/* Get arbitrary planetary barycenter position. Get the
velocity (in AU/YR) too, if desired. */
void
bodycenter_ssbary(double jd,
double *xyz,
int body,
double *vxyz)
{
double posn[3], vel[3];
static int init=0;
int i;
if (!init) {
if (Initialize_Ephemeris()) exit(1);
init = 1;
}
if (vxyz==NULL) {
Interpolate_Position(jd, body, posn);
} else {
Interpolate_State(jd, body, posn, vel);
}
for (i=0; i<3; i++) {
xyz[i] = posn[i] / R1.AU;
}
if (vxyz!=NULL) /* convert km/s to AU/YR: */
for (i=0; i<3; i++) {
vxyz[i] = vel[i] * (86400. * 365.25) / R1.AU ;
}
return;
}
int dele::detR(double *x, double *y, double *z, double Time, int nplanet, int proizv, int centr, int sk)
{
double xt, yt, zt;
double Em;
int npl = 0;
stateData State;
if((nplanet==GEOCENTR_NUM))
{
npl = 1;
nplanet = EARTH_NUM;
}
if(nplanet==MOON_NUM)
{
npl = 2;
nplanet = EARTH_NUM;
}
Interpolate_State( Time , nplanet , &State );
if(proizv)
{
*x = State.Velocity[0];
*y = State.Velocity[1];
*z = State.Velocity[2];
*x = *x/H1.data.AU*86400.0;
*y = *y/H1.data.AU*86400.0;
*z = *z/H1.data.AU*86400.0;
}
else
{
*x = State.Position[0];
*y = State.Position[1];
*z = State.Position[2];
*x = *x/H1.data.AU;
*y = *y/H1.data.AU;
*z = *z/H1.data.AU;
}
if(npl)
{
xt = yt = zt = 0.0;
Interpolate_State( Time , MOON_NUM , &State );
if(proizv)
{
xt = State.Velocity[0];
yt = State.Velocity[1];
zt = State.Velocity[2];
xt = xt/H1.data.AU*86400.0;
yt = yt/H1.data.AU*86400.0;
zt = zt/H1.data.AU*86400.0;
}
else
{
xt = State.Position[0];
yt = State.Position[1];
zt = State.Position[2];
xt = xt/H1.data.AU;
yt = yt/H1.data.AU;
zt = zt/H1.data.AU;
}
Em = H1.data.EMRAT;
if(npl==1)
{
*x = *x - (1.0/(1.0+Em))*xt;
*y = *y - (1.0/(1.0+Em))*yt;
*z = *z - (1.0/(1.0+Em))*zt;
}
if(npl==2)
{
*x = *x + (Em/(1.0+Em))*xt;
*y = *y + (Em/(1.0+Em))*yt;
*z = *z + (Em/(1.0+Em))*zt;
}
}
if(centr)
{
this->detR(&xt, &yt, &zt, Time, SUN_NUM, proizv, 0, 0);
*x -= xt;
*y -= yt;
*z -= zt;
}
if(sk)
{
xt = *x;
yt = *y;
zt = *z;
*y = cos(EKV)*yt + sin(EKV)*zt;
*z = -sin(EKV)*yt + cos(EKV)*zt;
}
return 0;
}
int dele::detState(double *x, double *y, double *z, double *vx, double *vy, double *vz, double Time, int nplanet, int centr, int sk)
{
double xt, yt, zt;
double vxt, vyt, vzt;
double Em;
int npl = 0;
stateData State;
if((nplanet==GEOCENTR_NUM))
{
npl = 1;
nplanet = EARTH_NUM;
}
if(nplanet==MOON_NUM)
{
npl = 2;
nplanet = EARTH_NUM;
}
Interpolate_State( Time , nplanet , &State );
*vx = State.Velocity[0];
*vy = State.Velocity[1];
*vz = State.Velocity[2];
*vx = *vx/H1.data.AU*86400.0;
*vy = *vy/H1.data.AU*86400.0;
*vz = *vz/H1.data.AU*86400.0;
*x = State.Position[0];
*y = State.Position[1];
*z = State.Position[2];
*x = *x/H1.data.AU;
*y = *y/H1.data.AU;
*z = *z/H1.data.AU;
if(npl)
{
xt = yt = zt = 0.0;
vxt = vyt = vzt = 0.0;
Interpolate_State( Time , MOON_NUM , &State );
vxt = State.Velocity[0];
vyt = State.Velocity[1];
vzt = State.Velocity[2];
vxt = vxt/H1.data.AU*86400.0;
vyt = vyt/H1.data.AU*86400.0;
vzt = vzt/H1.data.AU*86400.0;
xt = State.Position[0];
yt = State.Position[1];
zt = State.Position[2];
xt = xt/H1.data.AU;
yt = yt/H1.data.AU;
zt = zt/H1.data.AU;
Em = H1.data.EMRAT;
if(npl==1)
{
*x = *x - (1.0/(1.0+Em))*xt;
*y = *y - (1.0/(1.0+Em))*yt;
*z = *z - (1.0/(1.0+Em))*zt;
*vx = *vx - (1.0/(1.0+Em))*vxt;
*vy = *vy - (1.0/(1.0+Em))*vyt;
*vz = *vz - (1.0/(1.0+Em))*vzt;
}
if(npl==2)
{
*x = *x + (Em/(1.0+Em))*xt;
*y = *y + (Em/(1.0+Em))*yt;
*z = *z + (Em/(1.0+Em))*zt;
*vx = *vx + (Em/(1.0+Em))*vxt;
*vy = *vy + (Em/(1.0+Em))*vyt;
*vz = *vz + (Em/(1.0+Em))*vzt;
}
}
if(centr)
{
Interpolate_State( Time , SUN_NUM , &State );
*x -= State.Position[0]/H1.data.AU;
*y -= State.Position[1]/H1.data.AU;
*z -= State.Position[2]/H1.data.AU;
*vx -= State.Velocity[0]/H1.data.AU*86400.0;
*vy -= State.Velocity[1]/H1.data.AU*86400.0;
*vz -= State.Velocity[2]/H1.data.AU*86400.0;
}
if(sk)
{
xt = *x;
yt = *y;
zt = *z;
*y = cos(EKV)*yt + sin(EKV)*zt;
*z = -sin(EKV)*yt + cos(EKV)*zt;
xt = *vx;
yt = *vy;
zt = *vz;
*vy = cos(EKV)*yt + sin(EKV)*zt;
*vz = -sin(EKV)*yt + cos(EKV)*zt;
}
return 0;
}
