void mexFunction(int nlhs, mxArray *plhs[], int nrhs, const mxArray *prhs[]) {
size_t numRow,numVec;
mxArray *retMat;
double *xVec, *retData;
double TT1, TT2, UT11, UT12;
//The if-statements below should properly initialize all of the EOP.
//The following initializations to zero are to suppress warnings when
//compiling with -Wconditional-uninitialized.
double dX=0;
double dY=0;
double deltaT=0;
double LOD=0;
double GCRS2TIRS[3][3];
//Polar motion matrix. ITRS=POM*TIRS. We will just be setting it to the
//identity matrix as polar motion is not taken into account when going
//to the TIRS.
double rident[3][3]={{1,0,0},{0,1,0},{0,0,1}};
double Omega[3];//The rotation vector in the TIRS
if(nrhs<3||nrhs>6){
mexErrMsgTxt("Wrong number of inputs");
}
if(nlhs>2) {
mexErrMsgTxt("Wrong number of outputs.");
}
checkRealDoubleArray(prhs[0]);
numRow = mxGetM(prhs[0]);
numVec = mxGetN(prhs[0]);
if(!(numRow==3||numRow==6)) {
mexErrMsgTxt("The input vector has a bad dimensionality.");
}
xVec=(double*)mxGetData(prhs[0]);
TT1=getDoubleFromMatlab(prhs[1]);
TT2=getDoubleFromMatlab(prhs[2]);
//If some values from the function getEOP will be needed
if(nrhs<=5||mxIsEmpty(prhs[3])||mxIsEmpty(prhs[4])||mxIsEmpty(prhs[5])) {
mxArray *retVals[5];
double *dXdY;
mxArray *JulUTCMATLAB[2];
double JulUTC[2];
int retVal;
//Get the time in UTC to look up the parameters by going to TAI and
//then UTC.
retVal=iauTttai(TT1, TT2, &JulUTC[0], &JulUTC[1]);
if(retVal!=0) {
mexErrMsgTxt("An error occurred computing TAI.");
}
retVal=iauTaiutc(JulUTC[0], JulUTC[1], &JulUTC[0], &JulUTC[1]);
switch(retVal){
case 1:
mexWarnMsgTxt("Dubious Date entered.");
break;
case -1:
mexErrMsgTxt("Unacceptable date entered");
break;
default:
break;
}
JulUTCMATLAB[0]=doubleMat2Matlab(&JulUTC[0],1,1);
JulUTCMATLAB[1]=doubleMat2Matlab(&JulUTC[1],1,1);
//Get the Earth orientation parameters for the given date.
mexCallMATLAB(5,retVals,2,JulUTCMATLAB,"getEOP");
mxDestroyArray(JulUTCMATLAB[0]);
mxDestroyArray(JulUTCMATLAB[1]);
//%We do not need the polar motion coordinates.
mxDestroyArray(retVals[0]);
checkRealDoubleArray(retVals[1]);
if(mxGetM(retVals[1])!=2||mxGetN(retVals[1])!=1) {
mxDestroyArray(retVals[1]);
mxDestroyArray(retVals[2]);
mxDestroyArray(retVals[3]);
mxDestroyArray(retVals[4]);
mexErrMsgTxt("Error using the getEOP function.");
return;
}
dXdY=(double*)mxGetData(retVals[1]);
dX=dXdY[0];
dY=dXdY[1];
//This is TT-UT1
deltaT=getDoubleFromMatlab(retVals[3]);
LOD=getDoubleFromMatlab(retVals[4]);
//Free the returned arrays.
mxDestroyArray(retVals[1]);
mxDestroyArray(retVals[2]);
mxDestroyArray(retVals[3]);
mxDestroyArray(retVals[4]);
}
//If deltaT=TT-UT1 is given
if(nrhs>3&&!mxIsEmpty(prhs[3])) {
deltaT=getDoubleFromMatlab(prhs[3]);
}
//Obtain UT1 from terestrial time and deltaT.
iauTtut1(TT1, TT2, deltaT, &UT11, &UT12);
//Get celestial pole offsets, if given.
if(nrhs>4&&!mxIsEmpty(prhs[4])) {
size_t dim1, dim2;
checkRealDoubleArray(prhs[4]);
dim1 = mxGetM(prhs[4]);
dim2 = mxGetN(prhs[4]);
if((dim1==2&&dim2==1)||(dim1==1&&dim2==2)) {
double *dXdY=(double*)mxGetData(prhs[4]);
dX=dXdY[0];
dY=dXdY[1];
} else {
mexErrMsgTxt("The celestial pole offsets have the wrong dimensionality.");
return;
}
}
//If LOD is given
if(nrhs>5&&mxIsEmpty(prhs[5])) {
LOD=getDoubleFromMatlab(prhs[5]);
}
//Compute the rotation matrix for going from GCRS to ITRS as well as
//the instantaneous vector angular momentum due to the Earth's rotation
//in TIRS coordinates.
