char* spkezr_custom(char* target, double et, char* ref, char* abcorr, char* observer, double starg[6], double* lt) {
//SpiceDouble* starg_spice = malloc(sizeof(SpiceDouble) * 6);
SpiceDouble lt_spice;
spkezr_c(target, et, ref, abcorr, observer, starg, <_spice);
CHECK_EXCEPTION
//*starg = (double) starg_spice;
*lt = (double) lt_spice;
FINALIZE
}
void spice::eph_impl(double mjd2000, array3D &r, array3D &v) const{
SpiceDouble spice_epoch = kep_toolbox::util::epoch_to_spice(mjd2000);
spkezr_c ( m_target.c_str(), spice_epoch, m_reference_frame.c_str(), m_aberrations.c_str(), m_observer.c_str(), m_state, &m_lt );
r[0] = m_state[0] * 1000; r[1] = m_state[1] * 1000; r[2] = m_state[2] * 1000;
v[0] = m_state[3] * 1000; v[1] = m_state[4] * 1000; v[2] = m_state[5] * 1000;
/// Handling errors
if (failed_c()) {
std::ostringstream msg;
msg << "SPICE cannot compute the ephemerides, have you loaded all needed Kernel files?" << std::endl;
reset_c();
throw_value_error(msg.str());
}
}
int eom_impactor(double t,const double x[],double dxdt[],void *params)
{
char *param=(char *)params;
const double *r,*v;
double R_io,R_europa,R_calisto,R_ganymede,R_uranus,x_ie[4];
double Rj,R_sun,R_saturn,rho,G1,G2,alpha,delta;
double *a,gx,gy,gz,r_ie;
double ratio,zdivR;
double RI,Vimpc;
double xeqj[3],xecl[3];
int i;
SpiceDouble et,ET;
SpiceDouble lt;
SpiceDouble x_io[6],x_calisto[6],x_ganymede[6],x_uranus[6];
SpiceDouble x_europa[6],x_sun[6],x_saturn[6],x_earth[6],x_jup[6];
r=&x[0];
v=&x[3];
a=&dxdt[3];
/*
RI=sqrt(x[0]*x[0]+x[1]*x[1]+x[2]*x[2])*UL;
Vimpc=sqrt(x[3]*x[3]+x[4]*x[4]+x[5]*x[5])*(UL/UT);
cout.setf(ios::scientific);
cout.setf(ios::showpoint);
cout.precision(15);
cout<<"***************************************************"<<endl;
cout<<"Elementos de estado del impactor en EOM-impactor: "<<endl;
cout<<"x: "<<x[0]*UL<<" y: "<<x[1]*UL<<" z: "<<x[2]*UL<<"\n"
<<"vx: "<<x[3]*(UL/UT)<<" vy: "<<x[4]*(UL/UT)<<" vz: "<<x[5]*(UL/UT)<<"\n"
<<"Distance: "<<RI<<" Velocity: "<< Vimpc<<"\n"<<endl;
cout<<"***************************************************"<<endl;
//*/
if(!strcmp(param,"NOMOONS"))
{
//cout<<"In if of NOMOONS"<<endl;
//Velocidades en x, y, z
dxdt[0]=x[3];
dxdt[1]=x[4];
dxdt[2]=x[5];
et=t*UT;
spkezr_c("399",et,FRAME,"NONE","599",x_earth,<);
spkezr_c("10",et,FRAME,"NONE","599",x_sun,<);
spkezr_c("6",et,FRAME,"NONE","599",x_saturn,<);
x_sun[0]/=UL; x_sun[1]/=UL; x_sun[2]/=UL;
x_saturn[0]/=UL; x_saturn[1]/=UL; x_saturn[2]/=UL;
rho=sqrt(x[0]*x[0]+x[1]*x[1]); // Distancia polar (plano x-y) de la nave
Rj=magnitud(x);
R_sun=Distance(x,x_sun);
R_saturn=Distance(x,x_saturn);
gx=-G*MASA_JUPITER*x[0]/(Rj*Rj*Rj);
gy=-G*MASA_JUPITER*x[1]/(Rj*Rj*Rj);
gz=-G*MASA_JUPITER*x[2]/(Rj*Rj*Rj);
// ACELERACIONES EN X, Y, Z
dxdt[3]= gx-(G*MASA_SUN*(x[0]-x_sun[0])/(R_sun*R_sun*R_sun)-
G*MASA_SATURNO*(x[0]-x_saturn[0])/(R_saturn*R_saturn*R_saturn));
//G*MASA_URANUS*(x[0]-x_uranus[0])/(R_uranus*R_uranus*R_uranus));
