package sgp4;
/*     ----------------------------------------------------------------
*
*                               sgp4unit.cpp
*
*    this file contains the sgp4 procedures for analytical propagation
*    of a satellite. the code was originally released in the 1980 and 1986
*    spacetrack papers. a detailed discussion of the theory and history
*    may be found in the 2006 aiaa paper by vallado, crawford, hujsak,
*    and kelso.
*
*                            companion code for
*               fundamentals of astrodynamics and applications
*                                    2013
*                              by david vallado
*
*     (w) 719-573-2600, email dvallado@agi.com, davallado@gmail.com
*
*    current :
*               7 dec 15  david vallado
*                           fix jd, jdfrac
*    changes :
*               3 nov 14  david vallado
*                           update to msvs2013 c++
*              30 aug 10  david vallado
*                           delete unused variables in initl
*                           replace pow integer 2, 3 with multiplies for speed
*               3 nov 08  david vallado
*                           put returns in for error codes
*              29 sep 08  david vallado
*                           fix atime for faster operation in dspace
*                           add operationmode for afspc (a) or improved (i)
*                           performance mode
*              16 jun 08  david vallado
*                           update small eccentricity check
*              16 nov 07  david vallado
*                           misc fixes for better compliance
*              20 apr 07  david vallado
*                           misc fixes for constants
*              11 aug 06  david vallado
*                           chg lyddane choice back to strn3, constants, misc doc
*              15 dec 05  david vallado
*                           misc fixes
*              26 jul 05  david vallado
*                           fixes for paper
*                           note that each fix is preceded by a
*                           comment with "sgp4fix" and an explanation of
*                           what was changed
*              10 aug 04  david vallado
*                           2nd printing baseline working
*              14 may 01  david vallado
*                           2nd edition baseline
*                     80  norad
*                           original baseline
*       ----------------------------------------------------------------      */

public class SGP4 
{
	private static final double pi = Math.PI;
	private static final double twopi = 2.0d*Math.PI;
	private static final double deg2rad = pi / 180.0;

	public static final int wgs72old = 1;
	public static final int wgs72 = 2;
	public static final int wgs84 = 3;
	
	
	/* -----------------------------------------------------------------------------
	*
	*                           procedure dpper
	*
	*  this procedure provides deep space long period periodic contributions
	*    to the mean elements.  by design, these periodics are zero at epoch.
	*    this used to be dscom which included initialization, but it's really a
	*    recurring function.
	*
	*  author        : david vallado                  719-573-2600   28 jun 2005
	*
	*  inputs        :
	*    e3          -
	*    ee2         -
	*    peo         -
	*    pgho        -
	*    pho         -
	*    pinco       -
	*    plo         -
	*    se2 , se3 , sgh2, sgh3, sgh4, sh2, sh3, si2, si3, sl2, sl3, sl4 -
	*    t           -
	*    xh2, xh3, xi2, xi3, xl2, xl3, xl4 -
	*    zmol        -
	*    zmos        -
	*    ep          - eccentricity                           0.0 - 1.0
	*    inclo       - inclination - needed for lyddane modification
	*    nodep       - right ascension of ascending node
	*    argpp       - argument of perigee
	*    mp          - mean anomaly
	*
	*  outputs       :
	*    ep          - eccentricity                           0.0 - 1.0
	*    inclp       - inclination
	*    nodep        - right ascension of ascending node
	*    argpp       - argument of perigee
	*    mp          - mean anomaly
	*
	*  locals        :
	*    alfdp       -
	*    betdp       -
	*    cosip  , sinip  , cosop  , sinop  ,
	*    dalf        -
	*    dbet        -
	*    dls         -
	*    f2, f3      -
	*    pe          -
	*    pgh         -
	*    ph          -
	*    pinc        -
	*    pl          -
	*    sel   , ses   , sghl  , sghs  , shl   , shs   , sil   , sinzf , sis   ,
	*    sll   , sls
	*    xls         -
	*    xnoh        -
	*    zf          -
	*    zm          -
	*
	*  coupling      :
	*    none.
	*
	*  references    :
	*    hoots, roehrich, norad spacetrack report #3 1980
	*    hoots, norad spacetrack report #6 1986
	*    hoots, schumacher and glover 2004
	*    vallado, crawford, hujsak, kelso  2006
	----------------------------------------------------------------------------*/

	public static void dpper
		(
		double e3, double ee2, double peo, double pgho, double pho,
		double pinco, double plo, double se2, double se3, double sgh2,
		double sgh3, double sgh4, double sh2, double sh3, double si2,
		double si3, double sl2, double sl3, double sl4, double t,
		double xgh2, double xgh3, double xgh4, double xh2, double xh3,
		double xi2, double xi3, double xl2, double xl3, double xl4,
		double zmol, double zmos,
		char init,
		ElsetRec rec,
		char opsmode
		)
	{
		/* --------------------- local variables ------------------------ */
		double alfdp, betdp, cosip, cosop, dalf, dbet, dls,
			f2, f3, pe, pgh, ph, pinc, pl,
			sel, ses, sghl, sghs, shll, shs, sil,
			sinip, sinop, sinzf, sis, sll, sls, xls,
			xnoh, zf, zm, zel, zes, znl, zns;
		
		/* ---------------------- constants ----------------------------- */
		zns = 1.19459e-5;
		zes = 0.01675;
		znl = 1.5835218e-4;
		zel = 0.05490;

		/* --------------- calculate time varying periodics ----------- */
		zm = zmos + zns * t;
		// be sure that the initial call has time set to zero
		if (init == 'y')
			zm = zmos;
		zf = zm + 2.0 * zes * Math.sin(zm);
		sinzf = Math.sin(zf);
		f2 = 0.5 * sinzf * sinzf - 0.25;
		f3 = -0.5 * sinzf * Math.cos(zf);
		ses = se2* f2 + se3 * f3;
		sis = si2 * f2 + si3 * f3;
		sls = sl2 * f2 + sl3 * f3 + sl4 * sinzf;
		sghs = sgh2 * f2 + sgh3 * f3 + sgh4 * sinzf;
		shs = sh2 * f2 + sh3 * f3;
		zm = zmol + znl * t;
		if (init == 'y')
			zm = zmol;
		zf = zm + 2.0 * zel * Math.sin(zm);
		sinzf = Math.sin(zf);
		f2 = 0.5 * sinzf * sinzf - 0.25;
		f3 = -0.5 * sinzf * Math.cos(zf);
		sel = ee2 * f2 + e3 * f3;
		sil = xi2 * f2 + xi3 * f3;
		sll = xl2 * f2 + xl3 * f3 + xl4 * sinzf;
		sghl = xgh2 * f2 + xgh3 * f3 + xgh4 * sinzf;
		shll = xh2 * f2 + xh3 * f3;
		pe = ses + sel;
		pinc = sis + sil;
		pl = sls + sll;
		pgh = sghs + sghl;
		ph = shs + shll;
		
		if (init == 'n')
		{
			pe = pe - peo;
			pinc = pinc - pinco;
			pl = pl - plo;
			pgh = pgh - pgho;
			ph = ph - pho;
			rec.inclp = rec.inclp + pinc;
			rec.ep = rec.ep + pe;
			sinip = Math.sin(rec.inclp);
			cosip = Math.cos(rec.inclp);

