List of usage examples for org.apache.commons.math.geometry Vector3D PLUS_K
Vector3D PLUS_K
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From source file:org.orekit.frames.EME2000Frame.java
/** Simple constructor. * @param name name of the frame/*from w w w . j av a 2 s. c om*/ */ protected EME2000Frame(final String name) { super(FramesFactory.getGCRF(), null, name, true); // build the bias transform final Rotation r1 = new Rotation(Vector3D.PLUS_I, D_EPSILON_B); final Rotation r2 = new Rotation(Vector3D.PLUS_J, -D_PSI_B * Math.sin(EPSILON_0)); final Rotation r3 = new Rotation(Vector3D.PLUS_K, -ALPHA_0); final Rotation bias = r1.applyTo(r2.applyTo(r3)); // store the bias transform setTransform(new Transform(bias)); }
From source file:org.orekit.frames.ITRF2005Frame.java
/** Update the frame to the given date. * <p>The update considers the pole motion from IERS data.</p> * @param date new value of the date/*from w w w . ja v a 2s .c om*/ * @exception OrekitException if the nutation model data embedded in the * library cannot be read */ protected void updateFrame(final AbsoluteDate date) throws OrekitException { if ((cachedDate == null) || !cachedDate.equals(date)) { // offset from J2000 epoch in julian centuries final double tts = date.durationFrom(AbsoluteDate.J2000_EPOCH); final double ttc = tts / Constants.JULIAN_CENTURY; // pole correction parameters final PoleCorrection pCorr = ((TIRF2000Frame) getParent()).getPoleCorrection(date); final PoleCorrection nCorr = nutationCorrection(date); // elementary rotations due to pole motion in terrestrial frame final Rotation r1 = new Rotation(Vector3D.PLUS_I, -(pCorr.getYp() + nCorr.getYp())); final Rotation r2 = new Rotation(Vector3D.PLUS_J, -(pCorr.getXp() + nCorr.getXp())); final Rotation r3 = new Rotation(Vector3D.PLUS_K, S_PRIME_RATE * ttc); // complete pole motion in terrestrial frame final Rotation wRot = r3.applyTo(r2.applyTo(r1)); // combined effects final Rotation combined = wRot.revert(); // set up the transform from parent TIRF setTransform(new Transform(combined, Vector3D.ZERO)); cachedDate = date; } }
From source file:org.orekit.frames.LocalOrbitalFrame.java
/** {@inheritDoc} */ protected void updateFrame(final AbsoluteDate date) throws OrekitException { // get position/velocity with respect to parent frame final PVCoordinates pv = provider.getPVCoordinates(date, getParent()); final Vector3D p = pv.getPosition(); final Vector3D v = pv.getVelocity(); final Vector3D momentum = pv.getMomentum(); // compute the translation part of the transform final Transform translation = new Transform(p.negate(), v.negate()); // compute the rotation part of the transform final Rotation r = new Rotation((type == LOFType.TNW) ? v : p, momentum, Vector3D.PLUS_I, Vector3D.PLUS_K); final Transform rotation = new Transform(r, new Vector3D(1.0 / p.getNormSq(), r.applyTo(momentum))); // update the frame defining transform setTransform(new Transform(translation, rotation)); }
From source file:org.orekit.frames.MEMEFrame.java
/** Update the frame to the given date. * <p>The update considers the precession effects.</p> * @param date new value of the date//w w w . j a v a 2 s . c o m */ protected void updateFrame(final AbsoluteDate date) { if ((cachedDate == null) || !cachedDate.equals(date)) { // offset from J2000 epoch in julian centuries final double tts = date.durationFrom(AbsoluteDate.J2000_EPOCH); final double ttc = tts / Constants.JULIAN_CENTURY; // compute the zeta precession angle final double zeta = ((ZETA_3 * ttc + ZETA_2) * ttc + ZETA_1) * ttc; // compute the theta precession angle final double theta = ((THETA_3 * ttc + THETA_2) * ttc + THETA_1) * ttc; // compute the z precession angle final double z = ((Z_3 * ttc + Z_2) * ttc + Z_1) * ttc; // elementary rotations for precession final Rotation r1 = new Rotation(Vector3D.PLUS_K, z); final Rotation r2 = new Rotation(Vector3D.PLUS_J, -theta); final Rotation r3 = new Rotation(Vector3D.PLUS_K, zeta); // complete precession final Rotation precession = r1.applyTo(r2.applyTo(r3)); // set up the transform from parent GCRF setTransform(new Transform(precession)); cachedDate = date; } }
From source file:org.orekit.frames.PEFFrame.java
/** Update the frame to the given date. * <p>The update considers the earth rotation from IERS data.