LunarOrbit Class Reference

Inheritance diagram for LunarOrbit:

Collaboration diagram for LunarOrbit:

List of all members.

Private Member Functions
Point3d	computePosition (double jd) const
double	getBoundingRadius () const
double	getPeriod () const

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Member Function Documentation

Point3d LunarOrbit::computePosition (  double  jd  )  const [inline, private, virtual]

Implements CachingOrbit. Definition at line 580 of file customorbit.cpp. References cos(), degToRad(), distance(), EclipticToEquatorial(), EpochConvert(), pfmod(), PI, sin(), and TWOPI. { double jd19, t, t2; double ld, ms, md, de, f, n, hp; double a, sa, sn, b, sb, c, sc, e, e2, l, g, w1, w2; double m1, m2, m3, m4, m5, m6; double eclLon, eclLat, horzPar, distance; double RA, dec; // Computation requires an abbreviated Julian day: // epoch January 0.5, 1900. jd19 = jd - 2415020.0; t = jd19/36525; t2 = t*t; m1 = jd19/27.32158213; m1 = 360.0*(m1-(int)m1); m2 = jd19/365.2596407; m2 = 360.0*(m2-(int)m2); m3 = jd19/27.55455094; m3 = 360.0*(m3-(int)m3); m4 = jd19/29.53058868; m4 = 360.0*(m4-(int)m4); m5 = jd19/27.21222039; m5 = 360.0*(m5-(int)m5); m6 = jd19/6798.363307; m6 = 360.0*(m6-(int)m6); ld = 270.434164+m1-(.001133-.0000019*t)*t2; ms = 358.475833+m2-(.00015+.0000033*t)*t2; md = 296.104608+m3+(.009192+.0000144*t)*t2; de = 350.737486+m4-(.001436-.0000019*t)*t2; f = 11.250889+m5-(.003211+.0000003*t)*t2; n = 259.183275-m6+(.002078+.000022*t)*t2; a = degToRad(51.2+20.2*t); sa = sin(a); sn = sin(degToRad(n)); b = 346.56+(132.87-.0091731*t)*t; sb = .003964*sin(degToRad(b)); c = degToRad(n+275.05-2.3*t); sc = sin(c); ld = ld+.000233*sa+sb+.001964*sn; ms = ms-.001778*sa; md = md+.000817*sa+sb+.002541*sn; f = f+sb-.024691*sn-.004328*sc; de = de+.002011*sa+sb+.001964*sn; e = 1-(.002495+7.52e-06*t)*t; e2 = e*e; ld = degToRad(ld); ms = degToRad(ms); n = degToRad(n); de = degToRad(de); f = degToRad(f); md = degToRad(md); l = 6.28875*sin(md)+1.27402*sin(2*de-md)+.658309*sin(2*de)+ .213616*sin(2*md)-e*.185596*sin(ms)-.114336*sin(2*f)+ .058793*sin(2*(de-md))+.057212*e*sin(2*de-ms-md)+ .05332*sin(2*de+md)+.045874*e*sin(2*de-ms)+.041024*e*sin(md-ms); l = l-.034718*sin(de)-e*.030465*sin(ms+md)+.015326*sin(2*(de-f))- .012528*sin(2*f+md)-.01098*sin(2*f-md)+.010674*sin(4*de-md)+ .010034*sin(3*md)+.008548*sin(4*de-2*md)-e*.00791*sin(ms-md+2*de)- e*.006783*sin(2*de+ms); l = l+.005162*sin(md-de)+e*.005*sin(ms+de)+.003862*sin(4*de)+ e*.004049*sin(md-ms+2*de)+.003996*sin(2*(md+de))+ .003665*sin(2*de-3*md)+e*.002695*sin(2*md-ms)+ .002602*sin(md-2*(f+de))+e*.002396*sin(2*(de-md)-ms)- .002349*sin(md+de); l = l+e2*.002249*sin(2*(de-ms))-e*.002125*sin(2*md+ms)- e2*.002079*sin(2*ms)+e2*.002059*sin(2*(de-ms)-md)- .001773*sin(md+2*(de-f))-.001595*sin(2*(f+de))+ e*.00122*sin(4*de-ms-md)-.00111*sin(2*(md+f))+.000892*sin(md-3*de); l = l-e*.000811*sin(ms+md+2*de)+e*.000761*sin(4*de-ms-2*md)+ e2*.000704*sin(md-2*(ms+de))+e*.000693*sin(ms-2*(md-de))+ e*.000598*sin(2*(de-f)-ms)+.00055*sin(md+4*de)+.000538*sin(4*md)+ e*.000521*sin(4*de-ms)+.000486*sin(2*md-de); l = l+e2*.000717*sin(md-2*ms); eclLon = ld+degToRad(l); eclLon = pfmod(eclLon, TWOPI); g = 