#include

#include #include #include #include #include #include "fg_time.hxx"
#include "moonpos.hxx"

extern SolarSystem *solarSystem;

#undef E


/*
 * the epoch upon which these astronomical calculations are based is
 * 1990 january 0.0, 631065600 seconds since the beginning of the
 * "unix epoch" (00:00:00 GMT, Jan. 1, 1970)
 *
 * given a number of seconds since the start of the unix epoch,
 * DaysSinceEpoch() computes the number of days since the start of the
 * astronomical epoch (1990 january 0.0)
 */

#define EpochStart           (631065600)
#define DaysSinceEpoch(secs) (((secs)-EpochStart)*(1.0/(24*3600)))

/*
 * assuming the apparent orbit of the moon about the earth is circular,
 * the rate at which the orbit progresses is given by RadsPerDay --
 * FG_2PI radians per orbit divided by 365.242191 days per year:
 */

#define RadsPerDay (FG_2PI/365.242191)

/*
 * details of moon's apparent orbit at epoch 1990.0 (after
 * duffett-smith, table 6, section 46)
 *
 * Epsilon_g    (ecliptic longitude at epoch 1990.0) 279.403303 degrees
 * OmegaBar_g   (ecliptic longitude of perigee)      282.768422 degrees
 * Eccentricity (eccentricity of orbit)                0.016713
 */

#define Epsilon_g    (279.403303*(FG_2PI/360))
#define OmegaBar_g   (282.768422*(FG_2PI/360))
#define Eccentricity (0.016713)

/*
 * MeanObliquity gives the mean obliquity of the earth's axis at epoch
 * 1990.0 (computed as 23.440592 degrees according to the method given
 * in duffett-smith, section 27)
 */
#define MeanObliquity (23.440592*(FG_2PI/360))

/* static double solve_keplers_equation(double); */
/* static double moon_ecliptic_longitude(time_t); */
static void   ecliptic_to_equatorial(double, double, double *, double *);
static double julian_date(int, int, int);
static double GST(time_t);

/*
 * solve Kepler's equation via Newton's method
 * (after duffett-smith, section 47)
 */
/*
static double solve_keplers_equation(double M) {
    double E;
    double delta;

    E = M;
    while (1) {
	delta = E - Eccentricity*sin(E) - M;
	if (fabs(delta) <= 1e-10) break;
	E -= delta / (1 - Eccentricity*cos(E));
    }

    return E;
}
*/


/* compute ecliptic longitude of moon (in radians) (after
 * duffett-smith, section 47) */
/*
static double moon_ecliptic_longitude(time_t ssue) {
    // time_t ssue;              //  seconds since unix epoch
    double D, N;
    double M_moon, E;
    double v;

    D = DaysSinceEpoch(ssue);

    N = RadsPerDay * D;
    N = fmod(N, FG_2PI);
    if (N < 0) N += FG_2PI;

    M_moon = N + Epsilon_g - OmegaBar_g;
    if (M_moon < 0) M_moon += FG_2PI;

    E = solve_keplers_equation(M_moon);
    v = 2 * atan(sqrt((1+Eccentricity)/(1-Eccentricity)) * tan(E/2));

    return (v + OmegaBar_g);
}
*/


/* convert from ecliptic to equatorial coordinates (after
 * duffett-smith, section 27) */

static void ecliptic_to_equatorial(double lambda, double beta, 
				   double *alpha, double *delta) {
    /* double  lambda;            ecliptic longitude       */
    /* double  beta;              ecliptic latitude        */
    /* double *alpha;             (return) right ascension */
    /* double *delta;             (return) declination     */

    double sin_e, cos_e;
    double sin_l, cos_l;

    sin_e = sin(MeanObliquity);
    cos_e = cos(MeanObliquity);
    sin_l = sin(lambda);
    cos_l = cos(lambda);

    *alpha = atan2(sin_l*cos_e - tan(beta)*sin_e, cos_l);
    *delta = asin(sin(beta)*cos_e + cos(beta)*sin_e*sin_l);
}


/* computing julian dates (assuming gregorian calendar, thus this is
 * only valid for dates of 1582 oct 15 or later) (after duffett-smith,
 * section 4) */

static double julian_date(int y, int m, int d) {
    /* int y;                    year (e.g. 19xx)          */
    /* int m;                    month (jan=1, feb=2, ...) */
    /* int d;                    day of month              */

    int    A, B, C, D;
    double JD;

    /* lazy test to ensure gregorian calendar */
    if (y < 1583) {
	FG_LOG( FG_EVENT, FG_ALERT, 
		"WHOOPS! Julian dates only valid for 1582 oct 15 or later" );
    }

    if ((m == 1) || (m == 2)) {
	y -= 1;
	m += 12;
    }

    A = y / 100;
    B = 2 - A + (A / 4);
    C = (int)(365.25 * y);
    D = (int)(30.6001 * (m + 1));