</p> * @param date new value of the date/*from www. java 2 s.c o m*/ * @exception OrekitException if the nutation model data embedded in the * library cannot be read */ protected void updateFrame(final AbsoluteDate date) throws OrekitException { if ((cachedDate == null) || !cachedDate.equals(date)) { // offset from J2000.0 epoch final double tts = date.durationFrom(AbsoluteDate.J2000_EPOCH); // evaluate the nutation elements setInterpolatedNutationElements(tts); // offset from J2000 epoch in julian centuries final double ttc = tts / Constants.JULIAN_CENTURY; // compute the mean obliquity of the ecliptic moe = ((MOE_3 * ttc + MOE_2) * ttc + MOE_1) * ttc + MOE_0; final double eqe = getNewEquationOfEquinoxes(date, ttc); // offset in julian centuries from J2000 epoch (UT1 scale) final double dtai = date.durationFrom(GMST_REFERENCE); final double dutc = TimeScalesFactory.getUTC().offsetFromTAI(date); final double dut1 = eopHistory.getUT1MinusUTC(date); final double tut1 = dtai + dutc + dut1; final double tt = tut1 / Constants.JULIAN_CENTURY; // Seconds in the day, adjusted by 12 hours because the // UT1 is supplied as a Julian date beginning at noon. final double sd = (tut1 + Constants.JULIAN_DAY / 2.) % Constants.JULIAN_DAY; // compute Greenwich mean sidereal time, in radians final double gmst = (((GMST_3 * tt + GMST_2) * tt + GMST_1) * tt + GMST_0 + sd) * RADIANS_PER_SECOND; // compute Greenwich apparent sidereal time, in radians final double gast = gmst + eqe; // compute true angular rotation of Earth, in rad/s final double lod = ((TEMEFrame) getParent()).isEOPCorrectionApplied() ? eopHistory.getLOD(date) : 0.0; final double omp = AVE * (1 - lod / Constants.JULIAN_DAY); final Vector3D rotationRate = new Vector3D(omp, Vector3D.PLUS_K); // set up the transform from parent TEME setTransform(new Transform(new Rotation(Vector3D.PLUS_K, -gast), rotationRate)); cachedDate = date; } }
From source file:org.orekit.frames.TEMEFrame.java
/** Update the frame to the given date. * <p>The update considers the nutation effects from IERS data.</p> * @param date new value of the date//from w w w . j a va 2 s . co m * @exception OrekitException if the nutation model data embedded in the * library cannot be read */ protected void updateFrame(final AbsoluteDate date) throws OrekitException { if ((cachedDate == null) || !cachedDate.equals(date)) { // offset from J2000.0 epoch final double tts = date.durationFrom(AbsoluteDate.J2000_EPOCH); // evaluate the nutation elements setInterpolatedNutationElements(tts); // offset from J2000 epoch in julian centuries final double ttc = tts / Constants.JULIAN_CENTURY; // compute the mean obliquity of the ecliptic moe = ((MOE_3 * ttc + MOE_2) * ttc + MOE_1) * ttc + MOE_0; // get the IAU1980 corrections for the nutation parameters final NutationCorrection nutCorr = (eopHistory == null) ? NutationCorrection.NULL_CORRECTION : eopHistory.getNutationCorrection(date); final double deps = depsCurrent + nutCorr.getDdeps(); final double dpsi = dpsiCurrent + nutCorr.getDdpsi(); // compute the true obliquity of the ecliptic final double toe = moe + deps; // set up the elementary rotations for nutation final Rotation r1 = new Rotation(Vector3D.PLUS_I, toe); final Rotation r2 = new Rotation(Vector3D.PLUS_K, dpsi); final Rotation r3 = new Rotation(Vector3D.PLUS_I, -moe); // complete nutation final Rotation precession = r1.applyTo(r2.applyTo(r3)); // set up the transform from parent MEME setTransform(new Transform(precession)); cachedDate = date; } }
From source file:org.orekit.frames.TIRF2000Frame.java
/** Update the frame to the given date. * <p>The update considers the earth rotation from IERS data.</p> * @param date new value of the date//from ww w.j a va2 s.co m * @exception OrekitException if the nutation model data embedded in the * library cannot be read */ protected void updateFrame(final AbsoluteDate date) throws OrekitException { if ((cachedDate == null) || !cachedDate.equals(date)) { // compute Earth Rotation Angle using Nicole Capitaine model (2000) final double tidalDtu1 = (tidalCorrection == null) ? 0 : tidalCorrection.getDUT1(date); final double dtu1 = eopHistory.getUT1MinusUTC(date); final double utcMinusTai = TimeScalesFactory.getUTC().offsetFromTAI(date); final double tu = (date.durationFrom(ERA_REFERENCE) + utcMinusTai + dtu1 + tidalDtu1) / Constants.JULIAN_DAY; era = ERA_0 + ERA_1A * tu + ERA_1B * tu; era -= TWO_PI * Math.floor((era + Math.PI) / TWO_PI); // set up the transform from parent CIRF final Vector3D rotationRate = new Vector3D((ERA_1A + ERA_1B) / Constants.JULIAN_DAY, Vector3D.PLUS_K); setTransform(new Transform(new Rotation(Vector3D.PLUS_K, -era), rotationRate)); cachedDate = date; } }
From source file:org.orekit.frames.VEISFrame.java
/** Update the frame to the given date. * @param date new value of the date/*from w w w .jav a 2 s. c om*/ * @exception OrekitException if data embedded in the library cannot be read */ protected void updateFrame(final AbsoluteDate date) throws OrekitException { if ((cachedDate == null) || !cachedDate.equals(date)) { // offset from FIFTIES epoch (UT1 scale) final double dtai = date.durationFrom(VST_REFERENCE); final double dutc = TimeScalesFactory.getUTC().offsetFromTAI(date); final double dut1 = eopHistory.getUT1MinusUTC(date); final double tut1 = dtai + dutc + dut1; final double ttd = tut1 / Constants.JULIAN_DAY; final double rdtt = ttd - (int) ttd; // compute Veis sidereal time, in radians final double vst = (VST0 + VST1 * ttd + TWO_PI * rdtt) % TWO_PI; // compute angular rotation of Earth, in rad/s final Vector3D rotationRate = new Vector3D(-VSTD, Vector3D.PLUS_K); // set up the transform from parent PEF setTransform(new Transform(new Rotation(Vector3D.PLUS_K, vst), rotationRate)); cachedDate = date; } }