			/* ----------------- apply periodics directly ------------ */
			//  sgp4fix for lyddane choice
			//  strn3 used original inclination - this is technically feasible
			//  gsfc used perturbed inclination - also technically feasible
			//  probably best to readjust the 0.2 limit value and limit discontinuity
			//  0.2 rad = 11.45916 deg
			//  use next line for original strn3 approach and original inclination
			//  if (inclo >= 0.2)
			//  use next line for gsfc version and perturbed inclination
			if (rec.inclp >= 0.2)
			{
				ph = ph / sinip;
				pgh = pgh - cosip * ph;
				rec.argpp = rec.argpp + pgh;
				rec.nodep = rec.nodep + ph;
				rec.mp = rec.mp + pl;
			}
			else
			{
				/* ---- apply periodics with lyddane modification ---- */
				sinop = Math.sin(rec.nodep);
				cosop = Math.cos(rec.nodep);
				alfdp = sinip * sinop;
				betdp = sinip * cosop;
				dalf = ph * cosop + pinc * cosip * sinop;
				dbet = -ph * sinop + pinc * cosip * cosop;
				alfdp = alfdp + dalf;
				betdp = betdp + dbet;
				rec.nodep = fmod(rec.nodep, twopi);
				//  sgp4fix for afspc written intrinsic functions
				// nodep used without a trigonometric function ahead
				if ((rec.nodep < 0.0) && (opsmode == 'a'))
					rec.nodep = rec.nodep + twopi;
				xls = rec.mp + rec.argpp + cosip * rec.nodep;
				dls = pl + pgh - pinc * rec.nodep * sinip;
				xls = xls + dls;
				xls = fmod(xls,twopi);
				xnoh = rec.nodep;
				rec.nodep = Math.atan2(alfdp, betdp);
				//  sgp4fix for afspc written intrinsic functions
				// nodep used without a trigonometric function ahead
				if ((rec.nodep < 0.0) && (opsmode == 'a'))
					rec.nodep = rec.nodep + twopi;
				if (Math.abs(xnoh - rec.nodep) > pi)
					if (rec.nodep < xnoh)
						rec.nodep = rec.nodep + twopi;
					else
						rec.nodep = rec.nodep - twopi;
				rec.mp = rec.mp + pl;
				rec.argpp = xls - rec.mp - cosip * rec.nodep;
			}
		}   // if init == 'n'

	}  // dpper

	/*-----------------------------------------------------------------------------
	*
	*                           procedure dscom
	*
	*  this procedure provides deep space common items used by both the secular
	*    and periodics subroutines.  input is provided as shown. this routine
	*    used to be called dpper, but the functions inside weren't well organized.
	*
	*  author        : david vallado                  719-573-2600   28 jun 2005
	*
	*  inputs        :
	*    epoch       -
	*    ep          - eccentricity
	*    argpp       - argument of perigee
	*    tc          -
	*    inclp       - inclination
	*    nodep       - right ascension of ascending node
	*    np          - mean motion
	*
	*  outputs       :
	*    sinim  , cosim  , sinomm , cosomm , snodm  , cnodm
	*    day         -
	*    e3          -
	*    ee2         -
	*    em          - eccentricity
	*    emsq        - eccentricity squared
	*    gam         -
	*    peo         -
	*    pgho        -
	*    pho         -
	*    pinco       -
	*    plo         -
	*    rtemsq      -
	*    se2, se3         -
	*    sgh2, sgh3, sgh4        -
	*    sh2, sh3, si2, si3, sl2, sl3, sl4         -
	*    s1, s2, s3, s4, s5, s6, s7          -
	*    ss1, ss2, ss3, ss4, ss5, ss6, ss7, sz1, sz2, sz3         -
	*    sz11, sz12, sz13, sz21, sz22, sz23, sz31, sz32, sz33        -
	*    xgh2, xgh3, xgh4, xh2, xh3, xi2, xi3, xl2, xl3, xl4         -
	*    nm          - mean motion
	*    z1, z2, z3, z11, z12, z13, z21, z22, z23, z31, z32, z33         -
	*    zmol        -
	*    zmos        -
	*
	*  locals        :
	*    a1, a2, a3, a4, a5, a6, a7, a8, a9, a10         -
	*    betasq      -
	*    cc          -
	*    ctem, stem        -
	*    x1, x2, x3, x4, x5, x6, x7, x8          -
	*    xnodce      -
	*    xnoi        -
	*    zcosg  , zsing  , zcosgl , zsingl , zcosh  , zsinh  , zcoshl , zsinhl ,
	*    zcosi  , zsini  , zcosil , zsinil ,
	*    zx          -
	*    zy          -
	*
	*  coupling      :
	*    none.
	*
	*  references    :
	*    hoots, roehrich, norad spacetrack report #3 1980
	*    hoots, norad spacetrack report #6 1986
	*    hoots, schumacher and glover 2004
	*    vallado, crawford, hujsak, kelso  2006
	----------------------------------------------------------------------------*/

	public static void dscom
		(
		double epoch, double ep, double argpp, double tc, double inclp,
		double nodep, double np,
		ElsetRec rec
		)
	{
		/* -------------------------- constants ------------------------- */
		final double zes = 0.01675;
		final double zel = 0.05490;
		final double c1ss = 2.9864797e-6;
		final double c1l = 4.7968065e-7;
		final double zsinis = 0.39785416;
		final double zcosis = 0.91744867;
		final double zcosgs = 0.1945905;
		final double zsings = -0.98088458;

		/* --------------------- local variables ------------------------ */
		int lsflg;
		double a1, a2, a3, a4, a5, a6, a7,
			a8, a9, a10, betasq, cc, ctem, stem,
			x1, x2, x3, x4, x5, x6, x7,
			x8, xnodce, xnoi, zcosg, zcosgl, zcosh, zcoshl,
			zcosi, zcosil, zsing, zsingl, zsinh, zsinhl, zsini,
			zsinil, zx, zy;

		rec.nm = np;
		rec.em = ep;
		rec.snodm = Math.sin(nodep);
		rec.cnodm = Math.cos(nodep);
		rec.sinomm = Math.sin(argpp);
		rec.cosomm = Math.cos(argpp);
		rec.sinim = Math.sin(inclp);
		rec.cosim = Math.cos(inclp);
		rec.emsq = rec.em * rec.em;
		betasq = 1.0 - rec.emsq;
		rec.rtemsq = Math.sqrt(betasq);

