/* converts from polar coordinates of ecliptic of date
* to cartesian coordinates of equator 2000
* tjd date
* x array of position
*/
static void ecldat_equ2000(double tjd, double *xpm) {
/* cartesian */
swi_polcart(xpm, xpm);
/* equatorial */
swi_coortrf2(xpm, xpm, -swed.oec.seps, swed.oec.ceps);
/* j2000 */
swi_precess(xpm, tjd, J_TO_J2000);/**/
}
/* computes a planet from osculating elements *
* tjd julian day
* ipl body number
* ipli body number in planetary data structure
* iflag flags
*/
int swi_osc_el_plan(double tjd, double *xp, int ipl, int ipli, double *xearth, double *xsun, char *serr)
{
double pqr[9], x[6];
double eps, K, fac, rho, cose, sine;
double alpha, beta, zeta, sigma, M2, Msgn, M_180_or_0;
double tjd0, tequ, mano, sema, ecce, parg, node, incl, dmot;
double cosnode, sinnode, cosincl, sinincl, cosparg, sinparg;
double M, E;
struct plan_data *pedp = &swed.pldat[SEI_EARTH];
struct plan_data *pdp = &swed.pldat[ipli];
int32 fict_ifl = 0;
int i;
/* orbital elements, either from file or, if file not found,
* from above built-in set
*/
if (read_elements_file(ipl, tjd, &tjd0, &tequ,
&mano, &sema, &ecce, &parg, &node, &incl,
NULL, &fict_ifl, serr) == ERR)
return ERR;
dmot = 0.9856076686 * DEGTORAD / sema / sqrt(sema); /* daily motion */
if (fict_ifl & FICT_GEO)
dmot /= sqrt(SUN_EARTH_MRAT);
cosnode = cos(node);
sinnode = sin(node);
cosincl = cos(incl);
sinincl = sin(incl);
cosparg = cos(parg);
sinparg = sin(parg);
/* Gaussian vector */
pqr[0] = cosparg * cosnode - sinparg * cosincl * sinnode;
pqr[1] = -sinparg * cosnode - cosparg * cosincl * sinnode;
pqr[2] = sinincl * sinnode;
pqr[3] = cosparg * sinnode + sinparg * cosincl * cosnode;
pqr[4] = -sinparg * sinnode + cosparg * cosincl * cosnode;
pqr[5] = -sinincl * cosnode;
pqr[6] = sinparg * sinincl;
pqr[7] = cosparg * sinincl;
pqr[8] = cosincl;
/* Kepler problem */
E = M = swi_mod2PI(mano + (tjd - tjd0) * dmot); /* mean anomaly of date */
/* better E for very high eccentricity and small M */
if (ecce > 0.975) {
M2 = M * RADTODEG;
if (M2 > 150 && M2 < 210) {
M2 -= 180;
M_180_or_0 = 180;
} else
M_180_or_0 = 0;
if (M2 > 330)
M2 -= 360;
if (M2 < 0) {
M2 = -M2;
Msgn = -1;
} else
Msgn = 1;
if (M2 < 30) {
M2 *= DEGTORAD;
alpha = (1 - ecce) / (4 * ecce + 0.5);
beta = M2 / (8 * ecce + 1);
zeta = pow(beta + sqrt(beta * beta + alpha * alpha), 1/3);
sigma = zeta - alpha / 2;
sigma = sigma - 0.078 * sigma * sigma * sigma * sigma * sigma / (1 + ecce);
E = Msgn * (M2 + ecce * (3 * sigma - 4 * sigma * sigma * sigma))
+ M_180_or_0;
}
}
E = swi_kepler(E, M, ecce);
/* position and speed, referred to orbital plane */
if (fict_ifl & FICT_GEO)
K = KGAUSS_GEO / sqrt(sema);
else
K = KGAUSS / sqrt(sema);
cose = cos(E);
sine = sin(E);
fac = sqrt((1 - ecce) * (1 + ecce));
rho = 1 - ecce * cose;
x[0] = sema * (cose - ecce);
x[1] = sema * fac * sine;
x[3] = -K * sine / rho;
x[4] = K * fac * cose / rho;
/* transformation to ecliptic */
xp[0] = pqr[0] * x[0] + pqr[1] * x[1];
xp[1] = pqr[3] * x[0] + pqr[4] * x[1];
