Examples with TimeStampedPVCoordinates org.orekit.utils.TimeStampedPVCoordinates used on opensource projects

Example 41 with TimeStampedPVCoordinates

use of org.orekit.utils.TimeStampedPVCoordinates in project Orekit by CS-SI.

the class OEMParser method parseEphemeridesDataLines.

/**
 * Parse an ephemeris data line and add its content to the ephemerides
 * block.
 *
 * @param reader the reader
 * @param pi the parser info
 * @exception IOException if an error occurs while reading from the stream
 * @exception OrekitException if a date cannot be parsed
 */
private void parseEphemeridesDataLines(final BufferedReader reader, final ParseInfo pi) throws OrekitException, IOException {
    for (String line = reader.readLine(); line != null; line = reader.readLine()) {
        ++pi.lineNumber;
        if (line.trim().length() > 0) {
            pi.keyValue = new KeyValue(line, pi.lineNumber, pi.fileName);
            if (pi.keyValue.getKeyword() == null) {
                Scanner sc = null;
                try {
                    sc = new Scanner(line);
                    final AbsoluteDate date = parseDate(sc.next(), pi.lastEphemeridesBlock.getMetaData().getTimeSystem());
                    final Vector3D position = new Vector3D(Double.parseDouble(sc.next()) * 1000, Double.parseDouble(sc.next()) * 1000, Double.parseDouble(sc.next()) * 1000);
                    final Vector3D velocity = new Vector3D(Double.parseDouble(sc.next()) * 1000, Double.parseDouble(sc.next()) * 1000, Double.parseDouble(sc.next()) * 1000);
                    Vector3D acceleration = Vector3D.NaN;
                    boolean hasAcceleration = false;
                    if (sc.hasNext()) {
                        acceleration = new Vector3D(Double.parseDouble(sc.next()) * 1000, Double.parseDouble(sc.next()) * 1000, Double.parseDouble(sc.next()) * 1000);
                        hasAcceleration = true;
                    }
                    final TimeStampedPVCoordinates epDataLine;
                    if (hasAcceleration) {
                        epDataLine = new TimeStampedPVCoordinates(date, position, velocity, acceleration);
                    } else {
                        epDataLine = new TimeStampedPVCoordinates(date, position, velocity);
                    }
                    pi.lastEphemeridesBlock.getEphemeridesDataLines().add(epDataLine);
                    pi.lastEphemeridesBlock.updateHasAcceleration(hasAcceleration);
                } catch (NumberFormatException nfe) {
                    throw new OrekitException(OrekitMessages.UNABLE_TO_PARSE_LINE_IN_FILE, pi.lineNumber, pi.fileName, line);
                } finally {
                    if (sc != null) {
                        sc.close();
                    }
                }
            } else {
                switch(pi.keyValue.getKeyword()) {
                    case META_START:
                        pi.lastEphemeridesBlock.setEphemeridesDataLinesComment(pi.commentTmp);
                        pi.commentTmp.clear();
                        pi.lineNumber--;
                        reader.reset();
                        return;
                    case COVARIANCE_START:
                        pi.lastEphemeridesBlock.setEphemeridesDataLinesComment(pi.commentTmp);
                        pi.commentTmp.clear();
                        pi.lineNumber--;
                        reader.reset();
                        return;
                    case COMMENT:
                        pi.commentTmp.add(pi.keyValue.getValue());
                        break;
                    default:
                        throw new OrekitException(OrekitMessages.CCSDS_UNEXPECTED_KEYWORD, pi.lineNumber, pi.fileName, line);
                }
            }
        }
        reader.mark(300);
    }
}

Example 42 with TimeStampedPVCoordinates

use of org.orekit.utils.TimeStampedPVCoordinates in project Orekit by CS-SI.

the class OnBoardAntennaRangeModifier method modify.

