customorbit.cpp File Reference

#include <cassert>
#include <vector>
#include <fstream>
#include <iomanip>
#include <celmath/mathlib.h>
#include "astro.h"
#include "customorbit.h"
#include "vsop87.h"
#include "jpleph.h"

Include dependency graph for customorbit.cpp:

Go to the source code of this file.

Defines
#define	LPEJ   0.23509484
#define	TWOPI   6.28318530717958647692
Functions
void	auxJSun (double t, double *x1, double *x2, double *x3, double *x4, double *x5, double *x6)
void	ComputeGalileanElements (double t, double &l1, double &l2, double &l3, double &l4, double &p1, double &p2, double &p3, double &p4, double &w1, double &w2, double &w3, double &w4, double &gamma, double &phi, double &psi, double &G, double &Gp)
void	computePlanetCoords (int p, double map, double da, double dhl, double dl, double dm, double dml, double dr, double ds, double &eclLong, double &eclLat, double &distance)
void	computePlanetElements (double t, vector< int > pList)
void	ComputeSaturnianElements (double t, double &t1, double &t2, double &t3, double &t4, double &t5, double &t6, double &t7, double &t8, double &t9, double &t10, double &t11, double &W0, double &W1, double &W2, double &W3, double &W4, double &W5, double &W6, double &W7, double &W8)
static double	cosD (double theta)
static Orbit *	CreateJPLEphOrbit (JPLEphemItem body, double period, double boundingRadius)
static UranianSatelliteOrbit *	CreateUranianSatelliteOrbit (int n)
static void	EclipticToEquatorial (double t, double fEclLat, double fEclLon, double &RA, double &dec)
static Point3d	ellipsePosition (double a, double e, double M)
void	EpochConvert (double jdFrom, double jdTo, double a0, double d0, double &a, double &d)
Orbit *	GetCustomOrbit (const string &name)
double	meanAnomalySun (double t)
static void	Nutation (double t, double &deps, double &dpsi)
static double	Obliquity (double t)
static void	OuterSaturnMoonParams (double a, double e, double i, double Om_, double M, double lam_, double &lam, double &gam, double &r, double &w)
static Point3d	SaturnMoonPosition (double lam, double gam, double Om, double r)
static double	sinD (double theta)
static double	yearToJD (int year)
Variables
static const double	BoundingRadiusSlack = 1.2
double	gElements [8][23]
double	gPlanetElements [8][9]
static JPLEphemeris *	jpleph = NULL
static bool	jplephInitialized = false
static const double	JupAscendingNode = degToRad(22.203)
static const double	JupiterRadius = 71398.0
static const double	SatAscendingNode = 168.8112
static const double	SatTilt = 28.0817
static const double	SaturnRadius = 60330.0
static double	uran_a [5]
static double	uran_L0 [5]
static double	uran_L1 [5]
static double	uran_L_k [5][3]
static double	uran_L_phi [5][3]
static double	uran_L_theta [5][3]
static double	uran_n [5]
static double	uran_z_k [5][5]
static double	uran_z_phi [5][5]
static double	uran_z_theta [5][5]
static double	uran_zeta_k [5][2]
static double	uran_zeta_phi [5][2]
static double	uran_zeta_theta [5][2]

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Define Documentation

#define LPEJ   0.23509484

Definition at line 24 of file customorbit.cpp. Referenced by CallistoOrbit::computePosition(), GanymedeOrbit::computePosition(), EuropaOrbit::computePosition(), and IoOrbit::computePosition().

#define TWOPI   6.28318530717958647692

Definition at line 23 of file customorbit.cpp. Referenced by auxJSun(), computePlanetCoords(), NeptuneOrbit::computePosition(), UranusOrbit::computePosition(), LunarOrbit::computePosition(), EarthOrbit::computePosition(), and EclipticToEquatorial().