{
double x, y, s, era;
double rc2i[3][3];
double omega;
//Get the X,Y coordinates of the Celestial Intermediate Pole (CIP) and
//the Celestial Intermediate Origin (CIO) locator s, using the IAU 2006
//precession and IAU 2000A nutation models.
iauXys06a(TT1, TT2, &x, &y, &s);
//Add the CIP offsets.
x += dX;
y += dY;
//Get the GCRS-to-CIRS matrix
iauC2ixys(x, y, s, rc2i);
//Find the Earth rotation angle for the given UT1 time.
era = iauEra00(UT11, UT12);
//Set the polar motion matrix to the identity matrix so that the
//conversion stops at the TIRS instead of the ITRS.
//Combine the GCRS-to-CIRS matrix, the Earth rotation angle, and use
//the identity matrix instead of the polar motion matrix to get a
//to get the rotation matrix to go from GCRS to TIRS.
iauC2tcio(rc2i, era, rident,GCRS2TIRS);
//Next, to be able to transform the velocity, the rotation of the Earth
//has to be taken into account.
//The angular velocity vector of the Earth in the TIRS in radians.
omega=getScalarMatlabClassConst("Constants","IERSMeanEarthRotationRate");
//Adjust for LOD
omega=omega*(1-LOD/86400.0);//86400.0 is the number of seconds in a TT
//day.
Omega[0]=0;
Omega[1]=0;
Omega[2]=omega;
}
//Allocate space for the return vectors.
retMat=mxCreateDoubleMatrix(numRow,numVec,mxREAL);
retData=(double*)mxGetData(retMat);
{
size_t curVec;
for(curVec=0;curVec<numVec;curVec++) {
//Multiply the position vector with the rotation matrix.
iauRxp(GCRS2TIRS, xVec+numRow*curVec, retData+numRow*curVec);
//If a velocity vector was given.
if(numRow>3) {
double *posGCRS=xVec+numRow*curVec;
double posTIRS[3];
double *velGCRS=xVec+numRow*curVec+3;//Velocity in GCRS
double velTIRS[3];
double *retDataVel=retData+numRow*curVec+3;
double rotVel[3];
//If a velocity was provided with the position, first
//convert to TIRS coordinates, then account for the
//rotation of the Earth.
//Convert velocity from GCRS to TIRS.
iauRxp(GCRS2TIRS, velGCRS, velTIRS);
//Convert position from GCRS to TIRS
iauRxp(GCRS2TIRS, posGCRS, posTIRS);
//Evaluate the cross product for the angular velocity due
//to the Earth's rotation.
iauPxp(Omega, posTIRS, rotVel);
//Subtract out the instantaneous velocity due to rotation.
iauPmp(velTIRS, rotVel, retDataVel);
}
}
}
plhs[0]=retMat;
//If the rotation matrix is desired on the output.
if(nlhs>1) {
double *elPtr;
size_t i,j;
plhs[1]=mxCreateDoubleMatrix(3,3,mxREAL);
elPtr=(double*)mxGetData(plhs[1]);
for (i=0;i<3;i++) {
for(j=0;j<3;j++) {
elPtr[i+3*j]=GCRS2TIRS[i][j];
}
}
}
}
void mexFunction(int nlhs, mxArray *plhs[], int nrhs, const mxArray *prhs[]) {
double TT1, TT2, dX, dY, *xVec;
size_t numRow, numVec;
mxArray *retMat;
double *retData;
double GCRS2CIRS[3][3];
if(nrhs<3||nrhs>4){
mexErrMsgTxt("Wrong number of inputs");
}
if(nlhs>2) {
mexErrMsgTxt("Wrong number of outputs.");
}
checkRealDoubleArray(prhs[0]);
numRow = mxGetM(prhs[0]);
numVec = mxGetN(prhs[0]);
if(!(numRow==3||numRow==6)) {
mexErrMsgTxt("The input vector has a bad dimensionality.");
}
xVec=(double*)mxGetData(prhs[0]);
TT1=getDoubleFromMatlab(prhs[1]);
TT2=getDoubleFromMatlab(prhs[2]);
//If some values from the function getEOP will be needed.
if(nrhs<4||mxGetM(prhs[3])==0) {
mxArray *retVals[2];
double *dXdY;
mxArray *JulUTCMATLAB[2];
double JulUTC[2];
int retVal;
//Get the time in UTC to look up the parameters by going to TAI and
//then UTC.
retVal=iauTttai(TT1, TT2, &JulUTC[0], &JulUTC[1]);
if(retVal!=0) {
mexErrMsgTxt("An error occurred computing TAI.");
}
retVal=iauTaiutc(JulUTC[0], JulUTC[1], &JulUTC[0], &JulUTC[1]);
switch(retVal){
case 1:
mexWarnMsgTxt("Dubious Date entered.");
break;
case -1:
mexErrMsgTxt("Unacceptable date entered");
break;
default:
break;
}
JulUTCMATLAB[0]=doubleMat2Matlab(&JulUTC[0],1,1);
JulUTCMATLAB[1]=doubleMat2Matlab(&JulUTC[1],1,1);
//Get the Earth orientation parameters for the given date.