    JD = B + C + D + d + 1720994.5;

    return JD;
}


/* compute greenwich mean sidereal time (GST) corresponding to a given
 * number of seconds since the unix epoch (after duffett-smith,
 * section 12) */
static double GST(time_t ssue) {
    /* time_t ssue;           seconds since unix epoch */

    double     JD;
    double     T, T0;
    double     UT;
    struct tm *tm;

    tm = gmtime(&ssue);

    JD = julian_date(tm->tm_year+1900, tm->tm_mon+1, tm->tm_mday);
    T  = (JD - 2451545) / 36525;

    T0 = ((T + 2.5862e-5) * T + 2400.051336) * T + 6.697374558;

    T0 = fmod(T0, 24.0);
    if (T0 < 0) T0 += 24;

    UT = tm->tm_hour + (tm->tm_min + tm->tm_sec / 60.0) / 60.0;

    T0 += UT * 1.002737909;
    T0 = fmod(T0, 24.0);
    if (T0 < 0) T0 += 24;

    return T0;
}


/* given a particular time (expressed in seconds since the unix
 * epoch), compute position on the earth (lat, lon) such that moon is
 * directly overhead.  (lat, lon are reported in radians */

void fgMoonPosition(time_t ssue, double *lon, double *lat) {
    /* time_t  ssue;           seconds since unix epoch */
    /* double *lat;            (return) latitude        */
    /* double *lon;            (return) longitude       */

    /* double lambda; */
    double alpha, delta;
    double tmp;

    /* lambda = moon_ecliptic_longitude(ssue); */
    /* ecliptic_to_equatorial(lambda, 0.0, &alpha, &delta); */
    //ecliptic_to_equatorial (solarPosition.lonMoon, 0.0, &alpha, &delta);
    
    /* ********************************************************************** 
     * NOTE: in the next function, each time the moon's position is updated, the
     * the moon's longitude is returned from solarSystem->moon. Note that the 
     * moon's position is updated at a much higher frequency than the rate at 
     * which the solar system's rebuilds occur. This is not a problem, however,
     * because the fgMoonPosition we're talking about here concerns the changing
     * position of the moon due to the daily rotation of the earth.
     * The ecliptic longitude, however, represents the position of the moon with
     * respect to the stars, and completes just one cycle over the course of a 
     * year. Its therefore pretty safe to update the moon's longitude only once
     * every ten minutes. (Comment added by Durk Talsma).
     ************************************************************************/

    ecliptic_to_equatorial( SolarSystem::theSolarSystem->getMoon()->getLon(),
			    0.0, &alpha, &delta );
    tmp = alpha - (FG_2PI/24)*GST(ssue);
    if (tmp < -FG_PI) {
	do tmp += FG_2PI;
	while (tmp < -FG_PI);
    } else if (tmp > FG_PI) {
	do tmp -= FG_2PI;
	while (tmp < -FG_PI);
    }

    *lon = tmp;
    *lat = delta;
}


/* given a particular time expressed in side real time at prime
 * meridian (GST), compute position on the earth (lat, lon) such that
 * moon is directly overhead.  (lat, lon are reported in radians */

static void fgMoonPositionGST(double gst, double *lon, double *lat) {
    /* time_t  ssue;           seconds since unix epoch */
    /* double *lat;            (return) latitude        */
    /* double *lon;            (return) longitude       */

    /* double lambda; */
    double alpha, delta;
    double tmp;

    /* lambda = moon_ecliptic_longitude(ssue); */
    /* ecliptic_to_equatorial(lambda, 0.0, &alpha, &delta); */
    //ecliptic_to_equatorial (solarPosition.lonMoon, 0.0, &alpha, &delta);
    ecliptic_to_equatorial( SolarSystem::theSolarSystem->getMoon()->getLon(),
			    SolarSystem::theSolarSystem->getMoon()->getLat(), 
			    &alpha,  &delta );

//    tmp = alpha - (FG_2PI/24)*GST(ssue);
    tmp = alpha - (FG_2PI/24)*gst;	
    if (tmp < -FG_PI) {
	do tmp += FG_2PI;
	while (tmp < -FG_PI);
    } else if (tmp > FG_PI) {
	do tmp -= FG_2PI;
	while (tmp < -FG_PI);
    }

    *lon = tmp;
    *lat = delta;
}


// update the cur_time_params structure with the current moon position
void fgUpdateMoonPos( void ) {
    fgLIGHT *l;
    fgTIME *t;
    FGView *v;
    MAT3vec nup, nmoon, v0, surface_to_moon;
    Point3D p, rel_moonpos;
    double dot, east_dot;
    double moon_gd_lat, sl_radius;
    double ntmp;

    l = &cur_light_params;
    t = &cur_time_params;
    v = ¤t_view;