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Function Documentation

void auxJSun (  double  t, double *  x1, double *  x2, double *  x3, double *  x4, double *  x5, double *  x6 )

Definition at line 280 of file customorbit.cpp. References pfmod(), and TWOPI. Referenced by NeptuneOrbit::computePosition(), UranusOrbit::computePosition(), SaturnOrbit::computePosition(), and JupiterOrbit::computePosition(). { *x1 = t/5+0.1; *x2 = pfmod(4.14473+5.29691e1*t, TWOPI); *x3 = pfmod(4.641118+2.132991e1*t, TWOPI); *x4 = pfmod(4.250177+7.478172*t, TWOPI); *x5 = 5 * *x3 - 2 * *x2; *x6 = 2 * *x2 - 6 * *x3 + 3 * *x4; }

void ComputeGalileanElements (  double  t, double &  l1, double &  l2, double &  l3, double &  l4, double &  p1, double &  p2, double &  p3, double &  p4, double &  w1, double &  w2, double &  w3, double &  w4, double &  gamma, double &  phi, double &  psi, double &  G, double &  Gp )

Definition at line 348 of file customorbit.cpp. References sin(). Referenced by CallistoOrbit::computePosition(), GanymedeOrbit::computePosition(), EuropaOrbit::computePosition(), and IoOrbit::computePosition(). { // Parameter t is Julian days, epoch 1950.0. l1 = 1.8513962 + 3.551552269981*t; l2 = 3.0670952 + 1.769322724929*t; l3 = 2.1041485 + 0.87820795239*t; l4 = 1.473836 + 0.37648621522*t; p1 = 1.69451 + 2.8167146e-3*t; p2 = 2.702927 + 8.248962e-4*t; p3 = 3.28443 + 1.24396e-4*t; p4 = 5.851859 + 3.21e-5*t; w1 = 5.451267 - 2.3176901e-3*t; w2 = 1.753028 - 5.695121e-4*t; w3 = 2.080331 - 1.25263e-4*t; w4 = 5.630757 - 3.07063e-5*t; gamma = 5.7653e-3*sin(2.85674 + 1.8347e-5*t) + 6.002e-4*sin(0.60189 - 2.82274e-4*t); phi = 3.485014 + 3.033241e-3*t; psi = 5.524285 - 3.63e-8*t; G = 0.527745 + 1.45023893e-3*t + gamma; Gp = 0.5581306 + 5.83982523e-4*t; }

void computePlanetCoords (  int  p, double  map, double  da, double  dhl, double  dl, double  dm, double  dml, double  dr, double  ds, double &  eclLong, double &  eclLat, double &  distance )

Definition at line 319 of file customorbit.cpp. References astro::anomaly(), cos(), degToRad(), distance(), gPlanetElements, KM_PER_AU, pfmod(), PI, radToDeg(), sin(), and TWOPI. Referenced by PlutoOrbit::computePosition(), NeptuneOrbit::computePosition(), UranusOrbit::computePosition(), SaturnOrbit::computePosition(), JupiterOrbit::computePosition(), MarsOrbit::computePosition(), VenusOrbit::computePosition(), and MercuryOrbit::computePosition(). { double s, ma, nu, ea, lp, om, lo, slo, clo, inc, spsi, y; s = gPlanetElements[p][3] + ds; ma = map + dm; astro::anomaly(ma, s, nu, ea); distance = (gPlanetElements[p][6] + da)*(1 - s*s)/(1 + s*cos(nu)); lp = radToDeg(nu) + gPlanetElements[p][2] + radToDeg(dml - dm); lp = degToRad(lp); om = degToRad(gPlanetElements[p][5]); lo = lp - om; slo = sin(lo); clo = cos(lo); inc = degToRad(gPlanetElements[p][4]); distance += dr; spsi = slo*sin(inc); y = slo*cos(inc); eclLat = asin(spsi) + dhl; spsi = sin(eclLat); eclLong = atan(y/clo) + om + degToRad(dl); if (clo < 0) eclLong += PI; eclLong = pfmod(eclLong, TWOPI); distance *= KM_PER_AU; }

void computePlanetElements (  double  t, vector< int >  pList )

Definition at line 291 of file customorbit.cpp. References gElements, gPlanetElements, and pfmod(). Referenced by PlutoOrbit::computePosition(), NeptuneOrbit::computePosition(), UranusOrbit::computePosition(), SaturnOrbit::computePosition(), JupiterOrbit::computePosition(), MarsOrbit::computePosition(), VenusOrbit::computePosition(), and MercuryOrbit::computePosition(). { // Parameter t represents the Julian centuries elapsed since 1900. // In other words, t = (jd - 2415020.0) / 36525.0 double *ep, *pp; double aa; int planet; for(unsigned i = 0; i < pList.size(); i++) { planet = pList[i]; ep = gElements[planet]; pp = gPlanetElements[planet]; aa = ep[1]*t; pp[0] = ep[0] + 360*(aa-(int)aa) + (ep[3]*t + ep[2])*t*t; *pp = pfmod(*pp, 360.0); pp[1] = (ep[1]*9.856263e-3) + (ep[2] + ep[3])/36525; for(unsigned j = 4; j < 20; j += 4) pp[j/4+1] = ((ep[j+3]*t + ep[j+2])*t + ep[j+1])*t + ep[j+0]; pp[6] = ep[20]; pp[7] = ep[21]; pp[8] = ep[22]; } }