mexCallMATLAB(2,retVals,2,JulUTCMATLAB,"getEOP");
mxDestroyArray(JulUTCMATLAB[0]);
mxDestroyArray(JulUTCMATLAB[1]);
//%We do not need the polar motion coordinates.
mxDestroyArray(retVals[0]);
checkRealDoubleArray(retVals[1]);
if(mxGetM(retVals[1])!=2||mxGetN(retVals[1])!=1) {
mxDestroyArray(retVals[1]);
mexErrMsgTxt("Error using the getEOP function.");
return;
}
dXdY=(double*)mxGetData(retVals[1]);
dX=dXdY[0];
dY=dXdY[1];
//Free the returned arrays.
mxDestroyArray(retVals[1]);
} else {//Get the celestial pole offsets
size_t dim1, dim2;
checkRealDoubleArray(prhs[4]);
dim1 = mxGetM(prhs[4]);
dim2 = mxGetN(prhs[4]);
if((dim1==2&&dim2==1)||(dim1==1&&dim2==2)) {
double *dXdY=(double*)mxGetData(prhs[4]);
dX=dXdY[0];
dY=dXdY[1];
} else {
mexErrMsgTxt("The celestial pole offsets have the wrong dimensionality.");
return;
}
}
{
double x, y, s;
double omega;
//Get the X,Y coordinates of the Celestial Intermediate Pole (CIP) and
//the Celestial Intermediate Origin (CIO) locator s, using the IAU 2006
//precession and IAU 2000A nutation models.
iauXys06a(TT1, TT2, &x, &y, &s);
//Add the CIP offsets.
x += dX;
y += dY;
//Get the GCRS-to-CIRS matrix
iauC2ixys(x, y, s, GCRS2CIRS);
}
//Allocate space for the return vectors.
retMat=mxCreateDoubleMatrix(numRow,numVec,mxREAL);
retData=(double*)mxGetData(retMat);
{
size_t curVec;
for(curVec=0;curVec<numVec;curVec++) {
//Multiply the position vector with the rotation matrix.
iauRxp(GCRS2CIRS, xVec+numRow*curVec, retData+numRow*curVec);
//If a velocity vector was given.
if(numRow>3) {
double *velGCRS=xVec+numRow*curVec+3;//Velocity in GCRS
double *retDataVel=retData+numRow*curVec+3;
//Convert velocity from GCRS to CIRS.
iauRxp(GCRS2CIRS, velGCRS, retDataVel);
}
}
}
plhs[0]=retMat;
//If the rotation matrix is desired on the output.
if(nlhs>1) {
double *elPtr;
size_t i,j;
plhs[1]=mxCreateDoubleMatrix(3,3,mxREAL);
elPtr=(double*)mxGetData(plhs[1]);
for (i=0;i<3;i++) {
for(j=0;j<3;j++) {
elPtr[i+3*j]=GCRS2CIRS[i][j];
}
}
}
}
void mexFunction(int nlhs, mxArray *plhs[], int nrhs, const mxArray *prhs[]) {
size_t numRow,numVec;
mxArray *retMat;
double *retData;
double ITRS2TIRS[3][3];//Inverse polar motion matrix
double *xVec, TT1, TT2;
double xp=0;
double yp=0;//The polar motion coordinates
if(nrhs<3||nrhs>4){
mexErrMsgTxt("Wrong number of inputs");
}
if(nlhs>2) {
mexErrMsgTxt("Wrong number of outputs.");
}
numRow = mxGetM(prhs[0]);
numVec = mxGetN(prhs[0]);
if(!(numRow==3||numRow==6)) {
mexErrMsgTxt("The input vector has a bad dimensionality.");
}
checkRealDoubleArray(prhs[0]);
xVec=(double*)mxGetData(prhs[0]);
TT1=getDoubleFromMatlab(prhs[1]);
TT2=getDoubleFromMatlab(prhs[2]);
//If xpyp should be found using the function getEOP.
if(nrhs<4||mxIsEmpty(prhs[3])) {
mxArray *retVals[1];
double *xpyp;
mxArray *JulUTCMATLAB[2];
double JulUTC[2];
int retVal;
//Get the time in UTC to look up the parameters by going to TAI and
//then UTC.
retVal=iauTttai(TT1, TT2, &JulUTC[0], &JulUTC[1]);
if(retVal!=0) {
mexErrMsgTxt("An error occurred computing TAI.");
}
retVal=iauTaiutc(JulUTC[0], JulUTC[1], &JulUTC[0], &JulUTC[1]);
switch(retVal){
case 1:
mexWarnMsgTxt("Dubious Date entered.");
break;
case -1:
mexErrMsgTxt("Unacceptable date entered");
break;
default:
break;
}
JulUTCMATLAB[0]=doubleMat2Matlab(&JulUTC[0],1,1);
JulUTCMATLAB[1]=doubleMat2Matlab(&JulUTC[1],1,1);
//Get the Earth orientation parameters for the given date.
