/* 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);/**/
}
/* 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);
}
/* Moshier ephemeris.
* computes heliocentric cartesian equatorial coordinates of
* equinox 2000
* for earth and a planet
* tjd julian day
* ipli internal SWEPH planet number
* xp array of 6 doubles for planet's position and speed
* xe earth's
* serr error string
*/
int swi_moshplan(double tjd, int ipli, AS_BOOL do_save, double *xpret, double *xeret, char *serr)
{
int i;
int do_earth = FALSE;
double dx[3], x2[3], xxe[6], xxp[6];
double *xp, *xe;
double dt;
char s[AS_MAXCH];
int iplm = pnoint2msh[ipli];
struct plan_data *pdp = &swed.pldat[ipli];
struct plan_data *pedp = &swed.pldat[SEI_EARTH];
double seps2000 = swed.oec2000.seps;
double ceps2000 = swed.oec2000.ceps;
if (do_save) {
xp = pdp->x;
xe = pedp->x;
} else {
xp = xxp;
xe = xxe;
}
if (do_save || ipli == SEI_EARTH || xeret != NULL)
do_earth = TRUE;
/* tjd beyond ephemeris limits, give some margin for spped at edge */
if (tjd < MOSHPLEPH_START - 0.3 || tjd > MOSHPLEPH_END + 0.3) {
if (serr != NULL) {
sprintf(s, "jd %f outside Moshier planet range %.2f .. %.2f ",
tjd, MOSHPLEPH_START, MOSHPLEPH_END);
if (strlen(serr) + strlen(s) < AS_MAXCH)
strcat(serr, s);
}
return(ERR);
}
/* earth, for geocentric position */
if (do_earth) {
if (tjd == pedp->teval
&& pedp->iephe == SEFLG_MOSEPH) {
xe = pedp->x;
} else {
/* emb */
swi_moshplan2(tjd, pnoint2msh[SEI_EMB], xe); /* emb hel. ecl. 2000 polar */
swi_polcart(xe, xe); /* to cartesian */
swi_coortrf2(xe, xe, -seps2000, ceps2000);/* and equator 2000 */
embofs_mosh(tjd, xe); /* emb -> earth */
if (do_save) {
pedp->teval = tjd;
pedp->xflgs = -1;
pedp->iephe = SEFLG_MOSEPH;
}
/* one more position for speed. */
swi_moshplan2(tjd - PLAN_SPEED_INTV, pnoint2msh[SEI_EMB], x2);
swi_polcart(x2, x2);
swi_coortrf2(x2, x2, -seps2000, ceps2000);
embofs_mosh(tjd - PLAN_SPEED_INTV, x2);/**/
for (i = 0; i <= 2; i++)
dx[i] = (xe[i] - x2[i]) / PLAN_SPEED_INTV;
/* store speed */
for (i = 0; i <= 2; i++) {
xe[i+3] = dx[i];
}
}
if (xeret != NULL)
for (i = 0; i <= 5; i++)
xeret[i] = xe[i];
}
/* earth is the planet wanted */
if (ipli == SEI_EARTH) {
xp = xe;
} else {
/* other planet */
/* if planet has already been computed, return */
if (tjd == pdp->teval && pdp->iephe == SEFLG_MOSEPH) {
xp = pdp->x;
} else {
swi_moshplan2(tjd, iplm, xp);
swi_polcart(xp, xp);
swi_coortrf2(xp, xp, -seps2000, ceps2000);
if (do_save) {
pdp->teval = tjd;/**/
pdp->xflgs = -1;
pdp->iephe = SEFLG_MOSEPH;
}
/* one more position for speed.