void ComputeSaturnianElements (  double  t, double &  t1, double &  t2, double &  t3, double &  t4, double &  t5, double &  t6, double &  t7, double &  t8, double &  t9, double &  t10, double &  t11, double &  W0, double &  W1, double &  W2, double &  W3, double &  W4, double &  W5, double &  W6, double &  W7, double &  W8 )

Definition at line 1902 of file customorbit.cpp. Referenced by IapetusOrbit::computePosition(), HyperionOrbit::computePosition(), TitanOrbit::computePosition(), RheaOrbit::computePosition(), DioneOrbit::computePosition(), TethysOrbit::computePosition(), EnceladusOrbit::computePosition(), and MimasOrbit::computePosition(). { t1 = t - 2411093.0; t2 = t1 / 365.25; t3 = (t - 2433282.423) / 365.25 + 1950.0; t4 = t - 2411368.0; t5 = t4 / 365.25; t6 = t - 2415020.0; t7 = t6 / 36525; t8 = t6 / 365.25; t9 = (t - 2442000.5) / 365.25; t10 = t - 2409786.0; t11 = t10 / 36525; W0 = 5.095 * (t3 - 1866.39); W1 = 74.4 + 32.39 * t2; W2 = 134.3 + 92.62 * t2; W3 = 42.0 - 0.5118 * t5; W4 = 276.59 + 0.5118 * t5; W5 = 267.2635 + 1222.1136 * t7; W6 = 175.4762 + 1221.5515 * t7; W7 = 2.4891 + 0.002435 * t7; W8 = 113.35 - 0.2597 * t7; }

static double cosD (  double  theta  )  [static]

Definition at line 133 of file customorbit.cpp. References cos(), and degToRad(). Referenced by IapetusOrbit::computePosition(), HyperionOrbit::computePosition(), TitanOrbit::computePosition(), RheaOrbit::computePosition(), DioneOrbit::computePosition(), EnceladusOrbit::computePosition(), MimasOrbit::computePosition(), and OuterSaturnMoonParams(). { return cos(degToRad(theta)); }

static Orbit* CreateJPLEphOrbit (  JPLEphemItem  body, double  period, double  boundingRadius )  [static]

Definition at line 2746 of file customorbit.cpp. References JPLEphemeris::getEndDate(), JPLEphemeris::getStartDate(), and jpleph. Referenced by GetCustomOrbit(). { Orbit* o = new JPLEphOrbit(*jpleph, body, period, boundingRadius); return new MixedOrbit(o, jpleph->getStartDate(), jpleph->getEndDate(), astro::SolarMass); }

static UranianSatelliteOrbit* CreateUranianSatelliteOrbit (  int  n  )  [static]

Definition at line 2620 of file customorbit.cpp. References uran_a, uran_L0, uran_L1, uran_L_k, uran_L_phi, uran_L_theta, uran_n, uran_z_k, uran_z_phi, uran_z_theta, uran_zeta_k, uran_zeta_phi, and uran_zeta_theta. Referenced by GetCustomOrbit(). { assert(n >= 1 && n <= 5); n--; return new UranianSatelliteOrbit(uran_a[n], uran_n[n], uran_L0[n], uran_L1[n], 3, 5, 2, uran_L_k[n], uran_L_theta[n], uran_L_phi[n], uran_z_k[n], uran_z_theta[n], uran_z_phi[n], uran_zeta_k[n], uran_zeta_theta[n], uran_zeta_phi[n]); };

static void EclipticToEquatorial (  double  t, double  fEclLat, double  fEclLon, double &  RA, double &  dec )  [static]