    FG_LOG( FG_EVENT, FG_INFO, "  Updating Moon position" );

    // (not sure why there was two)
    // fgMoonPosition(t->cur_time, &l->moon_lon, &moon_gd_lat);
    fgMoonPositionGST(t->gst, &l->moon_lon, &moon_gd_lat);

    fgGeodToGeoc(moon_gd_lat, 0.0, &sl_radius, &l->moon_gc_lat);

    p = Point3D( l->moon_lon, l->moon_gc_lat, sl_radius );
    l->fg_moonpos = fgPolarToCart3d(p);

    FG_LOG( FG_EVENT, FG_INFO, "    t->cur_time = " << t->cur_time );
    FG_LOG( FG_EVENT, FG_INFO, 
	    "    Moon Geodetic lat = " << moon_gd_lat
	    << " Geocentric lat = " << l->moon_gc_lat );

    // I think this will work better for generating the moon light vector
    l->moon_vec[0] = l->fg_moonpos.x();
    l->moon_vec[1] = l->fg_moonpos.y();
    l->moon_vec[2] = l->fg_moonpos.z();
    MAT3_NORMALIZE_VEC(l->moon_vec, ntmp);
    MAT3_SCALE_VEC(l->moon_vec_inv, l->moon_vec, -1.0);

    // make sure these are directional light sources only
    l->moon_vec[3] = 0.0;
    l->moon_vec_inv[3] = 0.0;

    // printf("  l->moon_vec = %.2f %.2f %.2f\n", l->moon_vec[0], l->moon_vec[1],
    //        l->moon_vec[2]);

    // calculate the moon's relative angle to local up
    MAT3_COPY_VEC(nup, v->get_local_up());
    nmoon[0] = l->fg_moonpos.x(); 
    nmoon[1] = l->fg_moonpos.y();
    nmoon[2] = l->fg_moonpos.z();
    MAT3_NORMALIZE_VEC(nup, ntmp);
    MAT3_NORMALIZE_VEC(nmoon, ntmp);

    l->moon_angle = acos(MAT3_DOT_PRODUCT(nup, nmoon));
    // printf("  MOON ANGLE relative to current location = %.3f rads.\n", 
    //        l->moon_angle);
    
    // calculate vector to moon's position on the earth's surface
    rel_moonpos = l->fg_moonpos - (v->get_view_pos() + scenery.center);
    v->set_to_moon( rel_moonpos.x(), rel_moonpos.y(), rel_moonpos.z() );
    // printf( "Vector to moon = %.2f %.2f %.2f\n",
    //         v->to_moon[0], v->to_moon[1], v->to_moon[2]);

    // make a vector to the current view position
    Point3D view_pos = v->get_view_pos();
    MAT3_SET_VEC(v0, view_pos.x(), view_pos.y(), view_pos.z());

    // Given a vector from the view position to the point on the
    // earth's surface the moon is directly over, map into onto the
    // local plane representing "horizontal".
    map_vec_onto_cur_surface_plane( v->get_local_up(), v0, v->get_to_moon(), 
				    surface_to_moon );
    MAT3_NORMALIZE_VEC(surface_to_moon, ntmp);
    v->set_surface_to_moon( surface_to_moon[0], surface_to_moon[1], 
			   surface_to_moon[2] );
    // printf("Surface direction to moon is %.2f %.2f %.2f\n",
    //        v->surface_to_moon[0], v->surface_to_moon[1], v->surface_to_moon[2]);
    // printf("Should be close to zero = %.2f\n", 
    //        MAT3_DOT_PRODUCT(v->local_up, v->surface_to_moon));

    // calculate the angle between v->surface_to_moon and
    // v->surface_east.  We do this so we can sort out the acos()
    // ambiguity.  I wish I could think of a more efficient way ... :-(
    east_dot = MAT3_DOT_PRODUCT( surface_to_moon, v->get_surface_east() );
    // printf("  East dot product = %.2f\n", east_dot);

    // calculate the angle between v->surface_to_moon and
    // v->surface_south.  this is how much we have to rotate the sky
    // for it to align with the moon
    dot = MAT3_DOT_PRODUCT( surface_to_moon, v->get_surface_south() );
    // printf("  Dot product = %.2f\n", dot);
    if ( east_dot >= 0 ) {
	l->moon_rotation = acos(dot);
    } else {
	l->moon_rotation = -acos(dot);
    }
    // printf("  Sky needs to rotate = %.3f rads = %.1f degrees.\n", 
    //        angle, angle * RAD_TO_DEG); */
}