* the following dt gives good speed for light-time correction
*/
#if 0
for (i = 0; i <= 2; i++)
dx[i] = xp[i] - pedp->x[i];
dt = LIGHTTIME_AUNIT * sqrt(square_sum(dx));
#endif
dt = PLAN_SPEED_INTV;
swi_moshplan2(tjd - dt, iplm, x2);
swi_polcart(x2, x2);
swi_coortrf2(x2, x2, -seps2000, ceps2000);
for (i = 0; i <= 2; i++)
dx[i] = (xp[i] - x2[i]) / dt;
/* store speed */
for (i = 0; i <= 2; i++) {
xp[i+3] = dx[i];
}
}
if (xpret != NULL)
for (i = 0; i <= 5; i++)
xpret[i] = xp[i];
}
return(OK);
}
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;
}
/* mean lunar apogee ('dark moon', 'lilith')
* J julian day
* pol return array for position
* (polar coordinates of ecliptic of date)
* serr error return string
*/
int swi_mean_apog(double J, double *pol, char *serr)
{
#if 0
int i;
double a, b;
double x[3];
#endif
double node;
char s[AS_MAXCH];
T = (J-J2000)/36525.0;
T2 = T*T;
#ifndef NO_MOSHIER
T3 = T*T2;
T4 = T2*T2;
#endif
/* with elements from swi_moshmoon2(), which are fitted to jpl-ephemeris */
if (J < MOSHNDEPH_START || J > MOSHNDEPH_END) {
if (serr != NULL) {
sprintf(s, "jd %f outside mean apogee range %.2f .. %.2f ",
J, MOSHNDEPH_START, MOSHNDEPH_END);
if (strlen(serr) + strlen(s) < AS_MAXCH)
strcat(serr, s);
}
return(ERR);
}
mean_elements();
pol[0] = swi_mod2PI((LP - MP) * STR + PI);
#if 0
a = pol[0];
/* Chapront, according to Meeus, German, p. 339 */
pol[0] = 83.3532430 + 4069.0137111 * T - 0.0103238 * T2
- T3 / 80053 + T4 / 18999000;
pol[0] = swi_mod2PI(pol[0] * DEGTORAD + PI);
b = pol[0];
printf ("mean apogee\n");
printf ("moshier de404 - chapront %f\"\n", (a-b) * RADTODEG * 3600);
#endif
pol[1] = 0;
pol[2] = MOON_MEAN_DIST * (1 + MOON_MEAN_ECC) / AUNIT; /* apogee */
#if 0
pol[2] = 2 * MOON_MEAN_ECC * MOON_MEAN_DIST / AUNIT; /* 2nd focus */
#endif
/* Lilith or Dark Moon is either the empty focal point of the mean
* lunar ellipse or, for some people, its apogee ("aphelion").
* This is 180 degrees from the perigee.
*
* Since the lunar orbit is not in the ecliptic, the apogee must be
* projected onto the ecliptic.
* Joelle de Gravelaine has in her book "Lilith der schwarze Mond"
* (Astrodata, 1990) an ephemeris which gives noon (12.00) positions
* but does not project them onto the ecliptic.
* This results in a mistake of several arc minutes.
*
* There is also another problem. The other focal point doesn't
* coincide with the geocenter but with the barycenter of the
* earth-moon-system. The difference is about 4700 km. If one
* took this into account, it would result in an oscillation
* of the Black Moon. If defined as the apogee, this oscillation
* would be about +/- 40 arcmin.
* If defined as the second focus, the effect is very large:
* +/- 6 deg!
* We neglect this influence.
*/
/* apogee is now projected onto ecliptic */
node = (LP - NF) * STR;
pol[0] = swi_mod2PI(pol[0] - node);
swi_polcart(pol, pol);
swi_coortrf(pol, pol, -MOON_MEAN_INCL * DEGTORAD);
swi_cartpol(pol, pol);
pol[0] = swi_mod2PI(pol[0] + node);
#if 0
/* speed */
mean_elements(T-PLAN_SPEED_INTV, &LP, &MP, &NF, &M, &D);
pol[3] = swi_mod2PI((LP - MP) * STR + PI);
pol[4] = 0;
pol[5] = MOON_MEAN_DIST * (1 + MOON_MEAN_ECC) / AUNIT; /* apogee */
#if 0
pol[2] = 2 * MOON_MEAN_ECC * MOON_MEAN_DIST / AUNIT; /* 2nd focus */
#endif
node = (LP - NF) * STR;
pol[3] = swi_mod2PI(pol[3] - node);
swi_polcart(pol+3, pol+3);
swi_coortrf(pol+3, pol+3, -MOON_MEAN_INCL * DEGTORAD);
swi_cartpol(pol+3, pol+3);
pol[3] = swi_mod2PI(pol[3] + node);
for (i = 0; i <= 2; i++)
pol[3+i] = pol[i] - pol[3+i];
pol[3] = swi_mod2PI(pol[3]);
#endif
return OK;
}
