//---------------------------------------------------------------------------
bool TOEEqAxes::Initialize()
{
#ifdef DEBUG_TOEEQ
MessageInterface::ShowMessage(wxT("Entering TOEEq::Initialize ..........\n"));
#endif
InertialAxes::Initialize();
InitializeFK5();
#ifdef DEBUG_TOEEQ
MessageInterface::ShowMessage(wxT("Completed IA:Init and InitFK5 ..........\n"));
#endif
Real dPsi = 0.0;
Real longAscNodeLunar = 0.0;
Real cosEpsbar = 0.0;
// convert epoch (A1 MJD) to TT MJD (for calculations)
// 20.02.06 - arg: changed to use enum types instead of strings
// Real mjdTT = TimeConverterUtil::Convert(epoch.Get(),
// "A1Mjd", "TtMjd", GmatTimeConstants::JD_JAN_5_1941);
Real mjdTT = TimeConverterUtil::Convert(epoch.Get(),
TimeConverterUtil::A1MJD, TimeConverterUtil::TTMJD,
GmatTimeConstants::JD_JAN_5_1941);
//Real jdTT = mjdTT + GmatTimeConstants::JD_JAN_5_1941;
// Compute Julian centuries of TDB from the base epoch (J2000)
//Real tTDB = (jdTT -GmatTimeConstants::JD_OF_J2000) / GmatTimeConstants::DAYS_PER_JULIAN_CENTURY;
Real offset = GmatTimeConstants::JD_JAN_5_1941 - GmatTimeConstants::JD_OF_J2000;
Real tTDB = (mjdTT + offset) / GmatTimeConstants::DAYS_PER_JULIAN_CENTURY;
if (overrideOriginInterval) updateIntervalToUse =
((Planet*) origin)->GetNutationUpdateInterval();
else updateIntervalToUse = updateInterval;
// Rmatrix33 PREC = ComputePrecessionMatrix(tTDB, epoch);
// Rmatrix33 NUT = ComputeNutationMatrix(tTDB, epoch, dPsi,
// longAscNodeLunar, cosEpsbar);
#ifdef DEBUG_TOEEQ
MessageInterface::ShowMessage(wxT("About to call ComputePrecession/Nutation ..........\n"));
#endif
ComputePrecessionMatrix(tTDB, epoch);
#ifdef DEBUG_TOEEQ
MessageInterface::ShowMessage(wxT("Called ComputePrecession ..........\n"));
#endif
ComputeNutationMatrix(tTDB, epoch, dPsi, longAscNodeLunar, cosEpsbar, true);
#ifdef DEBUG_TOEEQ
MessageInterface::ShowMessage(wxT("Called ComputeNutation ..........\n"));
if (precData == NULL)
MessageInterface::ShowMessage(wxT("precData is NULL!!!!\n"));
if (nutData == NULL)
MessageInterface::ShowMessage(wxT("nutData is NULL!!!!\n"));
#endif
Real PrecT[9] = {precData[0], precData[3], precData[6],
precData[1], precData[4], precData[7],
precData[2], precData[5], precData[8]};
#ifdef DEBUG_TOEEQ
MessageInterface::ShowMessage(wxT("PrecT omputed ..........\n"));
#endif
Real NutT[9] = {nutData[0], nutData[3], nutData[6],
nutData[1], nutData[4], nutData[7],
nutData[2], nutData[5], nutData[8]};
#ifdef DEBUG_TOEEQ
MessageInterface::ShowMessage(wxT("NutT computed ..........\n"));
#endif
Integer p3 = 0;
Real res[3][3];
for (Integer p = 0; p < 3; ++p)
{
p3 = 3*p;
for (Integer q = 0; q < 3; ++q)
{