		/* ----------------- initialize lunar solar terms --------------- */
		rec.peo = 0.0;
		rec.pinco = 0.0;
		rec.plo = 0.0;
		rec.pgho = 0.0;
		rec.pho = 0.0;
		rec.day = epoch + 18261.5 + tc / 1440.0;
		xnodce = fmod(4.5236020 - 9.2422029e-4 * rec.day, twopi);
		stem = Math.sin(xnodce);
		ctem = Math.cos(xnodce);
		zcosil = 0.91375164 - 0.03568096 * ctem;
		zsinil = Math.sqrt(1.0 - zcosil * zcosil);
		zsinhl = 0.089683511 * stem / zsinil;
		zcoshl = Math.sqrt(1.0 - zsinhl * zsinhl);
		rec.gam = 5.8351514 + 0.0019443680 * rec.day;
		zx = 0.39785416 * stem / zsinil;
		zy = zcoshl * ctem + 0.91744867 * zsinhl * stem;
		zx = Math.atan2(zx, zy);
		zx = rec.gam + zx - xnodce;
		zcosgl = Math.cos(zx);
		zsingl = Math.sin(zx);

		/* ------------------------- do solar terms --------------------- */
		zcosg = zcosgs;
		zsing = zsings;
		zcosi = zcosis;
		zsini = zsinis;
		zcosh = rec.cnodm;
		zsinh = rec.snodm;
		cc = c1ss;
		xnoi = 1.0 / rec.nm;
		
		for (lsflg = 1; lsflg <= 2; lsflg++)
		{
			a1 = zcosg * zcosh + zsing * zcosi * zsinh;
			a3 = -zsing * zcosh + zcosg * zcosi * zsinh;
			a7 = -zcosg * zsinh + zsing * zcosi * zcosh;
			a8 = zsing * zsini;
			a9 = zsing * zsinh + zcosg * zcosi * zcosh;
			a10 = zcosg * zsini;
			a2 = rec.cosim * a7 + rec.sinim * a8;
			a4 = rec.cosim * a9 + rec.sinim * a10;
			a5 = -rec.sinim * a7 + rec.cosim * a8;
			a6 = -rec.sinim * a9 + rec.cosim * a10;

			x1 = a1 * rec.cosomm + a2 * rec.sinomm;
			x2 = a3 * rec.cosomm + a4 * rec.sinomm;
			x3 = -a1 * rec.sinomm + a2 * rec.cosomm;
			x4 = -a3 * rec.sinomm + a4 * rec.cosomm;
			x5 = a5 * rec.sinomm;
			x6 = a6 * rec.sinomm;
			x7 = a5 * rec.cosomm;
			x8 = a6 * rec.cosomm;

			rec.z31 = 12.0 * x1 * x1 - 3.0 * x3 * x3;
			rec.z32 = 24.0 * x1 * x2 - 6.0 * x3 * x4;
			rec.z33 = 12.0 * x2 * x2 - 3.0 * x4 * x4;
			rec.z1 = 3.0 *  (a1 * a1 + a2 * a2) + rec.z31 * rec.emsq;
			rec.z2 = 6.0 *  (a1 * a3 + a2 * a4) + rec.z32 * rec.emsq;
			rec.z3 = 3.0 *  (a3 * a3 + a4 * a4) + rec.z33 * rec.emsq;
			rec.z11 = -6.0 * a1 * a5 + rec.emsq *  (-24.0 * x1 * x7 - 6.0 * x3 * x5);
			rec.z12 = -6.0 *  (a1 * a6 + a3 * a5) + rec.emsq *
				(-24.0 * (x2 * x7 + x1 * x8) - 6.0 * (x3 * x6 + x4 * x5));
			rec.z13 = -6.0 * a3 * a6 + rec.emsq * (-24.0 * x2 * x8 - 6.0 * x4 * x6);
			rec.z21 = 6.0 * a2 * a5 + rec.emsq * (24.0 * x1 * x5 - 6.0 * x3 * x7);
			rec.z22 = 6.0 *  (a4 * a5 + a2 * a6) + rec.emsq *
				(24.0 * (x2 * x5 + x1 * x6) - 6.0 * (x4 * x7 + x3 * x8));
			rec.z23 = 6.0 * a4 * a6 + rec.emsq * (24.0 * x2 * x6 - 6.0 * x4 * x8);
			rec.z1 = rec.z1 + rec.z1 + betasq * rec.z31;
			rec.z2 = rec.z2 + rec.z2 + betasq * rec.z32;
			rec.z3 = rec.z3 + rec.z3 + betasq * rec.z33;
			rec.s3 = cc * xnoi;
			rec.s2 = -0.5 * rec.s3 / rec.rtemsq;
			rec.s4 = rec.s3 * rec.rtemsq;
			rec.s1 = -15.0 * rec.em * rec.s4;
			rec.s5 = x1 * x3 + x2 * x4;
			rec.s6 = x2 * x3 + x1 * x4;
			rec.s7 = x2 * x4 - x1 * x3;

			/* ----------------------- do lunar terms ------------------- */
			if (lsflg == 1)
			{
				rec.ss1 = rec.s1;
				rec.ss2 = rec.s2;
				rec.ss3 = rec.s3;
				rec.ss4 = rec.s4;
				rec.ss5 = rec.s5;
				rec.ss6 = rec.s6;
				rec.ss7 = rec.s7;
				rec.sz1 = rec.z1;
				rec.sz2 = rec.z2;
				rec.sz3 = rec.z3;
				rec.sz11 = rec.z11;
				rec.sz12 = rec.z12;
				rec.sz13 = rec.z13;
				rec.sz21 = rec.z21;
				rec.sz22 = rec.z22;
				rec.sz23 = rec.z23;
				rec.sz31 = rec.z31;
				rec.sz32 = rec.z32;
				rec.sz33 = rec.z33;
				zcosg = zcosgl;
				zsing = zsingl;
				zcosi = zcosil;
				zsini = zsinil;
				zcosh = zcoshl * rec.cnodm + zsinhl * rec.snodm;
				zsinh = rec.snodm * zcoshl - rec.cnodm * zsinhl;
				cc = c1l;
			}
		}

		rec.zmol = fmod(4.7199672 + 0.22997150  * rec.day - rec.gam, twopi);
		rec.zmos = fmod(6.2565837 + 0.017201977 * rec.day, twopi);