xp[2] = pqr[6] * x[0] + pqr[7] * x[1];
xp[3] = pqr[0] * x[3] + pqr[1] * x[4];
xp[4] = pqr[3] * x[3] + pqr[4] * x[4];
xp[5] = pqr[6] * x[3] + pqr[7] * x[4];
/* transformation to equator */
eps = swi_epsiln(tequ);
swi_coortrf(xp, xp, -eps);
swi_coortrf(xp+3, xp+3, -eps);
/* precess to J2000 */
if (tequ != J2000) {
swi_precess(xp, tequ, J_TO_J2000);
swi_precess(xp+3, tequ, J_TO_J2000);
}
/* to solar system barycentre */
if (fict_ifl & FICT_GEO) {
for (i = 0; i <= 5; i++) {
xp[i] += xearth[i];
}
} else {
for (i = 0; i <= 5; i++) {
xp[i] += xsun[i];
}
}
if (pdp->x == xp) {
pdp->teval = tjd; /* for precession! */
pdp->iephe = pedp->iephe;
}
return OK;
}
/* Adjust position from Earth-Moon barycenter to Earth
*
* J = Julian day number
* xemb = rectangular equatorial coordinates of Earth
*/
static void embofs_mosh(double tjd, double *xemb)
{
double T, M, a, L, B, p;
double smp, cmp, s2mp, c2mp, s2d, c2d, sf, cf;
double s2f, sx, cx, xyz[6];
double seps = swed.oec.seps;
double ceps = swed.oec.ceps;
int i;
/* Short series for position of the Moon
*/
T = (tjd-J1900)/36525.0;
/* Mean anomaly of moon (MP) */
a = swe_degnorm(((1.44e-5*T + 0.009192)*T + 477198.8491)*T + 296.104608);
a *= DEGTORAD;
smp = sin(a);
cmp = cos(a);
s2mp = 2.0*smp*cmp; /* sin(2MP) */
c2mp = cmp*cmp - smp*smp; /* cos(2MP) */
/* Mean elongation of moon (D) */
a = swe_degnorm(((1.9e-6*T - 0.001436)*T + 445267.1142)*T + 350.737486);
a = 2.0 * DEGTORAD * a;
s2d = sin(a);
c2d = cos(a);
/* Mean distance of moon from its ascending node (F) */
a = swe_degnorm((( -3.e-7*T - 0.003211)*T + 483202.0251)*T + 11.250889);
a *= DEGTORAD;
sf = sin(a);
cf = cos(a);
s2f = 2.0*sf*cf; /* sin(2F) */
sx = s2d*cmp - c2d*smp; /* sin(2D - MP) */
cx = c2d*cmp + s2d*smp; /* cos(2D - MP) */
/* Mean longitude of moon (LP) */
L = ((1.9e-6*T - 0.001133)*T + 481267.8831)*T + 270.434164;
/* Mean anomaly of sun (M) */
M = swe_degnorm((( -3.3e-6*T - 1.50e-4)*T + 35999.0498)*T + 358.475833);
/* Ecliptic longitude of the moon */
L = L
+ 6.288750*smp
+ 1.274018*sx
+ 0.658309*s2d
+ 0.213616*s2mp
- 0.185596*sin( DEGTORAD * M )
- 0.114336*s2f;
/* Ecliptic latitude of the moon */
a = smp*cf;
sx = cmp*sf;
B = 5.128189*sf
+ 0.280606*(a+sx) /* sin(MP+F) */
+ 0.277693*(a-sx) /* sin(MP-F) */
+ 0.173238*(s2d*cf - c2d*sf); /* sin(2D-F) */
B *= DEGTORAD;
/* Parallax of the moon */
p = 0.950724
+0.051818*cmp
+0.009531*cx
+0.007843*c2d
+0.002824*c2mp;
p *= DEGTORAD;
/* Elongation of Moon from Sun
*/
L = swe_degnorm(L);
L *= DEGTORAD;
/* Distance in au */
a = 4.263523e-5/sin(p);
/* Convert to rectangular ecliptic coordinates */
xyz[0] = L;
xyz[1] = B;
xyz[2] = a;
swi_polcart(xyz, xyz);
/* Convert to equatorial */
swi_coortrf2(xyz, xyz, -seps, ceps);
/* Precess to equinox of J2000.0 */
swi_precess(xyz, tjd, J_TO_J2000);/**/
/* now emb -> earth */
for (i = 0; i <= 2; i++)
xemb[i] -= xyz[i] / (EARTH_MOON_MRAT + 1.0);
}
int swe_sx_nod_aps(double tjd_et, int ind, int iflag,
int method,
double *xnasc, double *xndsc,
