public void Reset()
{
fidat = Enumerable.Range(0, SEI_NEPHFILES).Select(i => new file_data()).ToArray();
savedat = Enumerable.Range(0, SwissEph.SE_NPLANETS + 1).Select(i => new save_positions()).ToArray();
pldat = Enumerable.Range(0, SEI_NPLANETS).Select(i => new plan_data()).ToArray();
nddat = Enumerable.Range(0, SEI_NNODE_ETC).Select(i => new plan_data()).ToArray();
topd = new topo_data();
dpsi = new double[36525];
deps = new double[36525];
nut = new nut();
nut2000 = new nut();
nutv = new nut();
oec = new epsilon();
oec2000 = new epsilon();
}
public void Reset(bool full)
{
if (full)
{
fidat = Enumerable.Range(0, SEI_NEPHFILES).Select(i => new file_data()).ToArray();
savedat = Enumerable.Range(0, SwissEph.SE_NPLANETS + 1).Select(i => new save_positions()).ToArray();
pldat = Enumerable.Range(0, SEI_NPLANETS).Select(i => new plan_data()).ToArray();
nddat = Enumerable.Range(0, SEI_NNODE_ETC).Select(i => new plan_data()).ToArray();
topd = new topo_data();
//dpsi = new double[36525];
//deps = new double[36525];
astro_models = new Int32[Sweph.SEI_NMODELS];
}
oec = new epsilon();
oec2000 = new epsilon();
nut = new nut();
nut2000 = new nut();
nutv = new nut();
}
/* transforms the position of the moon in a way we can use it
* for calculation of osculating node and apogee:
* precession and nutation (attention to speed vector!)
* according to flags
* iflag flags
* tjd time for which the element is computed
* i.e. date of ecliptic
* xx array equatorial cartesian position and speed
* serr error string
*/
public int swi_plan_for_osc_elem(Int32 iflag, double tjd, CPointer<double> xx)
{
int i;
double[] x = new double[6];
nut nuttmp = new nut();
nut nutp = nuttmp; /* dummy assign, to silence gcc warning */
epsilon oe = swed.oec;
epsilon oectmp = new epsilon();
sid_data sip = new sid_data(); ;
/* ICRS to J2000 */
if (0 == (iflag & SwissEph.SEFLG_ICRS) && get_denum(SEI_SUN, iflag) >= 403) {
SE.SwephLib.swi_bias(xx, tjd, iflag, false);
}/**/
/************************************************
* precession, equator 2000 -> equator of date *
* attention: speed vector has to be rotated, *
* but daily precession 0.137" may not be added!*/
/*
#if SID_TNODE_FROM_ECL_T0
sid_data sip = &swed.sidd;
/* For sidereal calculation we need node refered*
* to ecliptic of t0 of ayanamsa *
************************************************ /
if (iflag & SEFLG_SIDEREAL) {
tjd = sip.t0;
swi_precess(xx, tjd, iflag, J2000_TO_J);
swi_precess(xx+3, tjd, iflag, J2000_TO_J);
calc_epsilon(tjd, iflag, &oectmp);
oe = &oectmp;
} else if (!(iflag & SEFLG_J2000)) {
#endif
swi_precess(xx, tjd, iflag, J2000_TO_J);
swi_precess(xx + 3, tjd, iflag, J2000_TO_J);
/* epsilon * /
if (tjd == swed.oec.teps)
oe = swed.oec;
else if (tjd == J2000)
oe = swed.oec2000;
else {
calc_epsilon(tjd, iflag, oectmp);
oe = oectmp;
}
#if SID_TNODE_FROM_ECL_T0
} else /* if SEFLG_J2000 * /
oe = &swed.oec2000;
#endif
*/
if (SID_TNODE_FROM_ECL_T0) {
sip = swed.sidd;
/* For sidereal calculation we need node refered*
* to ecliptic of t0 of ayanamsa *