		/* ------------------------ do solar terms ---------------------- */
		rec.se2 = 2.0 * rec.ss1 * rec.ss6;
		rec.se3 = 2.0 * rec.ss1 * rec.ss7;
		rec.si2 = 2.0 * rec.ss2 * rec.sz12;
		rec.si3 = 2.0 * rec.ss2 * (rec.sz13 - rec.sz11);
		rec.sl2 = -2.0 * rec.ss3 * rec.sz2;
		rec.sl3 = -2.0 * rec.ss3 * (rec.sz3 - rec.sz1);
		rec.sl4 = -2.0 * rec.ss3 * (-21.0 - 9.0 * rec.emsq) * zes;
		rec.sgh2 = 2.0 * rec.ss4 * rec.sz32;
		rec.sgh3 = 2.0 * rec.ss4 * (rec.sz33 - rec.sz31);
		rec.sgh4 = -18.0 * rec.ss4 * zes;
		rec.sh2 = -2.0 * rec.ss2 * rec.sz22;
		rec.sh3 = -2.0 * rec.ss2 * (rec.sz23 - rec.sz21);

		/* ------------------------ do lunar terms ---------------------- */
		rec.ee2 = 2.0 * rec.s1 * rec.s6;
		rec.e3 = 2.0 * rec.s1 * rec.s7;
		rec.xi2 = 2.0 * rec.s2 * rec.z12;
		rec.xi3 = 2.0 * rec.s2 * (rec.z13 - rec.z11);
		rec.xl2 = -2.0 * rec.s3 * rec.z2;
		rec.xl3 = -2.0 * rec.s3 * (rec.z3 - rec.z1);
		rec.xl4 = -2.0 * rec.s3 * (-21.0 - 9.0 * rec.emsq) * zel;
		rec.xgh2 = 2.0 * rec.s4 * rec.z32;
		rec.xgh3 = 2.0 * rec.s4 * (rec.z33 - rec.z31);
		rec.xgh4 = -18.0 * rec.s4 * zel;
		rec.xh2 = -2.0 * rec.s2 * rec.z22;
		rec.xh3 = -2.0 * rec.s2 * (rec.z23 - rec.z21);
	}  // dscom

	/*-----------------------------------------------------------------------------
	*
	*                           procedure dsinit
	*
	*  this procedure provides deep space contributions to mean motion dot due
	*    to geopotential resonance with half day and one day orbits.
	*
	*  author        : david vallado                  719-573-2600   28 jun 2005
	*
	*  inputs        :
	*    xke         - reciprocal of tumin
	*    cosim, sinim-
	*    emsq        - eccentricity squared
	*    argpo       - argument of perigee
	*    s1, s2, s3, s4, s5      -
	*    ss1, ss2, ss3, ss4, ss5 -
	*    sz1, sz3, sz11, sz13, sz21, sz23, sz31, sz33 -
	*    t           - time
	*    tc          -
	*    gsto        - greenwich sidereal time                   rad
	*    mo          - mean anomaly
	*    mdot        - mean anomaly dot (rate)
	*    no          - mean motion
	*    nodeo       - right ascension of ascending node
	*    nodedot     - right ascension of ascending node dot (rate)
	*    xpidot      -
	*    z1, z3, z11, z13, z21, z23, z31, z33 -
	*    eccm        - eccentricity
	*    argpm       - argument of perigee
	*    inclm       - inclination
	*    mm          - mean anomaly
	*    xn          - mean motion
	*    nodem       - right ascension of ascending node
	*
	*  outputs       :
	*    em          - eccentricity
	*    argpm       - argument of perigee
	*    inclm       - inclination
	*    mm          - mean anomaly
	*    nm          - mean motion
	*    nodem       - right ascension of ascending node
	*    irez        - flag for resonance           0-none, 1-one day, 2-half day
	*    atime       -
	*    d2201, d2211, d3210, d3222, d4410, d4422, d5220, d5232, d5421, d5433    -
	*    dedt        -
	*    didt        -
	*    dmdt        -
	*    dndt        -
	*    dnodt       -
	*    domdt       -
	*    del1, del2, del3        -
	*    ses  , sghl , sghs , sgs  , shl  , shs  , sis  , sls
	*    theta       -
	*    xfact       -
	*    xlamo       -
	*    xli         -
	*    xni
	*
	*  locals        :
	*    ainv2       -
	*    aonv        -
	*    cosisq      -
	*    eoc         -
	*    f220, f221, f311, f321, f322, f330, f441, f442, f522, f523, f542, f543  -
	*    g200, g201, g211, g300, g310, g322, g410, g422, g520, g521, g532, g533  -
	*    sini2       -
	*    temp        -
	*    temp1       -
	*    theta       -
	*    xno2        -
	*
	*  coupling      :
	*    getgravconst- no longer used
	*
	*  references    :
	*    hoots, roehrich, norad spacetrack report #3 1980
	*    hoots, norad spacetrack report #6 1986
	*    hoots, schumacher and glover 2004
	*    vallado, crawford, hujsak, kelso  2006
	----------------------------------------------------------------------------*/

	public static void dsinit
		(
		// sgp4fix just send in xke as a constant and eliminate getgravfinal call
		// gravconsttype whichconst, 
				double tc, double xpidot,
		ElsetRec rec
		)
	{
		/* --------------------- local variables ------------------------ */

		double ainv2, aonv = 0.0, cosisq, eoc, f220, f221, f311,
			f321, f322, f330, f441, f442, f522, f523,
			f542, f543, g200, g201, g211, g300, g310,
			g322, g410, g422, g520, g521, g532, g533,
			ses, sgs, sghl, sghs, shs, shll, sis,
			sini2, sls, temp, temp1, theta, xno2, q22,
			q31, q33, root22, root44, root54, rptim, root32,
			root52, x2o3, znl, emo, zns, emsqo;

		q22 = 1.7891679e-6;
		q31 = 2.1460748e-6;
		q33 = 2.2123015e-7;
		root22 = 1.7891679e-6;
		root44 = 7.3636953e-9;
		root54 = 2.1765803e-9;
		rptim = 4.37526908801129966e-3; // this equates to 7.29211514668855e-5 rad/sec
		root32 = 3.7393792e-7;
		root52 = 1.1428639e-7;
		x2o3 = 2.0 / 3.0;
		znl = 1.5835218e-4;
		zns = 1.19459e-5;

		// sgp4fix identify constants and allow alternate values
		// just xke is used here so pass it in rather than have multiple calls
		// getgravconst( whichconst, tumin, mu, radiusearthkm, xke, j2, j3, j4, j3oj2 );

