void slaSubet ( double rc, double dc, double eq, double *rm, double *dm )
/*
** - - - - - - - - -
** s l a S u b e t
** - - - - - - - - -
**
** Remove the e-terms (elliptic component of annual aberration)
** from a pre IAU 1976 catalogue RA,Dec to give a mean place.
**
** (double precision)
**
** Given:
** rc,dc double RA,Dec (radians) with e-terms included
** eq double Besselian epoch of mean equator and equinox
**
** Returned:
** *rm,*dm double RA,Dec (radians) without e-terms
**
** Called:
** slaEtrms, slaDcs2c, sla,dvdv, slaDcc2s, slaDranrm
**
** Explanation:
** Most star positions from pre-1984 optical catalogues (or
** derived from astrometry using such stars) embody the
** e-terms. This routine converts such a position to a
** formal mean place (allowing, for example, comparison with a
** pulsar timing position).
**
** Reference:
** Explanatory Supplement to the Astronomical Ephemeris,
** section 2D, page 48.
**
** Last revision: 31 October 1993
**
** Copyright P.T.Wallace. All rights reserved.
*/
{
double a[3], v[3], f;
int i;
/* E-terms */
slaEtrms ( eq, a );
/* Spherical to Cartesian */
slaDcs2c ( rc, dc, v );
/* Include the e-terms */
f = 1.0 + slaDvdv (v, a);
for ( i = 0; i < 3; i++ ) {
v[i] = f * v[i] - a[i];
}
/* Cartesian to spherical */
slaDcc2s ( v, rm, dm );
/* Bring RA into conventional range */
*rm = slaDranrm ( *rm );
}
void slaEqecl ( double dr, double dd, double date,
double *dl, double *db )
/*
** - - - - - - - - -
** s l a E q e c l
** - - - - - - - - -
**
** Transformation from J2000.0 equatorial coordinates to
** ecliptic coordinates.
**
** (double precision)
**
** Given:
** dr,dd double J2000.0 mean RA,Dec (radians)
** date double TDB (loosely ET) as Modified Julian Date
** (JD-2400000.5)
** Returned:
** *dl,*db double ecliptic longitude and latitude
** (mean of date, IAU 1980 theory, radians)
**
**
** Called:
** slaDcs2c, slaPrec, slaEpj, slaDmxv, slaEcmat, slaDcc2s,
** slaDranrm, slaDrange
**
**
** Last revision: 31 October 1993
**
** Copyright P.T.Wallace. All rights reserved.
*/
{
double rmat[3][3], v1[3], v2[3];
/* Spherical to Cartesian */
slaDcs2c ( dr, dd, v1 );
/* Mean J2000 to mean of date */
slaPrec ( 2000.0, slaEpj ( date ), rmat );
slaDmxv ( rmat, v1, v2 );
/* Equatorial to ecliptic */
slaEcmat ( date, rmat );
slaDmxv ( rmat, v2, v1 );
/* Cartesian to spherical */
slaDcc2s ( v1, dl, db );
/* Express in conventional ranges */
*dl = slaDranrm ( *dl );
*db = slaDrange ( *db );
}
void slaAmpqk ( double ra, double da, double amprms[21],
double *rm, double *dm )