double *xperi, double *xaphe,
char *serr)
{
int ij, i, j,ipl,fEquatorT,fUseJ2000T;
int32 iplx;
int32 ipli;
int istart, iend;
int32 iflJ2000;
double plm;
double t = (tjd_et - J2000) / 36525, dt;
double x[6], xx[24], *xp, xobs[6], x2000[6];
double xpos[3][6], xnorm[6];
double xposm[6];
double xn[3][6], xs[3][6];
double xq[3][6], xa[3][6];
double xobs2[6], x2[6];
double *xna, *xnd, *xpe, *xap;
double incl, sema, ecce, parg, ea, vincl, vsema, vecce, pargx, eax;
struct plan_data *pedp = &swed.pldat[SEI_EARTH];
struct plan_data *psbdp = &swed.pldat[SEI_SUNBARY];
struct plan_data pldat;
double *xsun = psbdp->x;
double *xear = pedp->x;
double *ep;
double Gmsm, dzmin;
double rxy, rxyz, fac, sgn;
double sinnode, cosnode, sinincl, cosincl, sinu, cosu, sinE, cosE, cosE2;
double uu, ny, ny2, c2, v2, pp, ro, ro2, rn, rn2;
struct epsilon *oe;
AS_BOOL is_true_nodaps = FALSE;
AS_BOOL do_aberr = !(iflag & (SEFLG_TRUEPOS | SEFLG_NOABERR));
AS_BOOL do_defl = !(iflag & SEFLG_TRUEPOS) && !(iflag & SEFLG_NOGDEFL);
AS_BOOL do_focal_point = method & SE_NODBIT_FOPOINT;
AS_BOOL ellipse_is_bary = FALSE;
int32 iflg0;
/* function calls for Pluto with asteroid number 134340
* are treated as calls for Pluto as main body SE_PLUTO */
ipl = AlToSweObj(ind);
if (ipl == SE_WHITE_MOON)
ipl = SE_AST_OFFSET+MaxNumberedAsteroid;
if (ipl == SE_AST_OFFSET + 134340)
ipl = SE_PLUTO;
xna = xx;
xnd = xx+6;
xpe = xx+12;
xap = xx+18;
xpos[0][0] = 0; /* to shut up mint */
/* to get control over the save area: */
swi_force_app_pos_etc();
method %= SE_NODBIT_FOPOINT;
ipli = ipl;
if (ipl == SE_SUN)
ipli = SE_EARTH;
if (ipl == SE_MOON)
{
do_defl = FALSE;
if (!(iflag & SEFLG_HELCTR))
do_aberr = FALSE;
}
iflg0 = (iflag & (SEFLG_EPHMASK|SEFLG_NONUT)) | SEFLG_SPEED | SEFLG_TRUEPOS;
if (ipli != SE_MOON)
iflg0 |= SEFLG_HELCTR;
if (ipl == SE_MEAN_NODE || ipl == SE_TRUE_NODE ||
ipl == SE_MEAN_APOG || ipl == SE_OSCU_APOG ||
ipl < 0 ||
(ipl >= SE_NPLANETS && ipl <= SE_AST_OFFSET))
{
/*(ipl >= SE_FICT_OFFSET && ipl - SE_FICT_OFFSET < SE_NFICT_ELEM)) */
if (serr != NULL)
sprintf(serr, "nodes/apsides for planet %5.0f are not implemented", (double) ipl);
if (xnasc != NULL)
for (i = 0; i <= 5; i++)
xnasc[i] = 0;
if (xndsc != NULL)
for (i = 0; i <= 5; i++)
xndsc[i] = 0;
if (xaphe != NULL)
for (i = 0; i <= 5; i++)
xaphe[i] = 0;
if (xperi != NULL)
for (i = 0; i <= 5; i++)
xperi[i] = 0;
return ERR;
}
for (i = 0; i < 24; i++)
xx[i] = 0;
/***************************************
* mean nodes and apsides
***************************************/
/* mean points only for Sun - Neptune */
if ((method == 0 || (method & SE_NODBIT_MEAN)) &&
((ipl >= SE_SUN && ipl <= SE_NEPTUNE) || ipl == SE_EARTH))
{
if (ipl == SE_MOON)
{
swi_mean_lunar_elements(tjd_et, &xna[0], &xna[3], &xpe[0], &xpe[3]);
incl = MOON_MEAN_INCL;
vincl = 0;
ecce = MOON_MEAN_ECC;
vecce = 0;
sema = MOON_MEAN_DIST / AUNIT;
vsema = 0;
}
else
{
iplx = ipl_to_elem[ipl];
ep = el_incl[iplx];
incl = ep[0] + ep[1] * t + ep[2] * t * t + ep[3] * t * t * t;