		/* -------------------- deep space initialization ------------ */
		rec.irez = 0;
		if ((rec.nm < 0.0052359877) && (rec.nm > 0.0034906585))
			rec.irez = 1;
		if ((rec.nm >= 8.26e-3) && (rec.nm <= 9.24e-3) && (rec.em >= 0.5))
			rec.irez = 2;

		/* ------------------------ do solar terms ------------------- */
		ses = rec.ss1 * zns * rec.ss5;
		sis = rec.ss2 * zns * (rec.sz11 + rec.sz13);
		sls = -zns * rec.ss3 * (rec.sz1 + rec.sz3 - 14.0 - 6.0 * rec.emsq);
		sghs = rec.ss4 * zns * (rec.sz31 + rec.sz33 - 6.0);
		shs = -zns * rec.ss2 * (rec.sz21 + rec.sz23);
		// sgp4fix for 180 deg incl
		if ((rec.inclm < 5.2359877e-2) || (rec.inclm > pi - 5.2359877e-2))
			shs = 0.0;
		if (rec.sinim != 0.0)
			shs = shs / rec.sinim;
		sgs = sghs - rec.cosim * shs;

		/* ------------------------- do lunar terms ------------------ */
		rec.dedt = ses + rec.s1 * znl * rec.s5;
		rec.didt = sis + rec.s2 * znl * (rec.z11 + rec.z13);
		rec.dmdt = sls - znl * rec.s3 * (rec.z1 + rec.z3 - 14.0 - 6.0 * rec.emsq);
		sghl = rec.s4 * znl * (rec.z31 + rec.z33 - 6.0);
		shll = -znl * rec.s2 * (rec.z21 + rec.z23);
		// sgp4fix for 180 deg incl
		if ((rec.inclm < 5.2359877e-2) || (rec.inclm > pi - 5.2359877e-2))
			shll = 0.0;
		rec.domdt = sgs + sghl;
		rec.dnodt = shs;
		if (rec.sinim != 0.0)
		{
			rec.domdt = rec.domdt - rec.cosim / rec.sinim * shll;
			rec.dnodt = rec.dnodt + shll / rec.sinim;
		}

		/* ----------- calculate deep space resonance effects -------- */
		rec.dndt = 0.0;
		theta = fmod(rec.gsto + tc * rptim, twopi);
		rec.em = rec.em + rec.dedt * rec.t;
		rec.inclm = rec.inclm + rec.didt * rec.t;
		rec.argpm = rec.argpm + rec.domdt * rec.t;
		rec.nodem = rec.nodem + rec.dnodt * rec.t;
		rec.mm = rec.mm + rec.dmdt * rec.t;
		//   sgp4fix for negative inclinations
		//   the following if statement should be commented out
		//if (inclm < 0.0)
		//  {
		//    inclm  = -inclm;
		//    argpm  = argpm - pi;
		//    nodem = nodem + pi;
		//  }

		/* -------------- initialize the resonance terms ------------- */
		if (rec.irez != 0)
		{
			aonv = Math.pow(rec.nm / rec.xke, x2o3);

			/* ---------- geopotential resonance for 12 hour orbits ------ */
			if (rec.irez == 2)
			{
				cosisq = rec.cosim * rec.cosim;
				emo = rec.em;
				rec.em = rec.ecco;
				emsqo = rec.emsq;
				rec.emsq = rec.eccsq;
				eoc = rec.em * rec.emsq;
				g201 = -0.306 - (rec.em - 0.64) * 0.440;

				if (rec.em <= 0.65)
				{
					g211 = 3.616 - 13.2470 * rec.em + 16.2900 * rec.emsq;
					g310 = -19.302 + 117.3900 * rec.em - 228.4190 * rec.emsq + 156.5910 * eoc;
					g322 = -18.9068 + 109.7927 * rec.em - 214.6334 * rec.emsq + 146.5816 * eoc;
					g410 = -41.122 + 242.6940 * rec.em - 471.0940 * rec.emsq + 313.9530 * eoc;
					g422 = -146.407 + 841.8800 * rec.em - 1629.014 * rec.emsq + 1083.4350 * eoc;
					g520 = -532.114 + 3017.977 * rec.em - 5740.032 * rec.emsq + 3708.2760 * eoc;
				}
				else
				{
					g211 = -72.099 + 331.819 * rec.em - 508.738 * rec.emsq + 266.724 * eoc;
					g310 = -346.844 + 1582.851 * rec.em - 2415.925 * rec.emsq + 1246.113 * eoc;
					g322 = -342.585 + 1554.908 * rec.em - 2366.899 * rec.emsq + 1215.972 * eoc;
					g410 = -1052.797 + 4758.686 * rec.em - 7193.992 * rec.emsq + 3651.957 * eoc;
					g422 = -3581.690 + 16178.110 * rec.em - 24462.770 * rec.emsq + 12422.520 * eoc;
					if (rec.em > 0.715)
						g520 = -5149.66 + 29936.92 * rec.em - 54087.36 * rec.emsq + 31324.56 * eoc;
					else
						g520 = 1464.74 - 4664.75 * rec.em + 3763.64 * rec.emsq;
				}
				if (rec.em < 0.7)
				{
					g533 = -919.22770 + 4988.6100 * rec.em - 9064.7700 * rec.emsq + 5542.21  * eoc;
					g521 = -822.71072 + 4568.6173 * rec.em - 8491.4146 * rec.emsq + 5337.524 * eoc;
					g532 = -853.66600 + 4690.2500 * rec.em - 8624.7700 * rec.emsq + 5341.4  * eoc;
				}
				else
				{
					g533 = -37995.780 + 161616.52 * rec.em - 229838.20 * rec.emsq + 109377.94 * eoc;
					g521 = -51752.104 + 218913.95 * rec.em - 309468.16 * rec.emsq + 146349.42 * eoc;
					g532 = -40023.880 + 170470.89 * rec.em - 242699.48 * rec.emsq + 115605.82 * eoc;
				}