Definition at line 205 of file customorbit.cpp. References cos(), Nutation(), Obliquity(), pfmod(), PI, sin(), and TWOPI. Referenced by LunarOrbit::computePosition(). { // Parameter t represents the Julian centuries elapsed since 1900. // In other words, t = (jd - 2415020.0) / 36525.0 double seps, ceps; // sin and cos of mean obliquity double sx, cx, sy, cy, ty; double eps; double deps, dpsi; t = (astro::J2000 - 2415020.0) / 36525.0; t = 0; eps = Obliquity(t); // mean obliquity for date Nutation(t, deps, dpsi); eps += deps; seps = sin(eps); ceps = cos(eps); sy = sin(fEclLat); cy = cos(fEclLat); // always non-negative if (fabs(cy)<1e-20) cy = 1e-20; // insure > 0 ty = sy/cy; cx = cos(fEclLon); sx = sin(fEclLon); dec = asin((sy*ceps)+(cy*seps*sx)); RA = atan(((sx*ceps)-(ty*seps))/cx); if (cx<0) RA += PI; // account for atan quad ambiguity RA = pfmod(RA, TWOPI); }

static Point3d ellipsePosition (  double  a, double  e, double  M )  [static]

Definition at line 1277 of file customorbit.cpp. References cos(), sin(), sqrt(), and square(). Referenced by DeimosOrbit::computePosition(), and PhobosOrbit::computePosition(). { // Solve Kepler's equation--for a low eccentricity orbit, just a few // iterations is enough. double E = M; for (int k = 0; k < 3; k++) E = M + e * sin(E); return Point3d(a * (cos(E) - e), 0.0, a * sqrt(1 - square(e)) * -sin(E)); }

void EpochConvert (  double  jdFrom, double  jdTo, double  a0, double  d0, double &  a, double &  d )

Definition at line 241 of file customorbit.cpp. References B, cos(), degToRad(), and sin(). Referenced by LunarOrbit::computePosition(). { double T = (jdFrom - astro::J2000) / 36525.0; double t = (jdTo - jdFrom) / 36525.0; double zeta = (2306.2181 + 1.39656 * T - 0.000139 * T * T) * t + (0.30188 - 0.000344 * T) * t * t + 0.017998 * t * t * t; double z = (2306.2181 + 1.39656 * T - 0.000139 * T * T) * t + (1.09468 + 0.000066 * T) * t * t + 0.018203 * t * t * t; double theta = (2004.3109 - 0.85330 * T - 0.000217 * T * T) * t - (0.42665 + 0.000217 * T) * t * t - 0.041833 * t * t * t; zeta = degToRad(zeta / 3600.0); z = degToRad(z / 3600.0); theta = degToRad(theta / 3600.0); double A = cos(d0) * sin(a0 + zeta); double B = cos(theta) * cos(d0) * cos(a0 + zeta) - sin(theta) * sin(d0); double C = sin(theta) * cos(d0) * cos(a0 + zeta) + cos(theta) * sin(d0); a = atan2(A, B) + z; d = asin(C); }

Orbit* GetCustomOrbit (  const string &  name  )