************************************************/
if ((iflag & SwissEph.SEFLG_SIDEREAL) != 0) {
tjd = sip.t0;
SE.SwephLib.swi_precess(xx, tjd, iflag, J2000_TO_J);
SE.SwephLib.swi_precess(xx + 3, tjd, iflag, J2000_TO_J);
calc_epsilon(tjd, iflag, oectmp);
oe = oectmp;
} else if (0 == (iflag & SwissEph.SEFLG_J2000)) {
SE.SwephLib.swi_precess(xx, tjd, iflag, J2000_TO_J);
SE.SwephLib.swi_precess(xx + 3, tjd, iflag, J2000_TO_J);
/* epsilon */
if (tjd == swed.oec.teps)
oe = swed.oec;
else if (tjd == J2000)
oe = swed.oec2000;
else {
calc_epsilon(tjd, iflag, oectmp);
oe = oectmp;
}
} else /* if SEFLG_J2000 */
oe = swed.oec2000;
} else {
SE.SwephLib.swi_precess(xx, tjd, iflag, J2000_TO_J);
SE.SwephLib.swi_precess(xx + 3, tjd, iflag, J2000_TO_J);
/* epsilon */
if (tjd == swed.oec.teps)
oe = swed.oec;
else if (tjd == J2000)
oe = swed.oec2000;
else {
calc_epsilon(tjd, iflag, oectmp);
oe = oectmp;
}
}
/************************************************
* nutation *
* again: speed vector must be rotated, but not *
* added 'speed' of nutation *
************************************************/
if (0 == (iflag & SwissEph.SEFLG_NONUT)) {
if (tjd == swed.nut.tnut) {
nutp = swed.nut;
} else if (tjd == J2000) {
nutp = swed.nut2000;
} else if (tjd == swed.nutv.tnut) {
nutp = swed.nutv;
} else {
nutp = nuttmp;
SE.SwephLib.swi_nutation(tjd, iflag, nutp.nutlo);
nutp.tnut = tjd;
nutp.snut = Math.Sin(nutp.nutlo[1]);
nutp.cnut = Math.Cos(nutp.nutlo[1]);
nut_matrix(nutp, oe);
}
for (i = 0; i <= 2; i++) {
x[i] = xx[0] * nutp.matrix[0, i] +
xx[1] * nutp.matrix[1, i] +
xx[2] * nutp.matrix[2, i];
}
/* speed:
* rotation only */
for (i = 0; i <= 2; i++) {
x[i + 3] = xx[3] * nutp.matrix[0, i] +
xx[4] * nutp.matrix[1, i] +
xx[5] * nutp.matrix[2, i];
}
for (i = 0; i <= 5; i++)
xx[i] = x[i];
}
/************************************************
* transformation to ecliptic *
************************************************/
SE.SwephLib.swi_coortrf2(xx, xx, oe.seps, oe.ceps);
SE.SwephLib.swi_coortrf2(xx + 3, xx + 3, oe.seps, oe.ceps);
if (SID_TNODE_FROM_ECL_T0 && (iflag & SwissEph.SEFLG_SIDEREAL) != 0) {
/* subtract ayan_t0 */
SE.SwephLib.swi_cartpol_sp(xx, xx);
xx[0] -= sip.ayan_t0;
SE.SwephLib.swi_polcart_sp(xx, xx);
} else
if (0 == (iflag & SwissEph.SEFLG_NONUT)) {
SE.SwephLib.swi_coortrf2(xx, xx, nutp.snut, nutp.cnut);
SE.SwephLib.swi_coortrf2(xx + 3, xx + 3, nutp.snut, nutp.cnut);
}
return (OK);
}
public void Reset(bool full)
{
if (full)
{
fidat = Enumerable.Range(0, SEI_NEPHFILES).Select(i => new file_data()).ToArray();
savedat = Enumerable.Range(0, SwissEph.SE_NPLANETS + 1).Select(i => new save_positions()).ToArray();
pldat = Enumerable.Range(0, SEI_NPLANETS).Select(i => new plan_data()).ToArray();
nddat = Enumerable.Range(0, SEI_NNODE_ETC).Select(i => new plan_data()).ToArray();
topd = new topo_data();
//dpsi = new double[36525];
//deps = new double[36525];
astro_models = new Int32[Sweph.SEI_NMODELS];
}
oec = new epsilon();
oec2000 = new epsilon();
nut = new nut();
nut2000 = new nut();
nutv = new nut();
}