				sini2 = rec.sinim * rec.sinim;
				f220 = 0.75 * (1.0 + 2.0 * rec.cosim + cosisq);
				f221 = 1.5 * sini2;
				f321 = 1.875 * rec.sinim  *  (1.0 - 2.0 * rec.cosim - 3.0 * cosisq);
				f322 = -1.875 * rec.sinim  *  (1.0 + 2.0 * rec.cosim - 3.0 * cosisq);
				f441 = 35.0 * sini2 * f220;
				f442 = 39.3750 * sini2 * sini2;
				f522 = 9.84375 * rec.sinim * (sini2 * (1.0 - 2.0 * rec.cosim - 5.0 * cosisq) +
					0.33333333 * (-2.0 + 4.0 * rec.cosim + 6.0 * cosisq));
				f523 = rec.sinim * (4.92187512 * sini2 * (-2.0 - 4.0 * rec.cosim +
					10.0 * cosisq) + 6.56250012 * (1.0 + 2.0 * rec.cosim - 3.0 * cosisq));
				f542 = 29.53125 * rec.sinim * (2.0 - 8.0 * rec.cosim + cosisq *
					(-12.0 + 8.0 * rec.cosim + 10.0 * cosisq));
				f543 = 29.53125 * rec.sinim * (-2.0 - 8.0 * rec.cosim + cosisq *
					(12.0 + 8.0 * rec.cosim - 10.0 * cosisq));
				xno2 = rec.nm * rec.nm;
				ainv2 = aonv * aonv;
				temp1 = 3.0 * xno2 * ainv2;
				temp = temp1 * root22;
				rec.d2201 = temp * f220 * g201;
				rec.d2211 = temp * f221 * g211;
				temp1 = temp1 * aonv;
				temp = temp1 * root32;
				rec.d3210 = temp * f321 * g310;
				rec.d3222 = temp * f322 * g322;
				temp1 = temp1 * aonv;
				temp = 2.0 * temp1 * root44;
				rec.d4410 = temp * f441 * g410;
				rec.d4422 = temp * f442 * g422;
				temp1 = temp1 * aonv;
				temp = temp1 * root52;
				rec.d5220 = temp * f522 * g520;
				rec.d5232 = temp * f523 * g532;
				temp = 2.0 * temp1 * root54;
				rec.d5421 = temp * f542 * g521;
				rec.d5433 = temp * f543 * g533;
				rec.xlamo = fmod(rec.mo + rec.nodeo + rec.nodeo - theta - theta, twopi);
				rec.xfact = rec.mdot + rec.dmdt + 2.0 * (rec.nodedot + rec.dnodt - rptim) - rec.no_unkozai;
				rec.em = emo;
				rec.emsq = emsqo;
			}

			/* ---------------- synchronous resonance terms -------------- */
			if (rec.irez == 1)
			{
				g200 = 1.0 + rec.emsq * (-2.5 + 0.8125 * rec.emsq);
				g310 = 1.0 + 2.0 * rec.emsq;
				g300 = 1.0 + rec.emsq * (-6.0 + 6.60937 * rec.emsq);
				f220 = 0.75 * (1.0 + rec.cosim) * (1.0 + rec.cosim);
				f311 = 0.9375 * rec.sinim * rec.sinim * (1.0 + 3.0 * rec.cosim) - 0.75 * (1.0 + rec.cosim);
				f330 = 1.0 + rec.cosim;
				f330 = 1.875 * f330 * f330 * f330;
				rec.del1 = 3.0 * rec.nm * rec.nm * aonv * aonv;
				rec.del2 = 2.0 * rec.del1 * f220 * g200 * q22;
				rec.del3 = 3.0 * rec.del1 * f330 * g300 * q33 * aonv;
				rec.del1 = rec.del1 * f311 * g310 * q31 * aonv;
				rec.xlamo = fmod(rec.mo + rec.nodeo + rec.argpo - theta, twopi);
				rec.xfact = rec.mdot + xpidot - rptim + rec.dmdt + rec.domdt + rec.dnodt - rec.no_unkozai;
			}

			/* ------------ for sgp4, initialize the integrator ---------- */
			rec.xli = rec.xlamo;
			rec.xni = rec.no_unkozai;
			rec.atime = 0.0;
			rec.nm = rec.no_unkozai + rec.dndt;
		}

	}  // dsinit

	/*-----------------------------------------------------------------------------
	*
	*                           procedure dspace
	*
	*  this procedure provides deep space contributions to mean elements for
	*    perturbing third body.  these effects have been averaged over one
	*    revolution of the sun and moon.  for earth resonance effects, the
	*    effects have been averaged over no revolutions of the satellite.
	*    (mean motion)
	*
	*  author        : david vallado                  719-573-2600   28 jun 2005
	*
	*  inputs        :
	*    d2201, d2211, d3210, d3222, d4410, d4422, d5220, d5232, d5421, d5433 -
	*    dedt        -
	*    del1, del2, del3  -
	*    didt        -
	*    dmdt        -
	*    dnodt       -
	*    domdt       -
	*    irez        - flag for resonance           0-none, 1-one day, 2-half day
	*    argpo       - argument of perigee
	*    argpdot     - argument of perigee dot (rate)
	*    t           - time
	*    tc          -
	*    gsto        - gst
	*    xfact       -
	*    xlamo       -
	*    no          - mean motion
	*    atime       -
	*    em          - eccentricity
	*    ft          -
	*    argpm       - argument of perigee
	*    inclm       - inclination
	*    xli         -
	*    mm          - mean anomaly
	*    xni         - mean motion
	*    nodem       - right ascension of ascending node
	*
	*  outputs       :
	*    atime       -
	*    em          - eccentricity
	*    argpm       - argument of perigee
	*    inclm       - inclination
	*    xli         -
	*    mm          - mean anomaly
	*    xni         -
	*    nodem       - right ascension of ascending node
	*    dndt        -
	*    nm          - mean motion
	*
	*  locals        :
	*    delt        -
	*    ft          -
	*    theta       -
	*    x2li        -
	*    x2omi       -
	*    xl          -
	*    xldot       -
	*    xnddt       -
	*    xndt        -
	*    xomi        -
	*
	*  coupling      :
	*    none        -
	*
	*  references    :
	*    hoots, roehrich, norad spacetrack report #3 1980
	*    hoots, norad spacetrack report #6 1986
	*    hoots, schumacher and glover 2004
	*    vallado, crawford, hujsak, kelso  2006
	----------------------------------------------------------------------------*/

	public static void dspace(double tc, ElsetRec rec)
	{
		int iretn;
		double delt, ft, theta, x2li, x2omi, xl, xldot, xnddt, xndt, xomi, g22, g32,
			g44, g52, g54, fasx2, fasx4, fasx6, rptim, step2, stepn, stepp;
		
		xndt = 0;
		xnddt = 0;
		xldot = 0;
		
		fasx2 = 0.13130908;
		fasx4 = 2.8843198;
		fasx6 = 0.37448087;
		g22 = 5.7686396;
		g32 = 0.95240898;
		g44 = 1.8014998;
		g52 = 1.0508330;
		g54 = 4.4108898;
		rptim = 4.37526908801129966e-3; // this equates to 7.29211514668855e-5 rad/sec
		stepp = 720.0;
		stepn = -720.0;
		step2 = 259200.0;