Definition at line 2764 of file customorbit.cpp. References CreateJPLEphOrbit(), CreateUranianSatelliteOrbit(), CreateVSOP87Orbit(), JPLEphemeris::getDENumber(), JPLEphemeris::getEndDate(), JPLEphemeris::getStartDate(), jpleph, JPLEph_EarthMoonBary, JPLEph_Jupiter, JPLEph_Mars, JPLEph_Mercury, JPLEph_Moon, JPLEph_Neptune, JPLEph_Pluto, JPLEph_Saturn, JPLEph_Uranus, JPLEph_Venus, jplephInitialized, JPLEphemeris::load(), and yearToJD(). Referenced by createCustomOrbit(), and CreateOrbit(). { // Attempt to load JPL ephemeris data if we haven't tried already if (!jplephInitialized) { jplephInitialized = true; ifstream in("data/jpleph.dat", ios::in | ios::binary); if (in.good()) jpleph = JPLEphemeris::load(in); if (jpleph != NULL) { clog << "Loaded DE" << jpleph->getDENumber() << " ephemeris. Valid from JD" << setprecision(8) << jpleph->getStartDate() << " to JD" << jpleph->getEndDate() << '\n'; } } if (name == "mercury") return new MixedOrbit(new MercuryOrbit(), yearToJD(-4000), yearToJD(4000), astro::SolarMass); if (name == "venus") return new MixedOrbit(new VenusOrbit(), yearToJD(-4000), yearToJD(4000), astro::SolarMass); if (name == "earth") return new MixedOrbit(new EarthOrbit(), yearToJD(-4000), yearToJD(4000), astro::SolarMass); if (name == "moon") return new MixedOrbit(new LunarOrbit(), yearToJD(-2000), yearToJD(4000), astro::EarthMass + astro::LunarMass); if (name == "mars") return new MixedOrbit(new MarsOrbit(), yearToJD(-4000), yearToJD(4000), astro::SolarMass); if (name == "jupiter") return new MixedOrbit(new JupiterOrbit(), yearToJD(-4000), yearToJD(4000), astro::SolarMass); if (name == "saturn") return new MixedOrbit(new SaturnOrbit(), yearToJD(-4000), yearToJD(4000), astro::SolarMass); if (name == "uranus") return new MixedOrbit(new UranusOrbit(), yearToJD(-4000), yearToJD(4000), astro::SolarMass); if (name == "neptune") return new MixedOrbit(new NeptuneOrbit(), yearToJD(-4000), yearToJD(4000), astro::SolarMass); if (name == "pluto") return new MixedOrbit(new PlutoOrbit(), yearToJD(-4000), yearToJD(4000), astro::SolarMass); if (name == "mercury-jpl") return CreateJPLEphOrbit(JPLEph_Mercury, 0.2408 * 365.25, 6.0e7); if (name == "venus-jpl") return CreateJPLEphOrbit(JPLEph_Venus, 0.6152 * 365.25, 1.0e8); if (name == "earth-jpl") return CreateJPLEphOrbit(JPLEph_EarthMoonBary, 365.25, 1.6e8); if (name == "mars-jpl") return CreateJPLEphOrbit(JPLEph_Mars, 1.8809 * 365.25, 2.4e8); if (name == "jupiter-jpl") return CreateJPLEphOrbit(JPLEph_Jupiter, 11.86 * 365.25, 8.0e8); if (name == "saturn-jpl") return CreateJPLEphOrbit(JPLEph_Saturn, 29.4577 * 365.25, 1.5e9); if (name == "uranus-jpl") return CreateJPLEphOrbit(JPLEph_Uranus, 84.0139 * 365.25, 3.0e9); if (name == "neptune-jpl") return CreateJPLEphOrbit(JPLEph_Neptune, 164.793 * 365.25, 4.7e9); if (name == "pluto-jpl") return CreateJPLEphOrbit(JPLEph_Pluto, 248.54 * 365.25, 6.0e9); if (name == "moon-jpl") return CreateJPLEphOrbit(JPLEph_Moon, 27.321661, 5.0e5); if (name == "phobos") return new PhobosOrbit(); if (name == "deimos") return new DeimosOrbit(); if (name == "io") return new IoOrbit(); if (name == "europa") return new EuropaOrbit(); if (name == "ganymede") return new GanymedeOrbit(); if (name == "callisto") return new CallistoOrbit(); if (name == "mimas") return new MimasOrbit(); if (name == "enceladus") return new EnceladusOrbit(); if (name == "tethys") return new TethysOrbit(); if (name == "dione") return new DioneOrbit(); if (name == "rhea") return new RheaOrbit(); if (name == "titan") return new TitanOrbit(); if (name == "hyperion") return new HyperionOrbit(); if (name == "iapetus") return new IapetusOrbit(); if (name == "phoebe") return new PhoebeOrbit(); if (name == "miranda") return CreateUranianSatelliteOrbit(1); if (name == "ariel") return CreateUranianSatelliteOrbit(2); if (name == "umbriel") return CreateUranianSatelliteOrbit(3); if (name == "titania") return CreateUranianSatelliteOrbit(4); if (name == "oberon") return CreateUranianSatelliteOrbit(5); if (name == "triton") return new TritonOrbit(); else return CreateVSOP87Orbit(name); }

double meanAnomalySun (  double  t  )

Definition at line 269 of file customorbit.cpp. References degToRad(). Referenced by MarsOrbit::computePosition(), EarthOrbit::computePosition(), and VenusOrbit::computePosition(). { double t2, a, b; t2 = t*t; a = 9.999736042e1*t; b = 360*(a - (int)a); return degToRad(3.5847583e2 - (1.5e-4 + 3.3e-6*t)*t2 + b); }

static void Nutation (  double  t, double &  deps, double &  dpsi )  [static]