vincl = ep[1] / 36525;
ep = el_sema[iplx];
sema = ep[0] + ep[1] * t + ep[2] * t * t + ep[3] * t * t * t;
vsema = ep[1] / 36525;
ep = el_ecce[iplx];
ecce = ep[0] + ep[1] * t + ep[2] * t * t + ep[3] * t * t * t;
vecce = ep[1] / 36525;
ep = el_node[iplx];
/* ascending node */
xna[0] = ep[0] + ep[1] * t + ep[2] * t * t + ep[3] * t * t * t;
xna[3] = ep[1] / 36525;
/* perihelion */
ep = el_peri[iplx];
xpe[0] = ep[0] + ep[1] * t + ep[2] * t * t + ep[3] * t * t * t;
xpe[3] = ep[1] / 36525;
}
/* descending node */
xnd[0] = swe_degnorm(xna[0] + 180);
xnd[3] = xna[3];
/* angular distance of perihelion from node */
parg = xpe[0] = swe_degnorm(xpe[0] - xna[0]);
pargx = xpe[3] = swe_degnorm(xpe[0] + xpe[3] - xna[3]);
/* transform from orbital plane to mean ecliptic of date */
swe_cotrans(xpe, xpe, -incl);
/* xpe+3 is aux. position, not speed!!! */
swe_cotrans(xpe+3, xpe+3, -incl-vincl);
/* add node again */
xpe[0] = swe_degnorm(xpe[0] + xna[0]);
/* xpe+3 is aux. position, not speed!!! */
xpe[3] = swe_degnorm(xpe[3] + xna[0] + xna[3]);
/* speed */
xpe[3] = swe_degnorm(xpe[3] - xpe[0]);
/* heliocentric distance of perihelion and aphelion */
xpe[2] = sema * (1 - ecce);
xpe[5] = (sema + vsema) * (1 - ecce - vecce) - xpe[2];
/* aphelion */
xap[0] = swe_degnorm(xpe[0] + 180);
xap[1] = -xpe[1];
xap[3] = xpe[3];
xap[4] = -xpe[4];
if (do_focal_point)
{
xap[2] = sema * ecce * 2;
xap[5] = (sema + vsema) * (ecce + vecce) * 2 - xap[2];
}
else
{
xap[2] = sema * (1 + ecce);
xap[5] = (sema + vsema) * (1 + ecce + vecce) - xap[2];
}
/* heliocentric distance of nodes */
ea = atan(tan(-parg * DEGTORAD / 2) * sqrt((1-ecce)/(1+ecce))) * 2;
eax = atan(tan(-pargx * DEGTORAD / 2) * sqrt((1-ecce-vecce)/(1+ecce+vecce))) * 2;
xna[2] = sema * (cos(ea) - ecce) / cos(parg * DEGTORAD);
xna[5] = (sema+vsema) * (cos(eax) - ecce - vecce) / cos(pargx * DEGTORAD);
xna[5] -= xna[2];
ea = atan(tan((180 - parg) * DEGTORAD / 2) * sqrt((1-ecce)/(1+ecce))) * 2;
eax = atan(tan((180 - pargx) * DEGTORAD / 2) * sqrt((1-ecce-vecce)/(1+ecce+vecce))) * 2;
xnd[2] = sema * (cos(ea) - ecce) / cos((180 - parg) * DEGTORAD);
xnd[5] = (sema+vsema) * (cos(eax) - ecce - vecce) / cos((180 - pargx) * DEGTORAD);
xnd[5] -= xnd[2];
/* no light-time correction because speed is extremely small */
for (i = 0, xp = xx; i < 4; i++, xp += 6)
{
/* to cartesian coordinates */
xp[0] *= DEGTORAD;
xp[1] *= DEGTORAD;
xp[3] *= DEGTORAD;
xp[4] *= DEGTORAD;
swi_polcart_sp(xp, xp);
}
/***************************************
* "true" or osculating nodes and apsides
***************************************/
} else {
/* first, we need a heliocentric distance of the planet */
if (swe_calc(tjd_et, ipli, iflg0, x, serr) == ERR)
{
if (FRiyalNumbered(tjd_et,ind,fTrue))
{
x[0]=planet[ind];
x[1]=planetalt[ind];
x[2]=planetdis[ind];
x[3]=ret[ind];
x[4]=altret[ind];
x[5]=disret[ind];
}
else return ERR;
}
iflJ2000 = (iflag & SEFLG_EPHMASK)|SEFLG_J2000|SEFLG_EQUATORIAL|SEFLG_XYZ|SEFLG_TRUEPOS|SEFLG_NONUT|SEFLG_SPEED;