		/* ----------- calculate deep space resonance effects ----------- */
		rec.dndt = 0.0;
		theta = fmod(rec.gsto + tc * rptim, twopi);
		rec.em = rec.em + rec.dedt * rec.t;

		rec.inclm = rec.inclm + rec.didt * rec.t;
		rec.argpm = rec.argpm + rec.domdt * rec.t;
		rec.nodem = rec.nodem + rec.dnodt * rec.t;
		rec.mm = rec.mm + rec.dmdt * rec.t;

		//   sgp4fix for negative inclinations
		//   the following if statement should be commented out
		//  if (inclm < 0.0)
		// {
		//    inclm = -inclm;
		//    argpm = argpm - pi;
		//    nodem = nodem + pi;
		//  }

		/* - update resonances : numerical (euler-maclaurin) integration - */
		/* ------------------------- epoch restart ----------------------  */
		//   sgp4fix for propagator problems
		//   the following integration works for negative time steps and periods
		//   the specific changes are unknown because the original code was so convoluted

		// sgp4fix take out atime = 0.0 and fix for faster operation
		ft = 0.0;
		if (rec.irez != 0)
		{
			// sgp4fix streamline check
			if ((rec.atime == 0.0) || (rec.t * rec.atime <= 0.0) || (Math.abs(rec.t) < Math.abs(rec.atime)))
			{
				rec.atime = 0.0;
				rec.xni = rec.no_unkozai;
				rec.xli = rec.xlamo;
			}
			// sgp4fix move check outside loop
			if (rec.t > 0.0)
				delt = stepp;
			else
				delt = stepn;

			iretn = 381; // added for do loop
			while (iretn == 381)
			{
				/* ------------------- dot terms calculated ------------- */
				/* ----------- near - synchronous resonance terms ------- */
				if (rec.irez != 2)
				{
					xndt = rec.del1 * Math.sin(rec.xli - fasx2) + rec.del2 * Math.sin(2.0 * (rec.xli - fasx4)) +
							rec.del3 * Math.sin(3.0 * (rec.xli - fasx6));
					xldot = rec.xni + rec.xfact;
					xnddt = rec.del1 * Math.cos(rec.xli - fasx2) +
						2.0 * rec.del2 * Math.cos(2.0 * (rec.xli - fasx4)) +
						3.0 * rec.del3 * Math.cos(3.0 * (rec.xli - fasx6));
					xnddt = xnddt * xldot;
				}
				else
				{
					/* --------- near - half-day resonance terms -------- */
					xomi = rec.argpo + rec.argpdot * rec.atime;
					x2omi = xomi + xomi;
					x2li = rec.xli + rec.xli;
					xndt = rec.d2201 * Math.sin(x2omi + rec.xli - g22) + rec.d2211 * Math.sin(rec.xli - g22) +
							rec.d3210 * Math.sin(xomi + rec.xli - g32) + rec.d3222 * Math.sin(-xomi + rec.xli - g32) +
							rec.d4410 * Math.sin(x2omi + x2li - g44) + rec.d4422 * Math.sin(x2li - g44) +
							rec.d5220 * Math.sin(xomi + rec.xli - g52) + rec.d5232 * Math.sin(-xomi + rec.xli - g52) +
							rec.d5421 * Math.sin(xomi + x2li - g54) + rec.d5433 * Math.sin(-xomi + x2li - g54);
					xldot = rec.xni + rec.xfact;
					xnddt = rec.d2201 * Math.cos(x2omi + rec.xli - g22) + rec.d2211 * Math.cos(rec.xli - g22) +
							rec.d3210 * Math.cos(xomi + rec.xli - g32) + rec.d3222 * Math.cos(-xomi + rec.xli - g32) +
							rec.d5220 * Math.cos(xomi + rec.xli - g52) + rec.d5232 * Math.cos(-xomi + rec.xli - g52) +
						2.0 * (rec.d4410 * Math.cos(x2omi + x2li - g44) +
								rec.d4422 * Math.cos(x2li - g44) + rec.d5421 * Math.cos(xomi + x2li - g54) +
								rec.d5433 * Math.cos(-xomi + x2li - g54));
					xnddt = xnddt * xldot;
				}

				/* ----------------------- integrator ------------------- */
				// sgp4fix move end checks to end of routine
				if (Math.abs(rec.t - rec.atime) >= stepp)
				{
					iretn = 381;
				}
				else // exit here
				{
					ft = rec.t - rec.atime;
					iretn = 0;
				}

				if (iretn == 381)
				{
					rec.xli = rec.xli + xldot * delt + xndt * step2;
					rec.xni = rec.xni + xndt * delt + xnddt * step2;
					rec.atime = rec.atime + delt;
				}
			}  // while iretn = 381

			
			rec.nm = rec.xni + xndt * ft + xnddt * ft * ft * 0.5;
			xl = rec.xli + xldot * ft + xndt * ft * ft * 0.5;
			if (rec.irez != 1)
			{
				rec.mm = xl - 2.0 * rec.nodem + 2.0 * theta;
				rec.dndt = rec.nm - rec.no_unkozai;
			}
			else
			{
				rec.mm = xl - rec.nodem - rec.argpm + theta;
				rec.dndt = rec.nm - rec.no_unkozai;
			}
			rec.nm = rec.no_unkozai + rec.dndt;
		}

	}  // dsspace

	/*-----------------------------------------------------------------------------
	*
	*                           procedure initl
	*
	*  this procedure initializes the spg4 propagator. all the initialization is
	*    consolidated here instead of having multiple loops inside other routines.
	*
	*  author        : david vallado                  719-573-2600   28 jun 2005
	*
	*  inputs        :
	*    satn        - satellite number - not needed, placed in satrec
	*    xke         - reciprocal of tumin
	*    j2          - j2 zonal harmonic
	*    ecco        - eccentricity                           0.0 - 1.0
	*    epoch       - epoch time in days from jan 0, 1950. 0 hr
	*    inclo       - inclination of satellite
	*    no          - mean motion of satellite
	*
	*  outputs       :
	*    ainv        - 1.0 / a
	*    ao          - semi major axis
	*    con41       -
	*    con42       - 1.0 - 5.0 cos(i)
	*    cosio       - cosine of inclination
	*    cosio2      - cosio squared
	*    eccsq       - eccentricity squared
	*    method      - flag for deep space                    'd', 'n'
	*    omeosq      - 1.0 - ecco * ecco
	*    posq        - semi-parameter squared
	*    rp          - radius of perigee
	*    rteosq      - square root of (1.0 - ecco*ecco)
	*    sinio       - sine of inclination
	*    gsto        - gst at time of observation               rad
	*    no          - mean motion of satellite
	*
	*  locals        :
	*    ak          -
	*    d1          -
	*    del         -
	*    adel        -
	*    po          -
	*
	*  coupling      :
	*    getgravconst- no longer used
	*    gstime      - find greenwich sidereal time from the julian date
	*
	*  references    :
	*    hoots, roehrich, norad spacetrack report #3 1980
	*    hoots, norad spacetrack report #6 1986
	*    hoots, schumacher and glover 2004
	*    vallado, crawford, hujsak, kelso  2006
	----------------------------------------------------------------------------*/

	public static void initl(double epoch, ElsetRec rec)
	{
		/* --------------------- local variables ------------------------ */
		double ak, d1, del, adel, po, x2o3;