mexCallMATLAB(1,retVals,2,JulUTCMATLAB,"getEOP");
mxDestroyArray(JulUTCMATLAB[0]);
mxDestroyArray(JulUTCMATLAB[1]);
checkRealDoubleArray(retVals[0]);
if(mxGetM(retVals[0])!=2||mxGetN(retVals[0])!=1) {
mxDestroyArray(retVals[0]);
mexErrMsgTxt("Error using the getEOP function.");
return;
}
xpyp=(double*)mxGetData(retVals[0]);
xp=xpyp[0];
yp=xpyp[1];
//Free the returned array.
mxDestroyArray(retVals[0]);
}
//Get polar motion coordinates, if given.
if(nrhs>3&&!mxIsEmpty(prhs[3])) {
size_t dim1, dim2;
checkRealDoubleArray(prhs[3]);
dim1 = mxGetM(prhs[3]);
dim2 = mxGetN(prhs[3]);
if((dim1==2&&dim2==1)||(dim1==1&&dim2==2)) {
double *xpyp=(double*)mxGetData(prhs[3]);
xp=xpyp[0];
yp=xpyp[1];
} else {
mexErrMsgTxt("The polar motion coordinates have the wrong dimensionality.");
return;
}
}
//Get the rotation matrix from TIRS to ITRS.
{
double sp;
double TIRS2ITRS[3][3];//Polar motion matrix
//Get the Terrestrial Intermediate Origin (TIO) locator s' in
//radians
sp=iauSp00(TT1,TT2);
//Get the polar motion matrix
iauPom00(xp,yp,sp,TIRS2ITRS);
//The inverse polar motion matrix is given by the transpose of the
//polar motion matrix.
iauTr(TIRS2ITRS, ITRS2TIRS);
}
//Allocate space for the return vectors.
retMat=mxCreateDoubleMatrix(numRow,numVec,mxREAL);
retData=(double*)mxGetData(retMat);
{
size_t curVec;
for(curVec=0;curVec<numVec;curVec++) {
//Multiply the position vector with the rotation matrix.
iauRxp(ITRS2TIRS, xVec+numRow*curVec, retData+numRow*curVec);
//Multiply the velocity vector with the rotation matrix.
if(numRow>3) {
double *velITRS=xVec+numRow*curVec+3;//Velocity in ITRS
double *retDataVel=retData+numRow*curVec+3;//Velocity in ITRS
//Convert velocity from ITRS to TIRS.
iauRxp(ITRS2TIRS, velITRS, retDataVel);
}
}
}
plhs[0]=retMat;
if(nlhs>1) {
double *elPtr;
size_t i,j;
plhs[1]=mxCreateDoubleMatrix(3,3,mxREAL);
elPtr=(double*)mxGetData(plhs[1]);
for (i=0;i<3;i++) {
for(j=0;j<3;j++) {
elPtr[i+3*j]=ITRS2TIRS[i][j];
}
}
}
}
void mexFunction(int nlhs, mxArray *plhs[], int nrhs, const mxArray *prhs[]) {
double TT1,TT2,*xVec;
double deltaT=0;
double LOD=0;
size_t numRow,numVec;
double CIRS2TIRS[3][3];
double TIRS2CIRS[3][3];
double Omega[3];//The rotation vector in the TIRS
mxArray *retMat;
double *retData;
if(nrhs<3||nrhs>5){
mexErrMsgTxt("Wrong number of inputs");
}
if(nlhs>2) {
mexErrMsgTxt("Wrong number of outputs.");
}
checkRealDoubleArray(prhs[0]);
numRow = mxGetM(prhs[0]);
numVec = mxGetN(prhs[0]);
if(!(numRow==3||numRow==6)) {
mexErrMsgTxt("The input vector has a bad dimensionality.");
}
xVec=(double*)mxGetData(prhs[0]);
TT1=getDoubleFromMatlab(prhs[1]);
TT2=getDoubleFromMatlab(prhs[2]);
//If some values from the function getEOP will be needed
if(nrhs<=4||mxIsEmpty(prhs[3])||mxIsEmpty(prhs[4])) {
mxArray *retVals[5];
mxArray *JulUTCMATLAB[2];
double JulUTC[2];
int retVal;
//Get the time in UTC to look up the parameters by going to TAI and
//then UTC.
retVal=iauTttai(TT1, TT2, &JulUTC[0], &JulUTC[1]);
if(retVal!=0) {
mexErrMsgTxt("An error occurred computing TAI.");
}
retVal=iauTaiutc(JulUTC[0], JulUTC[1], &JulUTC[0], &JulUTC[1]);
switch(retVal){
case 1:
mexWarnMsgTxt("Dubious Date entered.");
break;
case -1:
mexErrMsgTxt("Unacceptable date entered");
break;
default:
break;
}
JulUTCMATLAB[0]=doubleMat2Matlab(&JulUTC[0],1,1);
JulUTCMATLAB[1]=doubleMat2Matlab(&JulUTC[1],1,1);
//Get the Earth orientation parameters for the given date.
mexCallMATLAB(5,retVals,2,JulUTCMATLAB,"getEOP");
mxDestroyArray(JulUTCMATLAB[0]);
mxDestroyArray(JulUTCMATLAB[1]);
//We do not need the polar motion coordinates.