dxdt[4]= gy-(G*MASA_SUN*(x[1]-x_sun[1])/(R_sun*R_sun*R_sun)-
G*MASA_SATURNO*(x[1]-x_saturn[1])/(R_saturn*R_saturn*R_saturn));
//G*MASA_URANUS*(x[1]-x_uranus[1])/(R_uranus*R_uranus*R_uranus));
dxdt[5]= gz-(G*MASA_SUN*(x[2]-x_sun[2])/(R_sun*R_sun*R_sun)-
G*MASA_SATURNO*(x[2]-x_saturn[2])/(R_saturn*R_saturn*R_saturn));
//G*MASA_URANUS*(x[2]-x_uranus[2])/(R_uranus*R_uranus*R_uranus));
}
if(!strcmp(param,"MOONS"))
{
//cout<<"In if of MOONS"<<endl;
//Velocidades en x, y, z
dxdt[0]=x[3];
dxdt[1]=x[4];
dxdt[2]=x[5];
//Se calculan las efemerides del sol, saturno y las lunas mayores de jupiter
//Tengase en cuenta que el t pasado a esta rutina es el et de la efemeride.
//---------------------------------------------------------------------------
et=t*UT;
// spkezr_c("599",et,FRAME,"NONE","399",x_jup,<);
spkezr_c("399",et,FRAME,"NONE","599",x_earth,<);
spkezr_c("10",et,FRAME,"NONE","599",x_sun,<);
spkezr_c("501",et,FRAME,"NONE","599",x_io,<);
spkezr_c("502",et,FRAME,"NONE","599",x_europa,<);
spkezr_c("503",et,FRAME,"NONE","599",x_ganymede,<);
spkezr_c("504",et,FRAME,"NONE","599",x_calisto,<);
spkezr_c("6",et,FRAME,"NONE","599",x_saturn,<);
//spkezr_c("7",et,FRAME,"NONE","599",x_uranus,<);
// Se hace la conversion al sistema de unidades utilizados
//--------------------------------------------------------
x_sun[0]/=UL; x_sun[1]/=UL; x_sun[2]/=UL;
x_io[0]/=UL; x_io[1]/=UL; x_io[2]/=UL;
x_europa[0]/=UL; x_europa[1]/=UL; x_europa[2]/=UL;
x_ganymede[0]/=UL; x_ganymede[1]/=UL; x_ganymede[2]/=UL;
x_calisto[0]/=UL; x_calisto[1]/=UL; x_calisto[2]/=UL;
x_saturn[0]/=UL; x_saturn[1]/=UL; x_saturn[2]/=UL;
//x_uranus[0]/=UL; x_uranus[1]/=UL; x_uranus[2]/=UL;
// Se calcula la distancia de la nave a cada luna galileana,
// a saturno y al sol:
//-----------------------------------------------------------
rho=sqrt(x[0]*x[0]+x[1]*x[1]); // Distancia polar (plano x-y) de la nave
//*
Rj=magnitud(x);
R_sun=Distance(x,x_sun);
R_io=Distance(x,x_io);
R_europa=Distance(x,x_europa);
R_ganymede=Distance(x,x_ganymede);
R_calisto=Distance(x,x_calisto);
R_saturn=Distance(x,x_saturn);
//R_uranus=Distance(x,x_uranus);
//*/
/*
// PARA EL POTENCIAL AXISIMETRICO DE JUPITER:
// Se hace la transformacion de coordenadas, del
// sistema ecliptico al sistema ecuatorial de jupiter
//----------------------------------------------------
xecl[0]=x[0];
xecl[1]=x[1];
xecl[2]=x[2];
Ecl2EqJ(xecl,xeqj);
/*
xeqj[0]=x[0];
xeqj[1]=x[1];
xeqj[2]=x[2];
///
// Terminos del potencial axisimetrico de jupiter
//-----------------------------------------------
ratio=(R_eq/UL)/Rj;
zdivR=xeqj[2]/Rj;
/*
cout<<"IN EOM_IMPACTOR:"<<endl;
cout<<"Rj-ecl: "<<Rj*UL/AU<<" Rj-eq: "<<magnitud(xeqj)*UL/AU<<endl;
cout<<"xeqj: "<<xeqj[0]<<" yeqj: "<<xeqj[1]<<" zeqj: "<<xeqj[2]<<"\n"
<<"xecl: "<<xecl[0]<<" yecl: "<<xecl[1]<<" zecl: "<<xecl[2]<<"\n"<<endl;
///
//***************************************************
// Aceleracion de la particula debida a Jupiter
// considerando un potencial axisimetrico.