5.12819*sin(f)+.280606*sin(md+f)+.277693*sin(md-f)+ .173238*sin(2*de-f)+.055413*sin(2*de+f-md)+.046272*sin(2*de-f-md)+ .032573*sin(2*de+f)+.017198*sin(2*md+f)+.009267*sin(2*de+md-f)+ .008823*sin(2*md-f)+e*.008247*sin(2*de-ms-f); g = g+.004323*sin(2*(de-md)-f)+.0042*sin(2*de+f+md)+ e*.003372*sin(f-ms-2*de)+e*.002472*sin(2*de+f-ms-md)+ e*.002222*sin(2*de+f-ms)+e*.002072*sin(2*de-f-ms-md)+ e*.001877*sin(f-ms+md)+.001828*sin(4*de-f-md)-e*.001803*sin(f+ms)- .00175*sin(3*f); g = g+e*.00157*sin(md-ms-f)-.001487*sin(f+de)-e*.001481*sin(f+ms+md)+ e*.001417*sin(f-ms-md)+e*.00135*sin(f-ms)+.00133*sin(f-de)+ .001106*sin(f+3*md)+.00102*sin(4*de-f)+.000833*sin(f+4*de-md)+ .000781*sin(md-3*f)+.00067*sin(f+4*de-2*md); g = g+.000606*sin(2*de-3*f)+.000597*sin(2*(de+md)-f)+ e*.000492*sin(2*de+md-ms-f)+.00045*sin(2*(md-de)-f)+ .000439*sin(3*md-f)+.000423*sin(f+2*(de+md))+ .000422*sin(2*de-f-3*md)-e*.000367*sin(ms+f+2*de-md)- e*.000353*sin(ms+f+2*de)+.000331*sin(f+4*de); g = g+e*.000317*sin(2*de+f-ms+md)+e2*.000306*sin(2*(de-ms)-f)- .000283*sin(md+3*f); w1 = .0004664*cos(n); w2 = .0000754*cos(c); eclLat = degToRad(g)*(1-w1-w2); hp = .950724+.051818*cos(md)+.009531*cos(2*de-md)+.007843*cos(2*de)+ .002824*cos(2*md)+.000857*cos(2*de+md)+e*.000533*cos(2*de-ms)+ e*.000401*cos(2*de-md-ms)+e*.00032*cos(md-ms)-.000271*cos(de)- e*.000264*cos(ms+md)-.000198*cos(2*f-md); hp = hp+.000173*cos(3*md)+.000167*cos(4*de-md)-e*.000111*cos(ms)+ .000103*cos(4*de-2*md)-.000084*cos(2*md-2*de)- e*.000083*cos(2*de+ms)+.000079*cos(2*de+2*md)+.000072*cos(4*de)+ e*.000064*cos(2*de-ms+md)-e*.000063*cos(2*de+ms-md)+ e*.000041*cos(ms+de); hp = hp+e*.000035*cos(2*md-ms)-.000033*cos(3*md-2*de)- .00003*cos(md+de)-.000029*cos(2*(f-de))-e*.000029*cos(2*md+ms)+ e2*.000026*cos(2*(de-ms))-.000023*cos(2*(f-de)+md)+ e*.000019*cos(4*de-ms-md); horzPar = degToRad(hp); // At this point we have values of ecliptic longitude, latitude and // horizontal parallax (eclLong, eclLat, horzPar) in radians. // Now compute distance using horizontal parallax. distance = 6378.14 / sin(horzPar); // Finally convert eclLat, eclLon to RA, Dec. EclipticToEquatorial(t, eclLat, eclLon, RA, dec); // RA and Dec are referred to the equinox of date; we want to use // the J2000 equinox instead. A better idea would be to directly // compute the position of the Moon in this coordinate system, but // this was easier. EpochConvert(jd, astro::J2000, RA, dec, RA, dec); // Corrections for internal coordinate system dec -= (PI/2); RA += PI; return Point3d(cos(RA) * sin(dec) * distance, cos(dec) * distance, -sin(RA) * sin(dec) * distance); };

double LunarOrbit::getBoundingRadius (   )  const [inline, private, virtual]

Implements CachingOrbit. Definition at line 730 of file customorbit.cpp. References BoundingRadiusSlack. { return 405504 * BoundingRadiusSlack; };

double LunarOrbit::getPeriod (   )  const [inline, private, virtual]

Implements CachingOrbit. Definition at line 725 of file customorbit.cpp. { return 27.321661; };

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The documentation for this class was generated from the following file:

• src/celengine/customorbit.cpp

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