mxDestroyArray(retVals[0]);
//We do not need the celestial pole offsets.
mxDestroyArray(retVals[1]);
//This is TT-UT1
deltaT=getDoubleFromMatlab(retVals[3]);
LOD=getDoubleFromMatlab(retVals[4]);
//Free the returned arrays.
mxDestroyArray(retVals[2]);
mxDestroyArray(retVals[3]);
mxDestroyArray(retVals[4]);
}
//If deltaT=TT-UT1 is given
if(nrhs>3&&!mxIsEmpty(prhs[3])) {
deltaT=getDoubleFromMatlab(prhs[3]);
}
//If LOD is given
if(nrhs>4&&!mxIsEmpty(prhs[4])) {
LOD=getDoubleFromMatlab(prhs[4]);
}
//Compute the rotation matrix for going from CIRS to TIRS as well as
//the instantaneous vector angular momentum due to the Earth's rotation
//in GCRS coordinates.
{
double UT11, UT12;
double era, omega;
//Obtain UT1 from terestrial time and deltaT.
iauTtut1(TT1, TT2, deltaT, &UT11, &UT12);
//Find the Earth rotation angle for the given UT1 time.
era = iauEra00(UT11, UT12);
//Construct the rotation matrix.
CIRS2TIRS[0][0]=1;
CIRS2TIRS[0][1]=0;
CIRS2TIRS[0][2]=0;
CIRS2TIRS[1][0]=0;
CIRS2TIRS[1][1]=1;
CIRS2TIRS[1][2]=0;
CIRS2TIRS[2][0]=0;
CIRS2TIRS[2][1]=0;
CIRS2TIRS[2][2]=1;
iauRz(era, CIRS2TIRS);
//To go from the TIRS to the GCRS, we need to use the inverse rotation
//matrix, which is just the transpose of the rotation matrix.
iauTr(CIRS2TIRS, TIRS2CIRS);
//Next, to be able to transform the velocity, the rotation of the Earth
//has to be taken into account.
//The angular velocity vector of the Earth in the TIRS in radians.
omega=getScalarMatlabClassConst("Constants","IERSMeanEarthRotationRate");
//Adjust for LOD
omega=omega*(1-LOD/86400.0);//86400.0 is the number of seconds in a TT
//day.
Omega[0]=0;
Omega[1]=0;
Omega[2]=omega;
}
//Allocate space for the return vectors.
retMat=mxCreateDoubleMatrix(numRow,numVec,mxREAL);
retData=(double*)mxGetData(retMat);
{
size_t curVec;
for(curVec=0;curVec<numVec;curVec++) {
//Multiply the position vector with the rotation matrix.
iauRxp(TIRS2CIRS, xVec+numRow*curVec, retData+numRow*curVec);
//If a velocity vector was given.
if(numRow>3) {
double *posTIRS=xVec+numRow*curVec;
double *velTIRS=xVec+numRow*curVec+3;//Velocity in GCRS
double *retDataVel=retData+numRow*curVec+3;
double rotVel[3];
//Evaluate the cross product for the angular velocity due
//to the Earth's rotation.
iauPxp(Omega, posTIRS, rotVel);
//Add the instantaneous velocity due to rotation.
iauPpp(velTIRS, rotVel, retDataVel);
//Rotate from TIRS to GCRS
iauRxp(TIRS2CIRS, retDataVel, retDataVel);
}
}
}
plhs[0]=retMat;
if(nlhs>1) {
double *elPtr;
size_t i,j;
plhs[1]=mxCreateDoubleMatrix(3,3,mxREAL);
elPtr=(double*)mxGetData(plhs[1]);
for (i=0;i<3;i++) {
for(j=0;j<3;j++) {
elPtr[i+3*j]=TIRS2CIRS[i][j];
}
}
}
}
void mexFunction(int nlhs, mxArray *plhs[], int nrhs, const mxArray *prhs[]) {
double TT1,TT2,TDB1,TDB2,Jul2,deltaTTUT1,deltaT,Jul1UT1, Jul2UT1,UT1Frac;
double u, v, elon;
int retVal;
if(nrhs<2||nrhs>4){
mexErrMsgTxt("Wrong number of inputs.");
return;
}
if(nlhs>2){
mexErrMsgTxt("Wrong number of outputs.");
return;
}
TT1=getDoubleFromMatlab(prhs[0]);
TT2=getDoubleFromMatlab(prhs[1]);
//If the parameter is given and is not just an empty matrix.
if(nrhs>2&&!(mxGetM(prhs[2])==0||mxGetN(prhs[2])==0)) {
deltaTTUT1=getDoubleFromMatlab(prhs[2]);
} else {
mxArray *retVals[4];
mxArray *JulUTCMATLAB[2];
double JulUTC[2];
//Get the time in UTC to look up the parameters by going to TAI and
//then UTC.
