Edit Article: CEP to ITRF

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To transform the coordinates from CEP to ITRF it is necessary to correct the polar motion and the sidereal time (because CEP is a non-rotating system while ITRF is tied to the earth's rotation). Therefore the basic formula to apply is: ::<math> {\mathbf r}_{ITRF}={\mathbf R}_M\; {\mathbf R}_S\; {\mathbf r}_{CEP} \qquad \mbox{(1)} </math> In this case, the computation is easier, Figure 1 shows the needed steps to change from CEP to ITRF. ::[[File:CEP_to_ ITRF_Fig_1.png|none|thumb|640px|'''''Figure 1:''''' CEP to ITRF transformation.]] * '''Diurnal rotation matrix:''' <math>{\mathbf R}_S</math> :This matrix defines a rotation around the CEP pole of angle <math>\Theta_{_G}</math>. That is: :::<math> {\mathbf R}_S={\mathbf R}_3(\Theta_{_G})=\left[ \begin{array}{ccc} \cos \Theta_{_G} & \sin \Theta_{_G} & 0 \\ -\sin \Theta_{_G} & \cos \Theta_{_G} & 0 \\ 0 & 0 & 1 \end{array} \right] \qquad \mbox{(2)} </math> :where <math>\Theta_{_G}</math> is the Greenwich Apparent (=true) Sidereal Time (GAST) <ref group="footnotes"> That is, the hour angle of the true equinox, from Greenwich meridian (see [[Sidereal Time]]).</ref> of date, which is given by: :::<math> \Theta_{_G}=\theta_{_G} +\alpha _E \qquad \mbox{(3)} </math> :where <math>\theta_{_G}</math> is the Greenwich Mean Sidereal Time <ref group="footnotes"> The hour angle of the mean equinox of date, from Greenwich meridian.</ref> (GMST) and <math>\alpha_E</math> is the equinox equation at the observation time <math>UT1</math>, where <ref group="footnotes"> The ratio of universal to sidereal times 1.002737909350795 can be approximately computed as the ratio between <math>24^h</math> and <math>24^h-3^m56^s</math>. A very accurate value is <math>=1.002737909350795+5.9006\,10^{-11}T_u-5.9\,,10^{-15}T_u^2</math>.</ref>: :::<math> \theta_{_G}=1.002737909350795\cdot UT1+\theta_{G_0} \qquad \mbox{(4)} </math> : being <math>\theta_{G_0}</math> the GMST at <math>0^h</math> UT1: :::<math> \theta_{G_0}=6^h41^m 50^s_{\cdot}54841+8640184_{\cdot}^s812866\,T_u+0_{\cdot}^s093104\,T_u^2-6^s_{\cdot}2 \, 10^{-6}\, T_u^3 \qquad \mbox{(5)} </math> :with <math>T_u</math> expressed in centuries of Julian UT1 date: :::<math> T_u=\displaystyle \frac{(\mbox{Julian } UT1 \mbox{ date})-2\,451\,545.0}{36\,525} \qquad \mbox{(6)} </math> :The <math>\alpha_E</math> is the difference between the hour angle of the true equinox (<math>\gamma_{_T}</math>) of date and the mean equinox (<math>\gamma_{_M}</math>) of date <ref group="footnotes"> That is, between the GAST and GMST. This difference is called Equation of Equinoxes.</ref>, difference which is due to the nutation of earth and can be computed from: :::<math> \alpha _E=\tan ^{-1}\left( \frac{{\mathbf N}_{12}}{{\mathbf N}_{11}}\right) \qquad \mbox{(7)} </math> :where <math>{\mathbf N}_{ij}</math> is the component of the row <math>i</math> and column <math>j</math> of the Nutation Matrix (8) (see [[ICRF to CEP]]). Note that the sidereal time (GAST or GMST) is always measured from true Greenwich meridian. ::<math> \begin{array}{c} \begin{array}{c} {\mathbf N}={\mathbf R}_{1}\left( -(\varepsilon +\Delta \varepsilon )\right) \; {\mathbf R}_{3}\left( -\Delta \psi \right) \; {\mathbf R}_{1}\left( \varepsilon \right) = \end{array}\\ \\ \begin{array}{c} =\left[ \begin{array}{ccc} 1 & 0 & 0 \\ 0 & \cos -(\varepsilon +\Delta \varepsilon ) & \sin -(\varepsilon +\Delta \varepsilon ) \\ 0 & -\sin -(\varepsilon +\Delta \varepsilon ) & \cos -(\varepsilon +\Delta \varepsilon ) \end{array} \right] \; \left[ \begin{array}{ccc} \cos -\Delta \psi & \sin -\Delta \psi & 0 \\ -\sin -\Delta \psi & \cos -\Delta \psi & 0 \\ 0 & 0 & 1 \end{array} \right] \; \left[ \begin{array}{ccc} 1 & 0 & 0 \\ 0 & \cos \varepsilon & \sin \varepsilon \\ 0 & -\sin \varepsilon & \cos \varepsilon \end{array} \right] = \\ \\ \\ =\left[ \begin{array}{ccc} \cos \Delta \psi & -\cos \varepsilon \; \sin \Delta \psi & -\sin \varepsilon \; \sin \Delta \psi \\ -\cos (\varepsilon +\Delta \varepsilon )\; \sin \Delta \psi & \begin{array}{c} \cos (\varepsilon +\Delta \varepsilon )\; \cos \varepsilon \; \cos \Delta \psi - \\ -\sin (\varepsilon +\Delta \varepsilon )\; \sin \varepsilon \end{array} & \begin{array}{c} \cos (\varepsilon +\Delta \varepsilon )\; \sin \varepsilon \; \cos \Delta \psi + \\ +\sin (\varepsilon +\Delta \varepsilon )\; \cos \varepsilon \end{array} \\ \sin (\varepsilon +\Delta \varepsilon )\; \sin \Delta \psi & \begin{array}{c} -\sin (\varepsilon +\Delta \varepsilon )\; \cos \varepsilon \; \cos \Delta \psi + \\ +\cos (\varepsilon +\Delta \varepsilon )\; \sin \varepsilon \end{array} & \begin{array}{c} -\sin (\varepsilon +\Delta \varepsilon )\; \sin \varepsilon \; \cos \Delta \psi + \\ +\cos (\varepsilon +\Delta \varepsilon )\; \cos \varepsilon \end{array} \end{array} \right] \\ \end{array} \end{array} \qquad \mbox{(8)} </math> * '''Polar Motion Matrix''': <math>{\mathbf R}_M</math> :This matrix is given by two elemental rotations, <math>{\mathbf R}_1(-y_p)</math> and <math>{\mathbf R}_2(-x_p)</math> around the <math>x</math> and <math>y</math> axis, respectively. With these rotations the CEP pole is matched into the CTP pole: ::<math> {\mathbf R}_M={\mathbf R}_2(-x_p)\; {\mathbf R}_1(-y_p) \qquad \mbox{(9)} </math> :where <math>x_p</math> and <math>y_p</math> define the position of the CEP with respect to the CTP (see figure 2, at right side). :The <math>x_p</math>, <math>y_p</math> pole displacements between 1961 and 1964 are shown in figure 2, at left side. :Because of the polar movement is quite unpredictable the <math>x_p</math>, <math>y_p</math> displacements are estimated from observations and provided by the IERS as mentioned before. These values can be obtained the from the Earth Rotation Parameters files provided by the IERS or JPL. :::{| |+align="bottom"|''Figure 2: Polar Motion measurements from 2002 to 2008 (left) and polar coordinates (right)'' | [[File: CEP_to_ ITRF_Fig_2.png |none|thumb|400px|frameless]] | [[File: CEP_to_ ITRF_Fig_3.png |none|thumb|580px|frameless]] |} == Speed Transformation == According to the previous explanations it follows: ::<math> {\mathbf r}_{ITRF}={\mathbf R}_1(-y_p)\; {\mathbf R}_2(-x_p)\; {\mathbf R}_3(\Theta_{_G})\; {\mathbf r}_{CEP} \qquad \mbox{(10)} </math> The transformation for the velocity is found differentiating the equation (10) respect to time: ::<math> \begin{array}{c} {\mathbf v}_{ITRF}= {\mathbf R}_1(-y_p)\; {\mathbf R}_2(-x_p)\; \left[ \frac \partial {\partial t}\left( {\mathbf R}_3(\Theta_{_G})\right) \; {\mathbf r}_{CEP}+ {\mathbf R}_3(\Theta_{_G})\; \frac \partial {\partial t}\left( {\mathbf r}_{CEP}\right) \right] = \\ ={\mathbf R}_1(-y_p)\; {\mathbf R}_2(-x_p)\; \left[ \dot{\Theta}_{_G}\; {\stackrel{.}{\mathbf R}}_3(\Theta_{_G})\; {\mathbf r}_{CEP}+{\mathbf R}_3(\Theta_{_G})\; {\mathbf v}_{CEP}\right] \end{array} \qquad \mbox{(11)} </math> Where <math>\stackrel{.}{\Theta}_{_G}</math> is the earth revolution rate: ::<math> \stackrel{.}{\Theta}_{_G}=\frac{2\, \pi }{\left( 24\cdot 3600-236\right) }\left[ rad/s\right] \qquad \mbox{(12)} </math> ==Notes== <references group="footnotes"/> [[Category:Fundamentals]] [[Category:GNSS Time Reference, Coordinate Frames and Orbits]] [[Category:Coordinate Systems]]

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