ellipse_is_bary = FALSE;
if (ipli != SE_MOON)
{
if ((method & SE_NODBIT_OSCU_BAR) && x[2] > 6)
{
iflJ2000 |= SEFLG_BARYCTR; /* only planets beyond Jupiter */
ellipse_is_bary = TRUE;
}
else
{
iflJ2000 |= SEFLG_HELCTR;
}
}
/* we need three positions and three speeds
* for three nodes/apsides. from the three node positions,
* the speed of the node will be computed. */
if (ipli == SE_MOON)
{
dt = NODE_CALC_INTV;
dzmin = 1e-15;
Gmsm = GEOGCONST * (1 + 1 / EARTH_MOON_MRAT) /AUNIT/AUNIT/AUNIT*86400.0*86400.0;
}
else
{
if ((ipli >= SE_MERCURY && ipli <= SE_PLUTO) || ipli == SE_EARTH)
plm = 1 / plmass[ipl_to_elem[ipl]];
else
plm = 0;
dt = NODE_CALC_INTV * 10 * x[2];
dzmin = 1e-15 * dt / NODE_CALC_INTV;
Gmsm = HELGRAVCONST * (1 + plm) /AUNIT/AUNIT/AUNIT*86400.0*86400.0;
}
if (iflag & SEFLG_SPEED)
{
istart = 0;
iend = 2;
}
else
{
istart = iend = 0;
dt = 0;
}
for (i = istart, t = tjd_et - dt; i <= iend; i++, t += dt)
{
if (istart == iend)
t = tjd_et;
if (swe_calc(t, ipli, iflJ2000, xpos[i], serr) == ERR)
{
fUseJ2000T=fUseJ2000;
fEquatorT=us.fEquator;
fUseJ2000=fTrue;
us.fEquator=fTrue;
if (FRiyalNumbered(t,ind,fTrue))
{
xpos[i][0]=spacex[ind];
xpos[i][1]=spacey[ind];
xpos[i][2]=spacez[ind];
xpos[i][3]=spacedx[ind];
xpos[i][4]=spacedy[ind];
xpos[i][5]=spacedz[ind];
fUseJ2000=fUseJ2000T;
us.fEquator=fEquatorT;
}
else return ERR;
}
/* the EMB is used instead of the earth */
if (ipli == SE_EARTH)
{
if (swe_calc(t, SE_MOON, iflJ2000 & ~(SEFLG_BARYCTR|SEFLG_HELCTR), xposm, serr) == ERR)
return ERR;
for (j = 0; j <= 2; j++)
xpos[i][j] += xposm[j] / (EARTH_MOON_MRAT + 1.0);
}
swi_plan_for_osc_elem(iflg0, t, xpos[i]);
}
for (i = istart; i <= iend; i++)
{
if (fabs(xpos[i][5]) < dzmin)
xpos[i][5] = dzmin;
fac = xpos[i][2] / xpos[i][5];
sgn = xpos[i][5] / fabs(xpos[i][5]);
for (j = 0; j <= 2; j++)
{
xn[i][j] = (xpos[i][j] - fac * xpos[i][j+3]) * sgn;
xs[i][j] = -xn[i][j];
}
}
for (i = istart; i <= iend; i++)
{
/* node */
rxy = sqrt(xn[i][0] * xn[i][0] + xn[i][1] * xn[i][1]);
cosnode = xn[i][0] / rxy;
sinnode = xn[i][1] / rxy;
/* inclination */
swi_cross_prod(xpos[i], xpos[i]+3, xnorm);
rxy = xnorm[0] * xnorm[0] + xnorm[1] * xnorm[1];
c2 = (rxy + xnorm[2] * xnorm[2]);
rxyz = sqrt(c2);
rxy = sqrt(rxy);
sinincl = rxy / rxyz;
cosincl = sqrt(1 - sinincl * sinincl);
if (xnorm[2] < 0) cosincl = -cosincl; /* retrograde asteroid, e.g. 20461 Dioretsa */
/* argument of latitude */
cosu = xpos[i][0] * cosnode + xpos[i][1] * sinnode;
sinu = xpos[i][2] / sinincl;
uu = atan2(sinu, cosu);
/* semi-axis */
rxyz = sqrt(square_sum(xpos[i]));
v2 = square_sum((xpos[i]+3));
sema = 1 / (2 / rxyz - v2 / Gmsm);
/* eccentricity */
pp = c2 / Gmsm;
ecce = sqrt(1 - pp / sema);
/* eccentric anomaly */
cosE = 1 / ecce * (1 - rxyz / sema);
sinE = 1 / ecce / sqrt(sema * Gmsm) * dot_prod(xpos[i], (xpos[i]+3));
/* true anomaly */
ny = 2 * atan(sqrt((1+ecce)/(1-ecce)) * sinE / (1 + cosE));
/* distance of perihelion from ascending node */
xq[i][0] = swi_mod2PI(uu - ny);