retVal=iauTttai(TT1, TT2, &JulUTC[0], &JulUTC[1]);
if(retVal!=0) {
mexErrMsgTxt("An error occurred computing TAI.");
}
retVal=iauTaiutc(JulUTC[0], JulUTC[1], &JulUTC[0], &JulUTC[1]);
switch(retVal){
case 1:
mexWarnMsgTxt("Dubious Date entered.");
break;
case -1:
mexErrMsgTxt("Unacceptable date entered");
break;
default:
break;
}
JulUTCMATLAB[0]=doubleMat2Matlab(&JulUTC[0],1,1);
JulUTCMATLAB[1]=doubleMat2Matlab(&JulUTC[1],1,1);
//Get the Earth orientation parameters for the given date.
mexCallMATLAB(4,retVals,2,JulUTCMATLAB,"getEOP");
//This is TT-UT1
deltaTTUT1=getDoubleFromMatlab(retVals[3]);
//Free the returned arrays.
mxDestroyArray(retVals[0]);
mxDestroyArray(retVals[1]);
mxDestroyArray(retVals[2]);
mxDestroyArray(retVals[3]);
mxDestroyArray(JulUTCMATLAB[0]);
mxDestroyArray(JulUTCMATLAB[1]);
}
if(nrhs>3) {
double *xyzClock;
if(mxGetM(prhs[3])!=3||mxGetN(prhs[3])!=1) {
mexErrMsgTxt("The dimensionality of the clock location is incorrect.");
return;
}
checkRealDoubleArray(prhs[3]);
xyzClock=(double*)mxGetData(prhs[3]);
//Convert from meters to kilometers.
xyzClock[0]/=1000;xyzClock[1]/=1000;xyzClock[2]/=1000;
u=sqrt(xyzClock[0]*xyzClock[0] + xyzClock[1]*xyzClock[1]);
v=xyzClock[2];
elon=atan2(xyzClock[1],xyzClock[0]);
} else {
u=0;
v=0;
elon=0;
}
//Get UT1
retVal=iauTtut1(TT1, TT2, deltaTTUT1, &Jul1UT1, &Jul2UT1);
switch(retVal) {
case -1:
mexErrMsgTxt("Unacceptable date provided.");
return;
case 1:
mexWarnMsgTxt("Dubious year provided\n");
break;
default:
break;
}
//Find the fraction of a Julian day in UT1
UT1Frac=(Jul1UT1-floor(Jul1UT1))+(Jul2UT1-floor(Jul2UT1));
UT1Frac=UT1Frac-floor(UT1Frac);
/*Compute TDB-TT. The function iauDtdb takes TDB as an input, but we
*only have TT. The documentation for iauDtdb says that TT can be
*substituted within the precision limits of the function. However, an
*extra iteration is performed here to try to make the result
*consistent with TDB2TT to a few more digits of precision.*/
TDB1=TT1;
TDB2=TT2;
{
int curIter;
for(curIter=0;curIter<2;curIter++) {
deltaT = iauDtdb(TDB1, TDB2, UT1Frac, elon, u, v);
//TT -> TDB
retVal = iauTttdb(TT1, TT2, deltaT, &TDB1, &TDB2);
if(retVal!=0) {
mexErrMsgTxt("An error occured during an intermediate conversion to TDB.\n");
return;
}
}
}
plhs[0]=doubleMat2Matlab(&TDB1,1, 1);
if(nlhs>1) {
plhs[1]=doubleMat2Matlab(&TDB2,1, 1);
}
}
void mexFunction(int nlhs, mxArray *plhs[], int nrhs, const mxArray *prhs[]) {
size_t numRow,numVec;
mxArray *retMat;
double *xVec, *retData;
double TT1, TT2, UT11, UT12;
//The if-statements below should properly initialize all of the EOP.
//The following initializations to zero are to suppress warnings when
//compiling with -Wconditional-uninitialized.
double xp=0;
double yp=0;
double deltaT=0;
double LOD=0;
double ITRS2TEME[3][3];
double PEF2TEME[3][3];
double WInv[3][3];//The inverse polar motion matrix to go from ITRS to PEF.
double Omega[3];//The angular velocity vector for the Earth's rotation.
if(nrhs<3||nrhs>6){
mexErrMsgTxt("Wrong number of inputs");
}
if(nlhs>2) {
mexErrMsgTxt("Wrong number of outputs.");
return;
}
checkRealDoubleArray(prhs[0]);
numRow = mxGetM(prhs[0]);
numVec = mxGetN(prhs[0]);
if(!(numRow==3||numRow==6)) {
mexErrMsgTxt("The input vector has a bad dimensionality.");
}
xVec=(double*)mxGetData(prhs[0]);
TT1=getDoubleFromMatlab(prhs[1]);
TT2=getDoubleFromMatlab(prhs[2]);
//If some values from the function getEOP will be needed
if(nrhs<6||mxIsEmpty(prhs[3])||mxIsEmpty(prhs[4])||mxIsEmpty(prhs[5])) {
mxArray *retVals[5];
double *xpyp;
mxArray *JulUTCMATLAB[2];
double JulUTC[2];
int retVal;
//Get the time in UTC to look up the parameters by going to TAI and
//then UTC.
