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(); }