xq[i][1] = 0; /* latitude */
xq[i][2] = sema * (1 - ecce); /* distance of perihelion */
/* transformation to ecliptic coordinates */
swi_polcart(xq[i], xq[i]);
swi_coortrf2(xq[i], xq[i], -sinincl, cosincl);
swi_cartpol(xq[i], xq[i]);
/* adding node, we get perihelion in ecl. coord. */
xq[i][0] += atan2(sinnode, cosnode);
xa[i][0] = swi_mod2PI(xq[i][0] + PI);
xa[i][1] = -xq[i][1];
if (do_focal_point)
{
xa[i][2] = sema * ecce * 2; /* distance of aphelion */
}
else
{
xa[i][2] = sema * (1 + ecce); /* distance of aphelion */
}
swi_polcart(xq[i], xq[i]);
swi_polcart(xa[i], xa[i]);
/* new distance of node from orbital ellipse:
* true anomaly of node: */
ny = swi_mod2PI(ny - uu);
ny2 = swi_mod2PI(ny + PI);
/* eccentric anomaly */
cosE = cos(2 * atan(tan(ny / 2) / sqrt((1+ecce) / (1-ecce))));
cosE2 = cos(2 * atan(tan(ny2 / 2) / sqrt((1+ecce) / (1-ecce))));
/* new distance */
rn = sema * (1 - ecce * cosE);
rn2 = sema * (1 - ecce * cosE2);
/* old node distance */
ro = sqrt(square_sum(xn[i]));
ro2 = sqrt(square_sum(xs[i]));
/* correct length of position vector */
for (j = 0; j <= 2; j++)
{
xn[i][j] *= rn / ro;
xs[i][j] *= rn2 / ro2;
}
}
for (i = 0; i <= 2; i++)
{
if (iflag & SEFLG_SPEED)
{
xpe[i] = xq[1][i];
xpe[i+3] = (xq[2][i] - xq[0][i]) / dt / 2;
xap[i] = xa[1][i];
xap[i+3] = (xa[2][i] - xa[0][i]) / dt / 2;
xna[i] = xn[1][i];
xna[i+3] = (xn[2][i] - xn[0][i]) / dt / 2;
xnd[i] = xs[1][i];
xnd[i+3] = (xs[2][i] - xs[0][i]) / dt / 2;
}
else
{
xpe[i] = xq[0][i];
xpe[i+3] = 0;
xap[i] = xa[0][i];
xap[i+3] = 0;
xna[i] = xn[0][i];
xna[i+3] = 0;
xnd[i] = xs[0][i];
xnd[i+3] = 0;
}
}
is_true_nodaps = TRUE;
}
/* to set the variables required in the save area,
* i.e. ecliptic, nutation, barycentric sun, earth
* we compute the planet */
if (ipli == SE_MOON && (iflag & (SEFLG_HELCTR | SEFLG_BARYCTR)))
{
swi_force_app_pos_etc();
if (swe_calc(tjd_et, SE_SUN, iflg0, x, serr) == ERR)
return ERR;
} else {
if (swe_calc(tjd_et, ipli, iflg0 | (iflag & SEFLG_TOPOCTR), x, serr) == ERR)
{
if (FRiyalNumbered(tjd_et,ind,iflg0 && SEFLG_HELCTR))
{
x[0]=planet[ind];
x[1]=planetalt[ind];
x[2]=planetdis[ind];
x[3]=ret[ind];
x[4]=altret[ind];
x[5]=disret[ind];
}
else return ERR;
}
}
/***********************
* position of observer
***********************/
if (iflag & SEFLG_TOPOCTR)
{
/* geocentric position of observer */
if (swi_get_observer(tjd_et, iflag, FALSE, xobs, serr) != OK)
return ERR;
/*for (i = 0; i <= 5; i++)
xobs[i] = swed.topd.xobs[i];*/
}
else
{
for (i = 0; i <= 5; i++)
xobs[i] = 0;
}
if (iflag & (SEFLG_HELCTR | SEFLG_BARYCTR))
{
if ((iflag & SEFLG_HELCTR) && !(iflag & SEFLG_MOSEPH))
for (i = 0; i <= 5; i++)
xobs[i] = xsun[i];
}
else if (ipl == SE_SUN && !(iflag & SEFLG_MOSEPH))
{
for (i = 0; i <= 5; i++)
xobs[i] = xsun[i];
}
else
{
/* barycentric position of observer */
for (i = 0; i <= 5; i++)
xobs[i] += xear[i];
}
/* ecliptic obliqity */
if (iflag & SEFLG_J2000)
oe = &swed.oec2000;
else
oe = &swed.oec;
/*************************************************
