,7 +35,7 @@ import org.orekit.utils.PVCoordinates;
* includes translation, velocity, rotation, rotation rate and scale factor.
* The scale factor is useful for coordinates near Earth surface, but it
* cannot be extended to outer space as it would correspond to a non-unitary
* transform. Therefore, the scale factor is <em>not</em> used here.<p>
* transform. Therefore, the scale factor is <em>not</em> used here.
*
* <p>Instances of this class are guaranteed to be immutable.</p>
*
......
......@@ -35,7 +35,7 @@ public enum LOFType {
* <li>Y<sub>TNW</sub> = -Z<sub>VNC</sub></li>
* <li>Z<sub>TNW</sub> = Y<sub>VNC</sub></li>
* </ul>
* </p>
*
* @see #VNC
*/
TNW {
......@@ -58,7 +58,7 @@ public enum LOFType {
* <li>Y<sub>QSW/LVLH</sub> = X<sub>VVLH</sub></li>
* <li>Z<sub>QSW/LVLH</sub> = -Y<sub>VVLH</sub></li>
* </ul>
* </p>
*
* @see #LVLH
* @see #VVLH
*/
......@@ -82,7 +82,7 @@ public enum LOFType {
* <li>Y<sub>LVLH/QSW</sub> = X<sub>VVLH</sub></li>
* <li>Z<sub>LVLH/QSW</sub> = -Y<sub>VVLH</sub></li>
* </ul>
* </p>
*
* @see #QSW
* @see #VVLH
*/
......@@ -103,7 +103,7 @@ public enum LOFType {
* <li>Y<sub>VVLH</sub> = -Z<sub>QSW/LVLH</sub></li>
* <li>Z<sub>VVLH</sub> = -X<sub>QSW/LVLH</sub></li>
* </ul>
* </p>
*
* @see #QSW
* @see #LVLH
*/
......@@ -124,7 +124,7 @@ public enum LOFType {
* <li>Y<sub>VNC</sub> = Z<sub>TNW</sub></li>
* <li>Z<sub>VNC</sub> = -Y<sub>TNW</sub></li>
* </ul>
* </p>
*
* @see #TNW
*/
VNC {
......
......@@ -30,8 +30,8 @@ import org.orekit.utils.IERSConventions;
/** Mean Equator, Mean Equinox Frame.
* <p>This frame handles precession effects according to to selected IERS conventions.</p>
* <p>Its parent frame is the GCRF frame.<p>
* <p>It is sometimes called Mean of Date (MoD) frame.<p>
* <p>Its parent frame is the GCRF frame.
* <p>It is sometimes called Mean of Date (MoD) frame.
* @author Pascal Parraud
*/
class MODProvider implements TransformProvider {
......
......@@ -53,11 +53,11 @@ import org.orekit.utils.TimeStampedPVCoordinates;
* <p> The convention used in OREKIT is vectorial transformation. It means
* that a transformation is defined as a transform to apply to the
* coordinates of a vector expressed in the old frame to obtain the
* same vector expressed in the new frame.<p>
* same vector expressed in the new frame.
*
* <p>Instances of this class are guaranteed to be immutable.</p>
*
* <h5> Example </h5>
* <h1> Example </h1>
*
* <pre>
*
......@@ -618,12 +618,12 @@ public class Transform
* <pre>
* PV₁ = transform.transformPVCoordinates(PV₀), then
* </pre>
* their differentials dPV₁ and dPV₀ will obey the following relation
* where J is the matrix computed by this method:<br/>
* <p> 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>
* </p>
*
* @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,
* velocities and accelerations)
......
......@@ -27,7 +27,7 @@ import org.orekit.time.TimeScalesFactory;
import org.orekit.utils.Constants;
/** Veis 1950 Frame.
* <p>Its parent frame is the {@link GTODProvider} without EOP correction application.<p>
* <p>Its parent frame is the {@link GTODProvider} without EOP correction application.
* <p>This frame is mainly provided for consistency with legacy softwares.</p>
* @author Pascal Parraud
*/
......
......@@ -117,8 +117,8 @@ public class DOPComputer {
/**
* Compute the {@link DOP} at a given date for a set of GNSS spacecrafts.
* <p>Four GNSS spacecraft at least are needed to compute the DOP.<br/>
* If less than 4 propagators are provided, an exception will be thrown.<br/>
* <p>Four GNSS spacecraft at least are needed to compute the DOP.
* If less than 4 propagators are provided, an exception will be thrown.
* If less than 4 spacecrafts are visible at the date, all DOP values will be
* set to {@link java.lang.Double#NaN NaN}.</p>
*
......
......@@ -24,7 +24,7 @@ import org.orekit.time.AbsoluteDate;
/**
* This class holds a GPS almanac as read from SEM or YUMA files.
*
* <p>Depending on the source (SEM or YUMA), some fields may be filled in or not.<br/>
* <p>Depending on the source (SEM or YUMA), some fields may be filled in or not.
* An almanac read from a YUMA file doesn't hold SVN number, average URA and satellite
* configuration.</p>
*
......
......@@ -86,8 +86,8 @@ public class EarthITU453AtmosphereRefraction implements AtmosphericRefractionMod
/** refraction correction value where elevation+refraction correction is minimal (near inequality 11 validity domain). */
private final double refrac_star;
/** Creates a new default instance.
* * @param altitude altitude of the ground station from which measurement is performed (m)
/** Creates a new default instance.
* @param altitude altitude of the ground station from which measurement is performed (m)
*/
public EarthITU453AtmosphereRefraction(final double altitude) {
this.altitude = altitude;
......
......@@ -49,7 +49,7 @@ public class MariniMurrayModel implements TroposphericModel {
* environmental conditions.
* @param t0 the temperature at the station, K
* @param p0 the atmospheric pressure at the station, mbar
* @param rh the humidity at the station, percent (50% -> 0.5)
* @param rh the humidity at the station, percent (50% -&gt; 0.5)
* @param latitude site latitude
* @param lambda laser wavelength (c/f), nm
*/
......@@ -65,13 +65,13 @@ public class MariniMurrayModel implements TroposphericModel {
}
/** Create a new Marini-Murray model using a standard atmosphere model.
* <p>
*
* <ul>
* <li>temperature: 20 degree Celsius
* <li>pressure: 1013.25 mbar
* <li>humidity: 50%
* </ul>
* </p>
*
* @param latitude site latitude
* @param frequency laser frequency, Hz
*
......
......@@ -169,7 +169,7 @@ public class ReferenceEllipsoid extends OneAxisEllipsoid implements EarthShape {
* Get the fully normalized coefficient C<sub>2n,0</sub> for the normal
* gravity potential.
*
* @param n index in C<sub>2n,0</sub>, n >=1.
* @param n index in C<sub>2n,0</sub>, n &gt;= 1.
* @return normalized C<sub>2n,0</sub> of the ellipsoid
* @see "Department of Defense World Geodetic System 1984. 2000. NIMA TR
* 8350.2 Third Edition, Amendment 1."
......
......@@ -99,7 +99,7 @@ public class SaastamoinenModel implements TroposphericModel {
* environmental conditions.
* @param t0 the temperature at the station [K]
* @param p0 the atmospheric pressure at the station [mbar]