retVal=iauTttai(TT1, TT2, &JulUTC[0], &JulUTC[1]);
if(retVal!=0) {
mexErrMsgTxt("An error occurred computing TAI.");
}
retVal=iauTaiutc(JulUTC[0], JulUTC[1], &JulUTC[0], &JulUTC[1]);
switch(retVal){
case 1:
mexWarnMsgTxt("Dubious Date entered.");
break;
case -1:
mexErrMsgTxt("Unacceptable date entered");
break;
default:
break;
}
JulUTCMATLAB[0]=doubleMat2Matlab(&JulUTC[0],1,1);
JulUTCMATLAB[1]=doubleMat2Matlab(&JulUTC[1],1,1);
//Get the Earth orientation parameters for the given date.
mexCallMATLAB(5,retVals,2,JulUTCMATLAB,"getEOP");
mxDestroyArray(JulUTCMATLAB[0]);
mxDestroyArray(JulUTCMATLAB[1]);
checkRealDoubleArray(retVals[0]);
checkRealDoubleArray(retVals[1]);
if(mxGetM(retVals[0])!=2||mxGetN(retVals[0])!=1||mxGetM(retVals[1])!=2||mxGetN(retVals[1])!=1) {
mxDestroyArray(retVals[0]);
mxDestroyArray(retVals[1]);
mxDestroyArray(retVals[2]);
mxDestroyArray(retVals[3]);
mxDestroyArray(retVals[4]);
mexErrMsgTxt("Error using the getEOP function.");
return;
}
xpyp=(double*)mxGetData(retVals[0]);
xp=xpyp[0];
yp=xpyp[1];
//The celestial pole offsets are not used.
//This is TT-UT1
deltaT=getDoubleFromMatlab(retVals[3]);
LOD=getDoubleFromMatlab(retVals[4]);
//Free the returned arrays.
mxDestroyArray(retVals[0]);
mxDestroyArray(retVals[1]);
mxDestroyArray(retVals[2]);
mxDestroyArray(retVals[3]);
mxDestroyArray(retVals[4]);
}
//If deltaT=TT-UT1 is given
if(nrhs>3&&!mxIsEmpty(prhs[3])) {
deltaT=getDoubleFromMatlab(prhs[3]);
}
//Obtain UT1 from terestrial time and deltaT.
iauTtut1(TT1, TT2, deltaT, &UT11, &UT12);
//Get polar motion values, if given.
if(nrhs>4&&!mxIsEmpty(prhs[4])) {
size_t dim1, dim2;
checkRealDoubleArray(prhs[4]);
dim1 = mxGetM(prhs[4]);
dim2 = mxGetN(prhs[4]);
if((dim1==2&&dim2==1)||(dim1==1&&dim2==2)) {
double *xpyp=(double*)mxGetData(prhs[4]);
xp=xpyp[0];
yp=xpyp[1];
} else {
mexErrMsgTxt("The celestial pole offsets have the wrong dimensionality.");
return;
}
}
//If LOD is given
if(nrhs>5&&!mxIsEmpty(prhs[5])) {
LOD=getDoubleFromMatlab(prhs[5]);
}
{
double GMST1982=iauGmst82(UT11, UT12);
double TEME2PEF[3][3];
double TEME2ITRS[3][3];
double W[3][3];
double omega;
//Get Greenwhich mean sidereal time under the IAU's 1982 model. This
//is given in radians and will be used to build a rotation matrix to
//rotate into the PEF system.
GMST1982=iauGmst82(UT11, UT12);
{
double cosGMST,sinGMST;
cosGMST=cos(GMST1982);
sinGMST=sin(GMST1982);
//Build the rotation matrix to rotate by GMST about the z-axis. This
//will put the position vector in the PEF system.
TEME2PEF[0][0]=cosGMST;
TEME2PEF[0][1]=sinGMST;
TEME2PEF[0][2]=0;
TEME2PEF[1][0]=-sinGMST;
TEME2PEF[1][1]=cosGMST;
TEME2PEF[1][2]=0;
TEME2PEF[2][0]=0;
TEME2PEF[2][1]=0;
TEME2PEF[2][2]=1.0;
}
//The inverse rotation is just the transpose
iauTr(TEME2PEF, PEF2TEME);
//To go from PEF to ITRS, we need to build the polar motion matrix
//using the IAU's 1980 conventions.
{
double cosXp,sinXp,cosYp,sinYp;
cosXp=cos(xp);
sinXp=sin(xp);
cosYp=cos(yp);
sinYp=sin(yp);
W[0][0]=cosXp;
W[0][1]=sinXp*sinYp;
W[0][2]=sinXp*cosYp;
W[1][0]=0;
W[1][1]=cosYp;
W[1][2]=-sinYp;
W[2][0]=-sinXp;
W[2][1]=cosXp*sinXp;
W[2][2]=cosXp*cosYp;
}
//The inverse rotation is just the transpose
iauTr(W, WInv);
//The total rotation matrix is thus the product of the two rotations.