* conversions shared by mean and osculating points
*************************************************/
for (ij = 0, xp = xx; ij < 4; ij++, xp += 6)
{
/* no nodes for earth */
if (ipli == SE_EARTH && ij <= 1)
{
for (i = 0; i <= 5; i++)
xp[i] = 0;
continue;
}
/*********************
* to equator
*********************/
if (is_true_nodaps && !(iflag & SEFLG_NONUT))
{
swi_coortrf2(xp, xp, -swed.nut.snut, swed.nut.cnut);
if (iflag & SEFLG_SPEED)
swi_coortrf2(xp+3, xp+3, -swed.nut.snut, swed.nut.cnut);
}
swi_coortrf2(xp, xp, -oe->seps, oe->ceps);
swi_coortrf2(xp+3, xp+3, -oe->seps, oe->ceps);
if (is_true_nodaps)
{
/****************************
* to mean ecliptic of date
****************************/
if (!(iflag & SEFLG_NONUT))
swi_nutate(xp, iflag, TRUE);
}
/*********************
* to J2000
*********************/
swi_precess(xp, tjd_et, J_TO_J2000);
if (iflag & SEFLG_SPEED)
swi_precess_speed(xp, tjd_et, J_TO_J2000);
/*********************
* to barycenter
*********************/
if (ipli == SE_MOON)
{
for (i = 0; i <= 5; i++)
xp[i] += xear[i];
}
else
{
if (!(iflag & SEFLG_MOSEPH) && !ellipse_is_bary)
for (j = 0; j <= 5; j++)
xp[j] += xsun[j];
}
/*********************
* to correct center
*********************/
for (j = 0; j <= 5; j++)
xp[j] -= xobs[j];
/* geocentric perigee/apogee of sun */
if (ipl == SE_SUN && !(iflag & (SEFLG_HELCTR | SEFLG_BARYCTR)))
for (j = 0; j <= 5; j++)
xp[j] = -xp[j];
/*********************
* light deflection
*********************/
dt = sqrt(square_sum(xp)) * AUNIT / CLIGHT / 86400.0;
if (do_defl)
swi_deflect_light(xp, dt, iflag);
/*********************
* aberration
*********************/
if (do_aberr)
{
swi_aberr_light(xp, xobs, iflag);
/*
* Apparent speed is also influenced by
* the difference of speed of the earth between t and t-dt.
* Neglecting this would result in an error of several 0.1"
*/
if (iflag & SEFLG_SPEED)
{
/* get barycentric sun and earth for t-dt into save area */
if (swe_calc(tjd_et - dt, ipli, iflg0 | (iflag & SEFLG_TOPOCTR), x2, serr) == ERR)
{
if (FRiyalNumbered(tjd_et-dt,ind,iflg0 && SEFLG_HELCTR))
{
x2[0]=planet[ind];
x2[1]=planetalt[ind];
x2[2]=planetdis[ind];
x2[3]=ret[ind];
x2[4]=altret[ind];
x2[5]=disret[ind];
}
else return ERR;
}
if (iflag & SEFLG_TOPOCTR)
{
/* geocentric position of observer */
/* if (swi_get_observer(tjd_et - dt, iflag, FALSE, xobs, serr) != OK)
return ERR;*/
for (i = 0; i <= 5; i++)
xobs2[i] = swed.topd.xobs[i];
}
else
{
for (i = 0; i <= 5; i++)
xobs2[i] = 0;
}
if (iflag & (SEFLG_HELCTR | SEFLG_BARYCTR))
{
if ((iflag & SEFLG_HELCTR) && !(iflag & SEFLG_MOSEPH))
for (i = 0; i <= 5; i++)
xobs2[i] = xsun[i];
}
else if (ipl == SE_SUN && !(iflag & SEFLG_MOSEPH))
{
for (i = 0; i <= 5; i++)
xobs2[i] = xsun[i];
}
else
{
/* barycentric position of observer */
for (i = 0; i <= 5; i++)
xobs2[i] += xear[i];
}
for (i = 3; i <= 5; i++)
xp[i] += xobs[i] - xobs2[i];
/* The above call of swe_calc() has destroyed the
* parts of the save area
* (i.e. bary sun, earth nutation matrix!).