//***************************************************
//*
if(param=="OBLATE")
{
//cout<<"in oblate"<<endl;
gx=-xeqj[0]*(G*MASA_JUPITER/(Rj*Rj*Rj))*
( 1 - (3*J2/2.)*ratio*ratio*( 5*zdivR*zdivR - 1 ));
// -(5*J4*pow(ratio,4)/8.0)*( 3 - 42*zdivR*zdivR + 63*pow(zdivR,4)));
gy=xeqj[1]*gx/xeqj[0];
gz=-xeqj[2]*(G*MASA_JUPITER/(Rj*Rj*Rj))*
( 1 + (3*J2/2.)*pow(ratio,3)*( 3 - 5*zdivR*zdivR));
// -(5*J4/8.)*pow(ratio,4)*( 15 - 70*zdivR*zdivR + 63*pow(zdivR,4)));
}
// PARA EL POTENCIAL ESFERICO:
//-----------------------------
if(param=="SPHERICAL")
{
//cout<<"in spherical"<<endl;
gx=-G*MASA_JUPITER*x[0]/(Rj*Rj*Rj);
gy=-G*MASA_JUPITER*x[1]/(Rj*Rj*Rj);
gz=-G*MASA_JUPITER*x[2]/(Rj*Rj*Rj);
}//*/
gx=-G*MASA_JUPITER*x[0]/(Rj*Rj*Rj);
gy=-G*MASA_JUPITER*x[1]/(Rj*Rj*Rj);
gz=-G*MASA_JUPITER*x[2]/(Rj*Rj*Rj);
// ACELERACIONES EN X, Y, Z
dxdt[3]= gx-(G*MASA_IO*(x[0]-x_io[0])/(R_io*R_io*R_io)-
G*MASA_EUROPA*(x[0]-x_europa[0])/(R_europa*R_europa*R_europa)-
G*MASA_GANYMEDE*(x[0]-x_ganymede[0])/(R_ganymede*R_ganymede*R_ganymede)-
G*MASA_CALISTO*(x[0]-x_calisto[0])/(R_calisto*R_calisto*R_calisto)-
G*MASA_SUN*(x[0]-x_sun[0])/(R_sun*R_sun*R_sun)-
G*MASA_SATURNO*(x[0]-x_saturn[0])/(R_saturn*R_saturn*R_saturn));
//G*MASA_URANUS*(x[0]-x_uranus[0])/(R_uranus*R_uranus*R_uranus));
dxdt[4]= gy-(G*MASA_IO*(x[1]-x_io[1])/(R_io*R_io*R_io)-
G*MASA_EUROPA*(x[1]-x_europa[1])/(R_europa*R_europa*R_europa)-
G*MASA_GANYMEDE*(x[1]-x_ganymede[1])/(R_ganymede*R_ganymede*R_ganymede)-
G*MASA_CALISTO*(x[1]-x_calisto[1])/(R_calisto*R_calisto*R_calisto)-
G*MASA_SUN*(x[1]-x_sun[1])/(R_sun*R_sun*R_sun)-
G*MASA_SATURNO*(x[1]-x_saturn[1])/(R_saturn*R_saturn*R_saturn));
//G*MASA_URANUS*(x[1]-x_uranus[1])/(R_uranus*R_uranus*R_uranus));
dxdt[5]= gz-(G*MASA_IO*(x[2]-x_io[2])/(R_io*R_io*R_io)-
G*MASA_EUROPA*(x[2]-x_europa[2])/(R_europa*R_europa*R_europa)-
G*MASA_GANYMEDE*(x[2]-x_ganymede[2])/(R_ganymede*R_ganymede*R_ganymede)-
G*MASA_CALISTO*(x[2]-x_calisto[2])/(R_calisto*R_calisto*R_calisto)-
G*MASA_SUN*(x[2]-x_sun[2])/(R_sun*R_sun*R_sun)-
G*MASA_SATURNO*(x[2]-x_saturn[2])/(R_saturn*R_saturn*R_saturn));
//G*MASA_URANUS*(x[2]-x_uranus[2])/(R_uranus*R_uranus*R_uranus));
}
return 0;
}
//------------------------------------------------------------------------------
Rvector6 SpiceOrbitKernelReader::GetTargetState(const wxString &targetName,
const Integer targetNAIFId,
const A1Mjd &atTime,
const wxString &observingBodyName,
const wxString &referenceFrame,
const wxString &aberration)
{
#ifdef DEBUG_SPK_READING
MessageInterface::ShowMessage(
wxT("Entering SPKReader::GetTargetState with target = %s, naifId = %d, time = %12.10f, observer = %s\n"),
targetName.c_str(), targetNAIFId, atTime.Get(), observingBodyName.c_str());
Real start, end;
GetCoverageStartAndEnd(loadedKernels, targetNAIFId, start, end);
MessageInterface::ShowMessage(wxT(" coverage for object %s : %12.10f --> %12.10f\n"),
targetName.c_str(), start, end);
#endif
wxString targetNameToUse = GmatStringUtil::ToUpper(targetName);