//TEME2ITRS=W*TEME2PEF;
iauRxr(W, TEME2PEF, TEME2ITRS);
//We want the inverse rotation
iauTr(TEME2ITRS, ITRS2TEME);
//The angular velocity vector of the Earth in the TIRS in radians.
omega=getScalarMatlabClassConst("Constants","IERSMeanEarthRotationRate");
//Adjust for LOD
omega=omega*(1-LOD/86400.0);//86400.0 is the number of seconds in a TT day.
Omega[0]=0;
Omega[1]=0;
Omega[2]=omega;
}
//Allocate space for the return vectors.
retMat=mxCreateDoubleMatrix(numRow,numVec,mxREAL);
retData=(double*)mxGetData(retMat);
{
size_t curVec;
for(curVec=0;curVec<numVec;curVec++) {
//Multiply the position vector with the rotation matrix.
iauRxp(ITRS2TEME, xVec+numRow*curVec, retData+numRow*curVec);
//If a velocity vector was given.
if(numRow>3) {
double *posITRS=xVec+numRow*curVec;
double *velITRS=xVec+numRow*curVec+3;//Velocity in TEME
double posPEF[3];
double velPEF[3];
double *retDataVel=retData+numRow*curVec+3;
double rotVel[3];
//If a velocity was provided with the position, first
//convert to PEF coordinates, then account for the rotation
//of the Earth, then rotate into TEME coordinates.
//Convert velocity from ITRS to PEF.
iauRxp(WInv, velITRS, velPEF);
//Convert position from ITRS to PEF
iauRxp(WInv, posITRS, posPEF);
//Evaluate the cross product for the angular velocity due
//to the Earth's rotation.
iauPxp(Omega, posPEF, rotVel);
//Add the instantaneous velocity due to rotation.
iauPpp(velPEF, rotVel, retDataVel);
//Rotate from the PEF into the TEME
iauRxp(PEF2TEME, retDataVel, retDataVel);
}
}
}
plhs[0]=retMat;
if(nlhs>1) {
double *elPtr;
size_t i,j;
plhs[1]=mxCreateDoubleMatrix(3,3,mxREAL);
elPtr=(double*)mxGetData(plhs[1]);
for (i=0;i<3;i++) {
for(j=0;j<3;j++) {
elPtr[i+3*j]=ITRS2TEME[i][j];
}
}
}
}
void mexFunction(int nlhs, mxArray *plhs[], int nrhs, const mxArray *prhs[]) {
double TT1, TT2, UT11,UT12, deltaT,GMST;
int algToUse=2006;
int retVal;
if(nrhs<2||nrhs>4){
mexErrMsgTxt("Wrong number of inputs.");
return;
}
if(nlhs>1){
mexErrMsgTxt("Wrong number of outputs.");
return;
}
TT1=getDoubleFromMatlab(prhs[0]);
TT2=getDoubleFromMatlab(prhs[1]);
if(nrhs>2) {
algToUse=getIntFromMatlab(prhs[2]);
}
if(nrhs>3) {
deltaT=getDoubleFromMatlab(prhs[3]);
} else {
mxArray *retVals[4];
mxArray *JulUTCMATLAB[2];
double JulUTC[2];
//Get the time in UTC to look up the parameters by going to TAI and
//then UTC.
retVal=iauTttai(TT1, TT2, &JulUTC[0], &JulUTC[1]);
if(retVal!=0) {
mexErrMsgTxt("An error occurred computing TAI.");
}
retVal=iauTaiutc(JulUTC[0], JulUTC[1], &JulUTC[0], &JulUTC[1]);
switch(retVal){
case 1:
mexWarnMsgTxt("Dubious Date entered.");
break;
case -1:
mexErrMsgTxt("Unacceptable date entered");
break;
default:
break;
}
JulUTCMATLAB[0]=doubleMat2Matlab(&JulUTC[0],1,1);
JulUTCMATLAB[1]=doubleMat2Matlab(&JulUTC[1],1,1);
//Get the Earth orientation parameters for the given date.
mexCallMATLAB(4,retVals,2,JulUTCMATLAB,"getEOP");
//This is TT-UT1
deltaT=getDoubleFromMatlab(retVals[3]);
//Free the returned arrays.
mxDestroyArray(retVals[0]);
mxDestroyArray(retVals[1]);
mxDestroyArray(retVals[2]);
mxDestroyArray(retVals[3]);
mxDestroyArray(JulUTCMATLAB[0]);
mxDestroyArray(JulUTCMATLAB[1]);
}
//Get UT1
retVal=iauTtut1(TT1, TT2, deltaT, &UT11, &UT12);
if(retVal!=0) {
mexErrMsgTxt("An error occurred computing UT1.");
}
//Get Greenwhich mean sidereal time in radians using the chosen
//algorithm
switch(algToUse) {
case 1982:
GMST=iauGmst82(UT11, UT12);
break;
case 2000:
GMST=iauGmst00(UT11, UT12, TT1, TT2);
break;
case 2006:
GMST=iauGmst06(UT11, UT12, TT1, TT2);
break;
default:
mexErrMsgTxt("An invalid algorithm version was given.");
}
plhs[0]=doubleMat2Matlab(&GMST,1, 1);
}