res[p][q] = PrecT[p3] * NutT[q] +
PrecT[p3+1] * NutT[q+3] +
PrecT[p3+2] * NutT[q+6];
}
}
#ifdef DEBUG_TOEEQ
MessageInterface::ShowMessage(wxT("About to set rotMatrix ..........\n"));
#endif
rotMatrix.Set(res[0][0],res[0][1],res[0][2],
res[1][0],res[1][1],res[1][2],
res[2][0],res[2][1],res[2][2]);
//rotMatrix = PREC.Transpose() * NUT.Transpose();
//rotMatrix = PREC * NUT;
// rotDotMatrix is still the default zero matrix
#ifdef DEBUG_TOEEQ
MessageInterface::ShowMessage(wxT("EXITing TOEEq::Initialize ..........\n"));
#endif
return true;
}
//---------------------------------------------------------------------------
bool TOEEcAxes::Initialize()
{
InertialAxes::Initialize();
InitializeFK5();
Real dPsi = 0.0;
Real longAscNodeLunar = 0.0;
Real cosEpsbar = 0.0;
// convert epoch (A1 MJD) to TT MJD (for calculations)
Real mjdTT = TimeConverterUtil::Convert(epoch.Get(),
TimeConverterUtil::A1MJD, TimeConverterUtil::TTMJD,
GmatTimeConstants::JD_JAN_5_1941);
// Compute Julian centuries of TDB from the base epoch (J2000)
Real offset = GmatTimeConstants::JD_JAN_5_1941 - GmatTimeConstants::JD_OF_J2000;
Real tTDB = (mjdTT + offset) / GmatTimeConstants::DAYS_PER_JULIAN_CENTURY;
Real tTDB2 = tTDB * tTDB;
Real tTDB3 = tTDB * tTDB2;
// Vallado Eq. 3-52
Real Epsbar = (84381.448 - 46.8150*tTDB - 0.00059*tTDB2 + 0.001813*tTDB3)
* GmatMathConstants::RAD_PER_ARCSEC;
Real R1EpsT[9] = { 1.0, 0.0, 0.0,
0.0,GmatMathUtil::Cos(Epsbar),-GmatMathUtil::Sin(Epsbar),
0.0,GmatMathUtil::Sin(Epsbar), GmatMathUtil::Cos(Epsbar)};
if (overrideOriginInterval) updateIntervalToUse =
((Planet*) origin)->GetNutationUpdateInterval();
else updateIntervalToUse = updateInterval;
ComputePrecessionMatrix(tTDB, epoch);
ComputeNutationMatrix(tTDB, epoch, dPsi, longAscNodeLunar, cosEpsbar, true);
Real R3PsiT[3][3] = { { GmatMathUtil::Cos(-dPsi),-GmatMathUtil::Sin(-dPsi), 0.0},
{ GmatMathUtil::Sin(-dPsi), GmatMathUtil::Cos(-dPsi), 0.0},
{ 0.0, 0.0, 1.0}};
Real PrecT[9] = {precData[0], precData[3], precData[6],
precData[1], precData[4], precData[7],
precData[2], precData[5], precData[8]};
Real res[3][3], tmp[3][3];
Integer p3 = 0;
for (Integer p = 0; p < 3; ++p)
{
p3 = 3*p;
for (Integer q = 0; q < 3; ++q)
{
tmp[p][q] = R1EpsT[p3] * R3PsiT[0][q] +
R1EpsT[p3+1] * R3PsiT[1][q] +
R1EpsT[p3+2] * R3PsiT[2][q];
}
}
for (Integer p = 0; p < 3; ++p)
{
p3 = 3*p;
for (Integer q = 0; q < 3; ++q)
{
res[p][q] = PrecT[p3] * tmp[0][q] +
PrecT[p3+1] * tmp[1][q] +
PrecT[p3+2] * tmp[2][q];
}
}
rotMatrix.Set(res[0][0],res[0][1],res[0][2],
res[1][0],res[1][1],res[1][2],
res[2][0],res[2][1],res[2][2]);
// rotDotMatrix is still the default zero matrix
return true;
}
