List of usage examples for org.apache.commons.math.geometry Rotation applyTo
public Rotation applyTo(Rotation r)
From source file:org.orekit.frames.EME2000Frame.java
/** Simple constructor. * @param name name of the frame//from ww w. ja v a 2s .c o m */ 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/*w w w . ja v a 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 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 a2 s . co 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.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. ja v a 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; // 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; } }