/*
** - - - - - - - - -
** s l a A m p q k
** - - - - - - - - -
**
** Convert star RA,Dec from geocentric apparent to mean place.
**
** The mean coordinate system is the post IAU 1976 system,
** loosely called FK5.
**
** Use of this routine is appropriate when efficiency is important
** and where many star positions are all to be transformed for
** one epoch and equinox. The star-independent parameters can be
** obtained by calling the slaMappa routine.
**
** Given:
** ra double apparent RA (radians)
** da double apparent Dec (radians)
**
** amprms double[21] star-independent mean-to-apparent parameters:
**
** (0) time interval for proper motion (Julian years)
** (1-3) barycentric position of the Earth (AU)
** (4-6) heliocentric direction of the Earth (unit vector)
** (7) (grav rad Sun)*2/(Sun-Earth distance)
** (8-10) abv: barycentric Earth velocity in units of c
** (11) sqrt(1-v*v) where v=modulus(abv)
** (12-20) precession/nutation (3,3) matrix
**
** Returned:
** *rm double mean RA (radians)
** *dm double mean Dec (radians)
**
** References:
** 1984 Astronomical Almanac, pp B39-B41.
** (also Lederle & Schwan, Astron. Astrophys. 134, 1-6, 1984)
**
** Note:
**
** Iterative techniques are used for the aberration and
** light deflection corrections so that the routines
** slaAmp (or slaAmpqk) and slaMap (or slaMapqk) are
** accurate inverses; even at the edge of the Sun's disc
** the discrepancy is only about 1 nanoarcsecond.
**
** Called: slaDcs2c, slaDimxv, slaDvdv, slaDvn, slaDcc2s,
** slaDranrm
**
** Last revision: 7 May 2000
**
** Copyright P.T.Wallace. All rights reserved.
*/
{
double gr2e; /* (grav rad Sun)*2/(Sun-Earth distance) */
double ab1; /* sqrt(1-v*v) where v=modulus of Earth vel */
double ehn[3]; /* Earth position wrt Sun (unit vector, FK5) */
double abv[3]; /* Earth velocity wrt SSB (c, FK5) */
double p[3], p1[3], p2[3], p3[3]; /* work vectors */
double ab1p1, p1dv, p1dvp1, w, pde, pdep1;
int i, j;
/* Unpack some of the parameters */
gr2e = amprms[7];
ab1 = amprms[11];
for ( i = 0; i < 3; i++ ) {
ehn[i] = amprms[i + 4];
abv[i] = amprms[i + 8];
}
/* Apparent RA,Dec to Cartesian */
slaDcs2c ( ra, da, p3 );
/* Precession and nutation */
slaDimxv ( (double(*)[3]) &rms[12], p3, p2 );
/* Aberration */
ab1p1 = ab1 + 1.0;
for ( i = 0; i < 3; i++ ) {
p1[i] = p2[i];
}
for ( j = 0; j < 2; j++ ) {
p1dv = slaDvdv ( p1, abv );
p1dvp1 = 1.0 + p1dv;
w = 1.0 + p1dv / ab1p1;
for ( i = 0; i < 3; i++ ) {
p1[i] = ( p1dvp1 * p2[i] - w * abv[i] ) / ab1;
}
slaDvn ( p1, p3, &w );
for ( i = 0; i < 3; i++ ) {
p1[i] = p3[i];
}
}
/* Light deflection */
for ( i = 0; i < 3; i++ ) {
p[i] = p1[i];
}
for ( j = 0; j < 5; j++ ) {
pde = slaDvdv ( p, ehn );
pdep1 = 1.0 + pde;
w = pdep1 - gr2e * pde;
for ( i = 0; i < 3; i++ ) {
p[i] = ( pdep1 * p1[i] - gr2e * ehn[i] ) / w;
}
slaDvn ( p, p2, &w );
for ( i = 0; i < 3; i++ ) {
p[i] = p2[i];
}
}
/* Mean RA,Dec */
slaDcc2s ( p, rm, dm );
*rm = slaDranrm ( *rm );
}
void projCircle(double racen, double deccen, double radius, double val) {
int i, j, ip, in, sign, pixval;
float mx[NCIRC], my[NCIRC];
double t, axialvec[3], cenvec[3], angvec[3], rotvec[3], rmat[3][3];
double ra[NCIRC], rap[NCIRC], ran[NCIRC];
double dec[NCIRC], decp[NCIRC], decn[NCIRC];
double x, y;
// make Cartesian representation of the vector pointing to center
slaDcs2c(racen, deccen, cenvec);
// make Cartesian representation of a vector pointing radius away
if(deccen>0.0)
slaDcs2c(racen, deccen-radius, angvec);
else
slaDcs2c(racen, deccen+radius, angvec);
t = 0;
for(i=0; i<NCIRC; i++) {
// length of axial vector is angle of rotation
for(j=0;j<3;j++) axialvec[j] = cenvec[j]*t;
// get rotation matrix
slaDav2m(axialvec, rmat);
// apply rotation to angled vector
slaDmxv(rmat, angvec, rotvec);
// get new ra, dec
slaDcc2s(rotvec, &(ra[i]), &(dec[i]));
// if(ra[i] < 0 && racen > 0.0) ra[i] += 2*M_PI;
// if(ra[i] > 0 && racen < 0.0) ra[i] -= 2*M_PI;
// update rotation angle
t += 2.0*M_PI/(double) (NCIRC-1);
}
pixval = rint((__minind*(__maxval-val) + __maxind*(val-__minval))/
(__maxval-__minval));
// saturate properly
pixval = MIN(__maxind, pixval);
pixval = MAX(__minind, pixval);
cpgsci(pixval);
// determine if the polygon wraps around
sign = 0;
for(i=0; i<NCIRC-1; i++) {
if(dec[i]>deccen && ra[i+1]*ra[i] < 0 && ra[i+1]<ra[i]) sign = 1;
}
// if so, draw two polygons separately
if(sign) {
in = 0;
ip = 0;
for(i=0; i<NCIRC; i++) {
if(ra[i]<0.0) {
ran[in] = ra[i]; decn[in] = dec[i]; in++;
}
else {
ran[in] = -0.99999*M_PI; decn[in] = dec[i]; in++;
}
if(ra[i]>0.0) {
rap[ip] = ra[i]; decp[ip] = dec[i]; ip++;
}
else {
rap[ip] = 0.99999*M_PI; decp[ip] = dec[i]; ip++;
}
}
for(i=0; i<ip; i++) {
// Hammer-Aitoff projection
project(rap[i], decp[i], &x, &y);
mx[i] = x; my[i] = y;
}
cpgpoly(ip,mx,my);
for(i=0; i<in; i++) {
// Hammer-Aitoff projection
project(ran[i], decn[i], &x, &y);
mx[i] = x; my[i] = y;
}
cpgpoly(in,mx,my);
}
// otherwise draw only one
else {
for(i=0; i<NCIRC; i++) {
// Hammer-Aitoff projection
project(ra[i], dec[i], &x, &y);
mx[i] = x; my[i] = y;
}
cpgpoly(NCIRC,mx,my);
}
cpgsci(1);
}