* to restore it:
*/
if (swe_calc(tjd_et, SE_SUN, iflg0 | (iflag & SEFLG_TOPOCTR), x2, serr) == ERR)
return ERR;
}
}
/*********************
* precession
*********************/
/* save J2000 coordinates; required for sidereal positions */
for (j = 0; j <= 5; j++)
x2000[j] = xp[j];
if (!(iflag & SEFLG_J2000))
{
swi_precess(xp, tjd_et, J2000_TO_J);
if (iflag & SEFLG_SPEED)
swi_precess_speed(xp, tjd_et, J2000_TO_J);
}
/*********************
* nutation
*********************/
if (!(iflag & SEFLG_NONUT))
swi_nutate(xp, iflag, FALSE);
/* now we have equatorial cartesian coordinates; keep them */
for (j = 0; j <= 5; j++)
pldat.xreturn[18+j] = xp[j];
/************************************************
* transformation to ecliptic. *
* with sidereal calc. this will be overwritten *
* afterwards. *
************************************************/
swi_coortrf2(xp, xp, oe->seps, oe->ceps);
if (iflag & SEFLG_SPEED)
swi_coortrf2(xp+3, xp+3, oe->seps, oe->ceps);
if (!(iflag & SEFLG_NONUT))
{
swi_coortrf2(xp, xp, swed.nut.snut, swed.nut.cnut);
if (iflag & SEFLG_SPEED)
swi_coortrf2(xp+3, xp+3, swed.nut.snut, swed.nut.cnut);
}
/* now we have ecliptic cartesian coordinates */
for (j = 0; j <= 5; j++)
pldat.xreturn[6+j] = xp[j];
/************************************
* sidereal positions *
************************************/
if (iflag & SEFLG_SIDEREAL)
{
/* project onto ecliptic t0 */
if (swed.sidd.sid_mode & SE_SIDBIT_ECL_T0)
{
if (swi_trop_ra2sid_lon(x2000, pldat.xreturn+6, pldat.xreturn+18, iflag, serr) != OK)
return ERR;
/* project onto solar system equator */
}
else if (swed.sidd.sid_mode & SE_SIDBIT_SSY_PLANE)
{
if (swi_trop_ra2sid_lon_sosy(x2000, pldat.xreturn+6, pldat.xreturn+18, iflag, serr) != OK)
return ERR;
}
else
{
/* traditional algorithm */
swi_cartpol_sp(pldat.xreturn+6, pldat.xreturn);
pldat.xreturn[0] -= swe_get_ayanamsa(tjd_et) * DEGTORAD;
swi_polcart_sp(pldat.xreturn, pldat.xreturn+6);
}
}
if ((iflag & SEFLG_XYZ) && (iflag & SEFLG_EQUATORIAL))
{
for (j = 0; j <= 5; j++)
xp[j] = pldat.xreturn[18+j];
continue;
}
if (iflag & SEFLG_XYZ)
{
for (j = 0; j <= 5; j++)
xp[j] = pldat.xreturn[6+j];
continue;
}
/************************************************
* transformation to polar coordinates *
************************************************/
swi_cartpol_sp(pldat.xreturn+18, pldat.xreturn+12);
swi_cartpol_sp(pldat.xreturn+6, pldat.xreturn);
/**********************
* radians to degrees *
**********************/
for (j = 0; j < 2; j++)
{
pldat.xreturn[j] *= RADTODEG; /* ecliptic */
pldat.xreturn[j+3] *= RADTODEG;
pldat.xreturn[j+12] *= RADTODEG; /* equator */
pldat.xreturn[j+15] *= RADTODEG;
}
if (iflag & SEFLG_EQUATORIAL)
{
for (j = 0; j <= 5; j++)
xp[j] = pldat.xreturn[12+j];
continue;
}
else
{
for (j = 0; j <= 5; j++)
xp[j] = pldat.xreturn[j];
continue;
}
}
for (i = 0; i <= 5; i++)
{
if (i > 2 && !(iflag & SEFLG_SPEED))
xna[i] = xnd[i] = xpe[i] = xap[i] = 0;
if (xnasc != NULL)
xnasc[i] = xna[i];
if (xndsc != NULL)
xndsc[i] = xnd[i];
if (xperi != NULL)
xperi[i] = xpe[i];
if (xaphe != NULL)
xaphe[i] = xap[i];
}
return OK;
}