Definition at line 147 of file customorbit.cpp. References cos(), degToRad(), and sin(). Referenced by EclipticToEquatorial(). { // Parameter t represents the Julian centuries elapsed since 1900. // In other words, t = (jd - 2415020.0) / 36525.0 double ls, ld; // sun's mean longitude, moon's mean longitude double ms, md; // sun's mean anomaly, moon's mean anomaly double nm; // longitude of moon's ascending node double t2; double tls, tnm, tld; // twice above double a, b; t2 = t*t; a = 100.0021358*t; b = 360.*(a-(int)a); ls = 279.697+.000303*t2+b; a = 1336.855231*t; b = 360.*(a-(int)a); ld = 270.434-.001133*t2+b; a = 99.99736056000026*t; b = 360.*(a-(int)a); ms = 358.476-.00015*t2+b; a = 13255523.59*t; b = 360.*(a-(int)a); md = 296.105+.009192*t2+b; a = 5.372616667*t; b = 360.*(a-(int)a); nm = 259.183+.002078*t2-b; //convert to radian forms for use with trig functions. tls = 2*degToRad(ls); nm = degToRad(nm); tnm = 2*degToRad(nm); ms = degToRad(ms); tld = 2*degToRad(ld); md = degToRad(md); // find delta psi and eps, in arcseconds. dpsi = (-17.2327-.01737*t)*sin(nm)+(-1.2729-.00013*t)*sin(tls) +.2088*sin(tnm)-.2037*sin(tld)+(.1261-.00031*t)*sin(ms) +.0675*sin(md)-(.0497-.00012*t)*sin(tls+ms) -.0342*sin(tld-nm)-.0261*sin(tld+md)+.0214*sin(tls-ms) -.0149*sin(tls-tld+md)+.0124*sin(tls-nm)+.0114*sin(tld-md); deps = (9.21+.00091*t)*cos(nm)+(.5522-.00029*t)*cos(tls) -.0904*cos(tnm)+.0884*cos(tld)+.0216*cos(tls+ms) +.0183*cos(tld-nm)+.0113*cos(tld+md)-.0093*cos(tls-ms) -.0066*cos(tls-nm); // convert to radians. dpsi = degToRad(dpsi/3600); deps = degToRad(deps/3600); }

static double Obliquity (  double  t  )  [static]

Definition at line 139 of file customorbit.cpp. References degToRad(). Referenced by EclipticToEquatorial(). { // Parameter t represents the Julian centuries elapsed since 1900. // In other words, t = (jd - 2415020.0) / 36525.0 return degToRad(2.345229444E1 - ((((-1.81E-3*t)+5.9E-3)*t+4.6845E1)*t)/3600.0); }

static void OuterSaturnMoonParams (  double  a, double  e, double  i, double  Om_, double  M, double  lam_, double &  lam, double &  gam, double &  r, double &  w )  [static]

Definition at line 1957 of file customorbit.cpp. References cosD(), radToDeg(), SatAscendingNode, SatTilt, sinD(), sqrt(), and square(). Referenced by PhoebeOrbit::computePosition(), IapetusOrbit::computePosition(), HyperionOrbit::computePosition(), TitanOrbit::computePosition(), and RheaOrbit::computePosition(). { double s1 = sinD(SatTilt); double c1 = cosD(SatTilt); double e_2 = e * e; double e_3 = e_2 * e; double e_4 = e_3 * e; double e_5 = e_4 * e; double C = (2 * e - 0.25 * e_3 + 0.0520833333 * e_5) * sinD(M) + (1.25 * e_2 - 0.458333333 * e_4) * sinD(2 * M) + (1.083333333 * e_3 - 0.671875 * e_5) * sinD(3 * M) + 1.072917 * e_4 * sinD(4 * M) + 1.142708 * e_5 * sinD(5 * M); double g = Om_ - SatAscendingNode; double a1 = sinD(i) * sinD(g); double a2 = c1 * sinD(i) * cosD(g) - s1 * cosD(i); double u = radToDeg(atan2(a1, a2)); double h = c1 * sinD(i) - s1 * cosD(i) * cosD(g); double psi = radToDeg(atan2(s1 * sinD(g), h)); C = radToDeg(C); lam = lam_ + C + u - g - psi; gam = radToDeg(asin(sqrt(square(a1) + square(a2)))); r = a * (1 - e * e) / (1 + e * cosD(M + C)); w = SatAscendingNode + u; }

static Point3d SaturnMoonPosition (  double  lam, double  gam, double  Om, double  r )  [static]