/**
 * {@inheritDoc}
 */
@Override
public void modify(final EstimatedMeasurement<Range> estimated) {
    // the participants are ground station at emission, spacecraft, ground station at reception
    final TimeStampedPVCoordinates[] participants = estimated.getParticipants();
    final Vector3D pEmission = participants[0].getPosition();
    final AbsoluteDate transitDate = participants[1].getDate();
    final Vector3D pReception = participants[2].getPosition();
    // transform from spacecraft to inertial frame at transit date
    final SpacecraftState refState = estimated.getStates()[0];
    final SpacecraftState transitState = refState.shiftedBy(transitDate.durationFrom(refState.getDate()));
    final Transform spacecraftToInert = transitState.toTransform().getInverse();
    // compute the geometrical value of the range directly from participants positions.
    // Note that this may be different from the value returned by estimated.getEstimatedValue(),
    // because other modifiers may already have been taken into account
    final Vector3D pSpacecraft = spacecraftToInert.transformPosition(Vector3D.ZERO);
    final double rangeUsingSpacecraftCenter = 0.5 * (Vector3D.distance(pEmission, pSpacecraft) + Vector3D.distance(pSpacecraft, pReception));
    // compute the geometrical value of the range replacing
    // the spacecraft position with antenna phase center position
    final Vector3D pAPC = spacecraftToInert.transformPosition(antennaPhaseCenter);
    final double rangeUsingAntennaPhaseCenter = 0.5 * (Vector3D.distance(pEmission, pAPC) + Vector3D.distance(pAPC, pReception));
    // get the estimated value before this modifier is applied
    final double[] value = estimated.getEstimatedValue();
    // modify the value
    value[0] += rangeUsingAntennaPhaseCenter - rangeUsingSpacecraftCenter;
    estimated.setEstimatedValue(value);
}

Example 43 with TimeStampedPVCoordinates

use of org.orekit.utils.TimeStampedPVCoordinates in project Orekit by CS-SI.

the class OEMWriter method write.

/**
 * {@inheritDoc}
 */
@Override
public void write(final Appendable writer, final EphemerisFile ephemerisFile) throws OrekitException, IOException {
    if (writer == null) {
        throw new OrekitIllegalArgumentException(OrekitMessages.NULL_ARGUMENT, "writer");
    }
    if (ephemerisFile == null) {
        return;
    }
    final String idToProcess;
    if (spaceObjectId != null) {
        if (ephemerisFile.getSatellites().containsKey(spaceObjectId)) {
            idToProcess = spaceObjectId;
        } else {
            throw new OrekitIllegalArgumentException(OrekitMessages.VALUE_NOT_FOUND, spaceObjectId, "ephemerisFile");
        }
    } else if (ephemerisFile.getSatellites().keySet().size() == 1) {
        idToProcess = ephemerisFile.getSatellites().keySet().iterator().next();
    } else {
        throw new OrekitIllegalArgumentException(OrekitMessages.EPHEMERIS_FILE_NO_MULTI_SUPPORT);
    }
    // Get satellite and ephemeris segments to output.
    final EphemerisFile.SatelliteEphemeris satEphem = ephemerisFile.getSatellites().get(idToProcess);
    final List<? extends EphemerisSegment> segments = satEphem.getSegments();
    if (segments.isEmpty()) {
        // no data -> no output
        return;
    }
    final EphemerisSegment firstSegment = segments.get(0);
    final String objectName = this.spaceObjectName == null ? idToProcess : this.spaceObjectName;
    // Only one time scale per OEM file, see Section 5.2.4.5
    final TimeScale timeScale = firstSegment.getTimeScale();
    // metadata that is constant for the whole OEM file
    final Map<Keyword, String> metadata = new LinkedHashMap<>();
    metadata.put(Keyword.TIME_SYSTEM, firstSegment.getTimeScaleString());
    metadata.put(Keyword.ORIGINATOR, this.originator);
    // Only one object in an OEM file, see Section 2.1
    metadata.put(Keyword.OBJECT_ID, idToProcess);
    metadata.put(Keyword.OBJECT_NAME, objectName);
    metadata.put(Keyword.INTERPOLATION, this.interpolationMethod.toString());
    final StreamingOemWriter oemWriter = new StreamingOemWriter(writer, timeScale, metadata);
    oemWriter.writeHeader();
    for (final EphemerisSegment segment : segments) {
        // segment specific metadata
        metadata.clear();
        metadata.put(Keyword.CENTER_NAME, segment.getFrameCenterString());
        metadata.put(Keyword.REF_FRAME, segment.getFrameString());
        metadata.put(Keyword.START_TIME, segment.getStart().toString(timeScale));
        metadata.put(Keyword.STOP_TIME, segment.getStop().toString(timeScale));
        metadata.put(Keyword.INTERPOLATION_DEGREE, String.valueOf(segment.getInterpolationSamples() - 1));
        final Segment segmentWriter = oemWriter.newSegment(null, metadata);
        segmentWriter.writeMetadata();
        for (final TimeStampedPVCoordinates coordinates : segment.getCoordinates()) {
            segmentWriter.writeEphemerisLine(coordinates);
        }
    }
}

Example 44 with TimeStampedPVCoordinates

use of org.orekit.utils.TimeStampedPVCoordinates in project Orekit by CS-SI.

the class EphemerisSegmentPropagator method getPVCoordinates.