if (targetNameToUse == wxT("LUNA")) // We use Luna, instead of Moon, for GMAT
targetNameToUse = wxT("MOON");
if (targetNameToUse == wxT("SOLARSYSTEMBARYCENTER"))
targetNameToUse = wxT("SSB");
objectNameSPICE = targetNameToUse.char_str();
observingBodyNameSPICE = observingBodyName.char_str();
referenceFrameSPICE = referenceFrame.char_str();
aberrationSPICE = aberration.char_str();
// convert time to Ephemeris Time (TDB)
etSPICE = A1ToSpiceTime(atTime.Get());
naifIDSPICE = targetNAIFId;
boddef_c(objectNameSPICE, naifIDSPICE); // CSPICE method to set NAIF ID for an object
#ifdef DEBUG_SPK_READING
MessageInterface::ShowMessage(wxT("SET NAIF Id for object %s to %d\n"),
targetNameToUse.c_str(), targetNAIFId);
// MessageInterface::ShowMessage(
// wxT("In SPKReader::Converted (to TBD) time = %12.10f\n"), etMjdAtTime);
// MessageInterface::ShowMessage(wxT(" then the full JD = %12.10f\n"),
// (etMjdAtTime + GmatTimeConstants::JD_JAN_5_1941));
MessageInterface::ShowMessage(wxT("So time passed to SPICE is %12.14f\n"), (Real) etSPICE);
#endif
SpiceDouble state[6];
SpiceDouble oneWayLightTime;
spkezr_c(objectNameSPICE, etSPICE, referenceFrameSPICE, aberrationSPICE,
observingBodyNameSPICE, state, &oneWayLightTime);
#ifdef DEBUG_SPK_PLANETS
Real ttMjdAtTime = TimeConverterUtil::Convert(atTime.Get(), TimeConverterUtil::A1MJD,
TimeConverterUtil::TTMJD, GmatTimeConstants::JD_JAN_5_1941);
// Real etJd = etMjdAtTime + GmatTimeConstants::JD_JAN_5_1941;
Real ttJd = ttMjdAtTime + GmatTimeConstants::JD_JAN_5_1941;
MessageInterface::ShowMessage(wxT("Asking CSPICE for state of body %s, with observer %s, referenceFrame %s, and aberration correction %s\n"),
objectNameSPICE, observingBodyNameSPICE, referenceFrameSPICE, aberrationSPICE);
MessageInterface::ShowMessage(
wxT(" Body: %s TT Time: %12.10f TDB Time: %12.10f state: %12.10f %12.10f %12.10f %12.10f %12.10f %12.10f\n"),
targetName.c_str(), ttJd, /*etJd,*/ state[0], state[1], state[2], state[3], state[4], state[5]);
#endif
if (failed_c())
{
// ConstSpiceChar option[] = wxT("SHORT"); // retrieve short error message, for now
// SpiceInt numChar = MAX_SHORT_MESSAGE;
// SpiceChar err[MAX_SHORT_MESSAGE];
ConstSpiceChar option[] = "LONG"; // retrieve long error message, for now
SpiceInt numChar = MAX_LONG_MESSAGE_VALUE;
//SpiceChar err[MAX_LONG_MESSAGE_VALUE];
SpiceChar *err = new SpiceChar[MAX_LONG_MESSAGE_VALUE];
getmsg_c(option, numChar, err);
wxString errStr(wxString::FromAscii(err));
wxString errmsg = wxT("Error getting state for body \"");
errmsg += targetName + wxT("\". Message received from CSPICE is: ");
errmsg += errStr + wxT("\n");
reset_c();
delete [] err;
throw UtilityException(errmsg);
}
#ifdef DEBUG_SPK_READING
MessageInterface::ShowMessage(
wxT("In SPKReader::Called spkezr_c and got state out\n"));
#endif
Rvector6 r6(state[0],state[1],state[2],state[3],state[4],state[5]);
return r6;
}
/** Cache J2000 rotation quaternion over a time range.