Definition at line 1935 of file customorbit.cpp. References cos(), degToRad(), SatAscendingNode, SaturnRadius, and sin(). Referenced by PhoebeOrbit::computePosition(), IapetusOrbit::computePosition(), HyperionOrbit::computePosition(), TitanOrbit::computePosition(), RheaOrbit::computePosition(), DioneOrbit::computePosition(), TethysOrbit::computePosition(), EnceladusOrbit::computePosition(), and MimasOrbit::computePosition(). { double u = lam - Om; double w = Om - SatAscendingNode; u = degToRad(u); w = degToRad(w); gam = -degToRad(gam); r = r * SaturnRadius; // Corrections for Celestia's coordinate system u = -u; w = -w; double x = r * (cos(u) * cos(w) - sin(u) * sin(w) * cos(gam)); double y = r * sin(u) * sin(gam); double z = r * (sin(u) * cos(w) * cos(gam) + cos(u) * sin(w)); return Point3d(x, y, z); }

static double sinD (  double  theta  )  [static]

Definition at line 128 of file customorbit.cpp. References degToRad(), and sin(). Referenced by IapetusOrbit::computePosition(), HyperionOrbit::computePosition(), TitanOrbit::computePosition(), RheaOrbit::computePosition(), DioneOrbit::computePosition(), TethysOrbit::computePosition(), EnceladusOrbit::computePosition(), MimasOrbit::computePosition(), and OuterSaturnMoonParams(). { return sin(degToRad(theta)); }

static double yearToJD (  int  year  )  [static]

Definition at line 2758 of file customorbit.cpp. Referenced by CreateVSOP87Orbit(), and GetCustomOrbit(). { return (double) astro::Date(year, 1, 1); }

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Variable Documentation

const double BoundingRadiusSlack = 1.2 [static]

Definition at line 36 of file customorbit.cpp. Referenced by TritonOrbit::getBoundingRadius(), UranianSatelliteOrbit::getBoundingRadius(), PhoebeOrbit::getBoundingRadius(), IapetusOrbit::getBoundingRadius(), HyperionOrbit::getBoundingRadius(), TitanOrbit::getBoundingRadius(), RheaOrbit::getBoundingRadius(), DioneOrbit::getBoundingRadius(), TethysOrbit::getBoundingRadius(), EnceladusOrbit::getBoundingRadius(), MimasOrbit::getBoundingRadius(), CallistoOrbit::getBoundingRadius(), GanymedeOrbit::getBoundingRadius(), EuropaOrbit::getBoundingRadius(), IoOrbit::getBoundingRadius(), DeimosOrbit::getBoundingRadius(), PhobosOrbit::getBoundingRadius(), PlutoOrbit::getBoundingRadius(), NeptuneOrbit::getBoundingRadius(), UranusOrbit::getBoundingRadius(), SaturnOrbit::getBoundingRadius(), JupiterOrbit::getBoundingRadius(), MarsOrbit::getBoundingRadius(), LunarOrbit::getBoundingRadius(), EarthOrbit::getBoundingRadius(), VenusOrbit::getBoundingRadius(), and MercuryOrbit::getBoundingRadius().

double gElements[8][23]

Definition at line 43 of file customorbit.cpp. Referenced by computePlanetElements().

double gPlanetElements[8][9]

Definition at line 42 of file customorbit.cpp. Referenced by computePlanetCoords(), computePlanetElements(), PlutoOrbit::computePosition(), NeptuneOrbit::computePosition(), UranusOrbit::computePosition(), SaturnOrbit::computePosition(), JupiterOrbit::computePosition(), MarsOrbit::computePosition(), VenusOrbit::computePosition(), and MercuryOrbit::computePosition().

JPLEphemeris* jpleph = NULL [static]

Definition at line 39 of file customorbit.cpp. Referenced by CreateJPLEphOrbit(), and GetCustomOrbit().

bool jplephInitialized = false [static]

Definition at line 38 of file customorbit.cpp. Referenced by GetCustomOrbit().

const double JupAscendingNode = degToRad(22.203) [static]

Definition at line 1494 of file customorbit.cpp. Referenced by CallistoOrbit::computePosition(), GanymedeOrbit::computePosition(), EuropaOrbit::computePosition(), and IoOrbit::computePosition().

const double JupiterRadius = 71398.0 [static]

Definition at line 28 of file customorbit.cpp. Referenced by CallistoOrbit::computePosition(), GanymedeOrbit::computePosition(), EuropaOrbit::computePosition(), and IoOrbit::computePosition().