@Override
public TimeStampedPVCoordinates getPVCoordinates(final AbsoluteDate date, final Frame frame) throws OrekitException {
    final Stream<TimeStampedPVCoordinates> neighbors = this.cache.getNeighbors(date);
    final TimeStampedPVCoordinates point = TimeStampedPVCoordinates.interpolate(date, ephemeris.getAvailableDerivatives(), neighbors);
    return ephemerisFrame.getTransformTo(frame, date).transformPVCoordinates(point);
}

Example 45 with TimeStampedPVCoordinates

use of org.orekit.utils.TimeStampedPVCoordinates in project Orekit by CS-SI.

the class KeplerianOrbitTest method testPositionAngleDerivatives.

@Test
public void testPositionAngleDerivatives() throws OrekitException {
    final AbsoluteDate date = new AbsoluteDate("2003-05-01T00:00:20.000", TimeScalesFactory.getUTC());
    final Vector3D position = new Vector3D(6896874.444705, 1956581.072644, -147476.245054);
    final Vector3D velocity = new Vector3D(166.816407662, -1106.783301861, -7372.745712770);
    final Vector3D acceleration = new Vector3D(-7.466182457944, -2.118153357345, 0.160004048437);
    final TimeStampedPVCoordinates pv = new TimeStampedPVCoordinates(date, position, velocity, acceleration);
    final Frame frame = FramesFactory.getEME2000();
    final double mu = Constants.EIGEN5C_EARTH_MU;
    final KeplerianOrbit orbit = new KeplerianOrbit(pv, frame, mu);
    for (PositionAngle type : PositionAngle.values()) {
        final KeplerianOrbit rebuilt = new KeplerianOrbit(orbit.getA(), orbit.getE(), orbit.getI(), orbit.getPerigeeArgument(), orbit.getRightAscensionOfAscendingNode(), orbit.getAnomaly(type), orbit.getADot(), orbit.getEDot(), orbit.getIDot(), orbit.getPerigeeArgumentDot(), orbit.getRightAscensionOfAscendingNodeDot(), orbit.getAnomalyDot(type), type, orbit.getFrame(), orbit.getDate(), orbit.getMu());
        Assert.assertThat(rebuilt.getA(), relativelyCloseTo(orbit.getA(), 1));
        Assert.assertThat(rebuilt.getE(), relativelyCloseTo(orbit.getE(), 1));
        Assert.assertThat(rebuilt.getI(), relativelyCloseTo(orbit.getI(), 1));
        Assert.assertThat(rebuilt.getPerigeeArgument(), relativelyCloseTo(orbit.getPerigeeArgument(), 1));
        Assert.assertThat(rebuilt.getRightAscensionOfAscendingNode(), relativelyCloseTo(orbit.getRightAscensionOfAscendingNode(), 1));
        Assert.assertThat(rebuilt.getADot(), relativelyCloseTo(orbit.getADot(), 1));
        Assert.assertThat(rebuilt.getEDot(), relativelyCloseTo(orbit.getEDot(), 1));
        Assert.assertThat(rebuilt.getIDot(), relativelyCloseTo(orbit.getIDot(), 1));
        Assert.assertThat(rebuilt.getPerigeeArgumentDot(), relativelyCloseTo(orbit.getPerigeeArgumentDot(), 1));
        Assert.assertThat(rebuilt.getRightAscensionOfAscendingNodeDot(), relativelyCloseTo(orbit.getRightAscensionOfAscendingNodeDot(), 1));
        for (PositionAngle type2 : PositionAngle.values()) {
            Assert.assertThat(rebuilt.getAnomaly(type2), relativelyCloseTo(orbit.getAnomaly(type2), 1));
            Assert.assertThat(rebuilt.getAnomalyDot(type2), relativelyCloseTo(orbit.getAnomalyDot(type2), 1));
        }
    }
}