*
* This method will load an internal cache with frames over a time
* range. This prevents the NAIF kernels from being read over-and-over
* again and slowing an application down due to I/O performance. Once the
* cache has been loaded then the kernels can be unloaded from the NAIF
* system.
*
* @internal
* @history 2010-12-23 Debbie A. Cook Added set of full cache time
* parameters
*/
void LineScanCameraRotation::LoadCache() {
NaifStatus::CheckErrors();
double startTime = p_cacheTime[0];
int size = p_cacheTime.size();
double endTime = p_cacheTime[size-1];
SetFullCacheParameters(startTime, endTime, size);
// TODO Add a label value to indicate pointing is already decomposed to line scan angles
// and set p_pointingDecomposition=none,framing angles, or line scan angles.
// Also add a label value to indicate jitterOffsets=jitterFileName
// Then we can decide whether to simply grab the crot angles or do new decomposition and whether
// to apply jitter or throw an error because jitter has already been applied.
// *** May need to do a frame trace and load the frames (at least the constant ones) ***
// Loop and load the cache
double state[6];
double lt;
NaifStatus::CheckErrors();
double R[3]; // Direction of radial axis of line scan camera
double C[3]; // Direction of cross-track axis
double I[3]; // Direction of in-track axis
double *velocity;
std::vector<double> IB(9);
std::vector<double> CI(9);
SpiceRotation *prot = p_spi->bodyRotation();
SpiceRotation *crot = p_spi->instrumentRotation();
for(std::vector<double>::iterator i = p_cacheTime.begin(); i < p_cacheTime.end(); i++) {
double et = *i;
prot->SetEphemerisTime(et);
crot->SetEphemerisTime(et);
// The following code will be put into method LoadIBcache()
spkezr_c("MRO", et, "IAU_MARS", "NONE", "MARS", state, <);
NaifStatus::CheckErrors();
// Compute the direction of the radial axis (3) of the line scan camera
vscl_c(1. / vnorm_c(state), state, R); // vscl and vnorm only operate on first 3 members of state
// Compute the direction of the cross-track axis (2) of the line scan camera
velocity = state + 3;
vscl_c(1. / vnorm_c(velocity), velocity, C);
vcrss_c(R, C, C);
// Compute the direction of the in-track axis (1) of the line scan camera
vcrss_c(C, R, I);
// Load the matrix IB and enter it into the cache
vequ_c(I, (SpiceDouble( *)) &IB[0]);
vequ_c(C, (SpiceDouble( *)) &IB[3]);
vequ_c(R, (SpiceDouble( *)) &IB[6]);
p_cacheIB.push_back(IB);
// end IB code
// Compute the CIcr matrix - in-track, cross-track, radial frame to constant frame
mxmt_c((SpiceDouble( *)[3]) & (crot->TimeBasedMatrix())[0], (SpiceDouble( *)[3]) & (prot->Matrix())[0],
(SpiceDouble( *)[3]) &CI[0]);
// Put CI into parent cache to use the parent class methods on it
mxmt_c((SpiceDouble( *)[3]) &CI[0], (SpiceDouble( *)[3]) &IB[0], (SpiceDouble( *)[3]) &CI[0]);
p_cache.push_back(CI);
}
p_cachesLoaded = true;
SetSource(Memcache);
NaifStatus::CheckErrors();
}
/*
Function: Calculate the state vector of an object.
Parameters:
object: ID of the target.
t: ephemeris time.
origin: object in the origin.
frame: frame of reference.
Returns:
state: State vector (x,y,z,vx,vy,vz)
*/
int whereIsIt(SpiceChar* object,SpiceDouble t,SpiceChar* origin,SpiceChar* frame,SpiceDouble state[])
{
SpiceDouble state[6],lt
spkezr_c(object,t,frame,"NONE",origin,state,<);
return 0;
}