const double SatAscendingNode = 168.8112 [static]

Definition at line 1893 of file customorbit.cpp. Referenced by OuterSaturnMoonParams(), and SaturnMoonPosition().

const double SatTilt = 28.0817 [static]

Definition at line 1894 of file customorbit.cpp. Referenced by OuterSaturnMoonParams().

const double SaturnRadius = 60330.0 [static]

Definition at line 29 of file customorbit.cpp. Referenced by PhoebeOrbit::computePosition(), and SaturnMoonPosition().

double uran_a[5] [static]

Initial value: { 129800, 191200, 266000, 435800, 583600 } Definition at line 2550 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_L0[5] [static]

Initial value: { -0.23805158, 3.09804641, 2.28540169, 0.85635879, -0.91559180 } Definition at line 2552 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_L1[5] [static]

Initial value: { 4.44519055, 2.49295252, 1.51614811, 0.72171851, 0.46669212 } Definition at line 2554 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_L_k[5][3] [static]

Initial value: { { 0.02547217, -0.00308831, -3.181e-4 }, { -1.86050e-3, 2.1999e-4, 0 }, { 6.6057e-4, 0, 0 }, { 0, 0, 0 }, { 0, 0, 0 } } Definition at line 2556 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_L_phi[5][3] [static]

Initial value: { { 1.32, 2.64, 3.97 }, { 1.32, 2.64, 0 }, { 1.32, 0, 0 }, { 0, 0, 0 }, { 0, 0, 0 }, } Definition at line 2570 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_L_theta[5][3] [static]

Initial value: { { -2.18167e-4, -4.36336e-4, -6.54502e-4 }, { -2.18167e-4, -4.36336e-4, 0 }, { -2.18167e-4, 0, 0 }, { 0, 0, 0 }, { 0, 0, 0 } } Definition at line 2563 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_n[5] [static]

Initial value: { 4.44352267, 2.49254257, 1.51595490, 0.72166316, 0.46658054 } Definition at line 2548 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_z_k[5][5] [static]

Initial value: { { 1.31238e-3, -1.2331e-4, -1.9410e-4, 0, 0 }, { 1.18763e-3, 8.6159e-4, 0, 0, 0 }, { -2.2795e-4, 3.90496e-3, 3.0917e-4, 2.2192e-4, 5.4923e-4 }, { 9.3281e-4, 1.12089e-3, 7.9343e-4, 0, 0 }, { -7.5868e-4, 1.39734e-3, -9.8726e-4, 0, 0 } } Definition at line 2577 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_z_phi[5][5] [static]

Initial value: { { 0.61, 0.15, 6.04, 0, 0 }, { 2.41, 2.07, 0, 0, 0 }, { 2.41, 2.07, 0.74, 0.43, 5.71 }, { 0.74, 0.43, 1.82, 0, 0 }, { 0.74, 0.43, 1.82, 0, 0 } } Definition at line 2591 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_z_theta[5][5] [static]

Initial value: { { 1.5273e-4, 0.08606, 0.709, 0, 0 }, { 4.727824e-5, 2.179316e-5, 0, 0, 0 }, { 4.727824e-5, 2.179132e-5, 1.580524e-5, 2.9363068e-6, -0.01157 }, { 1.580524e-5, 2.9363068e-6, -6.9008e-3, 0, 0 }, { 1.580524e-5, 2.9363068e-6, -6.9008e-3, 0, 0 } } Definition at line 2584 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_zeta_k[5][2] [static]

Initial value: { { 0.03787171, 0 }, { 3.5825e-4, 2.9008e-4 }, { 1.11336e-3, 3.5014e-4 }, { 6.8572e-4, 3.7832e-4 }, { -5.9633e-4, 4.5169e-4 } } Definition at line 2598 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_zeta_phi[5][2] [static]

Initial value: { { 5.70, 0 }, { 0.40, 0.59 }, { 0.59, 1.75 }, { 1.75, 4.21 }, { 1.75, 4.21 }, } Definition at line 2612 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

double uran_zeta_theta[5][2] [static]

Initial value: { { -1.54449e-4, 0 }, { -4.782474e-5, -2.156628e-5 }, { -2.156628e-5, -1.401373e-5 }, { -1.401373e-5, -1.9713918e-6 }, { -1.401373e-5, -1.9713918e-6 } } Definition at line 2605 of file customorbit.cpp. Referenced by CreateUranianSatelliteOrbit().

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