		// sgp4fix use old way of finding gst
		double ds70;
		double ts70, tfrac, c1, thgr70, fk5r, c1p2p;
		
		/* ----------------------- earth constants ---------------------- */
		// sgp4fix identify constants and allow alternate values
		// only xke and j2 are used here so pass them in directly
		// getgravconst( whichconst, tumin, mu, radiusearthkm, xke, j2, j3, j4, j3oj2 );
		x2o3 = 2.0 / 3.0;

		/* ------------- calculate auxillary epoch quantities ---------- */
		rec.eccsq = rec.ecco * rec.ecco;
		rec.omeosq = 1.0 - rec.eccsq;
		rec.rteosq = Math.sqrt(rec.omeosq);
		rec.cosio = Math.cos(rec.inclo);
		rec.cosio2 = rec.cosio * rec.cosio;

		/* ------------------ un-kozai the mean motion ----------------- */
		ak = Math.pow(rec.xke / rec.no_kozai, x2o3);
		d1 = 0.75 * rec.j2 * (3.0 * rec.cosio2 - 1.0) / (rec.rteosq * rec.omeosq);
		del = d1 / (ak * ak);
		adel = ak * (1.0 - del * del - del *
			(1.0 / 3.0 + 134.0 * del * del / 81.0));
		del = d1 / (adel * adel);
		rec.no_unkozai = rec.no_kozai / (1.0 + del);

		rec.ao = Math.pow(rec.xke / (rec.no_unkozai), x2o3);
		rec.sinio = Math.sin(rec.inclo);
		po = rec.ao * rec.omeosq;
		rec.con42 = 1.0 - 5.0 * rec.cosio2;
		rec.con41 = -rec.con42 - rec.cosio2 - rec.cosio2;
		rec.ainv = 1.0 / rec.ao;
		rec.posq = po * po;
		rec.rp = rec.ao * (1.0 - rec.ecco);
		rec.method = 'n';

		// sgp4fix modern approach to finding sidereal time
		//   if (opsmode == 'a')
		//      {
		// sgp4fix use old way of finding gst
		// count integer number of days from 0 jan 1970
		ts70 = epoch - 7305.0;
		ds70 = Math.floor(ts70 + 1.0e-8);
		tfrac = ts70 - ds70;
		// find greenwich location at epoch
		c1 = 1.72027916940703639e-2;
		thgr70 = 1.7321343856509374;
		fk5r = 5.07551419432269442e-15;
		c1p2p = c1 + twopi;
		double gsto1 = fmod(thgr70 + c1*ds70 + c1p2p*tfrac + ts70*ts70*fk5r, twopi);
		if (gsto1 < 0.0)
			gsto1 = gsto1 + twopi;
		//    }
		//    else
		rec.gsto = gstime(epoch + 2433281.5);
	}  // initl

	/*-----------------------------------------------------------------------------
	*
	*                             procedure sgp4init
	*
	*  this procedure initializes variables for sgp4.
	*
	*  author        : david vallado                  719-573-2600   28 jun 2005
	*
	*  inputs        :
	*    opsmode     - mode of operation afspc or improved 'a', 'i'
	*    whichconst  - which set of constants to use  72, 84
	*    satn        - satellite number
	*    bstar       - sgp4 type drag coefficient              kg/m2er
	*    ecco        - eccentricity
	*    epoch       - epoch time in days from jan 0, 1950. 0 hr
	*    argpo       - argument of perigee (output if ds)
	*    inclo       - inclination
	*    mo          - mean anomaly (output if ds)
	*    no          - mean motion
	*    nodeo       - right ascension of ascending node
	*
	*  outputs       :
	*    satrec      - common values for subsequent calls
	*    return code - non-zero on error.
	*                   1 - mean elements, ecc >= 1.0 or ecc < -0.001 or a < 0.95 er
	*                   2 - mean motion less than 0.0
	*                   3 - pert elements, ecc < 0.0  or  ecc > 1.0
	*                   4 - semi-latus rectum < 0.0
	*                   5 - epoch elements are sub-orbital
	*                   6 - satellite has decayed
	*
	*  locals        :
	*    cnodm  , snodm  , cosim  , sinim  , cosomm , sinomm
	*    cc1sq  , cc2    , cc3
	*    coef   , coef1
	*    cosio4      -
	*    day         -
	*    dndt        -
	*    em          - eccentricity
	*    emsq        - eccentricity squared
	*    eeta        -
	*    etasq       -
	*    gam         -
	*    argpm       - argument of perigee
	*    nodem       -
	*    inclm       - inclination
	*    mm          - mean anomaly
	*    nm          - mean motion
	*    perige      - perigee
	*    pinvsq      -
	*    psisq       -
	*    qzms24      -
	*    rtemsq      -
	*    s1, s2, s3, s4, s5, s6, s7          -
	*    sfour       -
	*    ss1, ss2, ss3, ss4, ss5, ss6, ss7         -
	*    sz1, sz2, sz3
	*    sz11, sz12, sz13, sz21, sz22, sz23, sz31, sz32, sz33        -
	*    tc          -
	*    temp        -
	*    temp1, temp2, temp3       -
	*    tsi         -
	*    xpidot      -
	*    xhdot1      -
	*    z1, z2, z3          -
	*    z11, z12, z13, z21, z22, z23, z31, z32, z33         -
	*
	*  coupling      :
	*    getgravconst-
	*    initl       -
	*    dscom       -
	*    dpper       -
	*    dsinit      -
	*    sgp4        -
	*
	*  references    :
	*    hoots, roehrich, norad spacetrack report #3 1980
	*    hoots, norad spacetrack report #6 1986
	*    hoots, schumacher and glover 2004
	*    vallado, crawford, hujsak, kelso  2006
	----------------------------------------------------------------------------*/

	public static boolean sgp4init
		(
		char opsmode,ElsetRec satrec
		)
	{
		/* --------------------- local variables ------------------------ */
		
		double cc1sq,
			cc2, cc3, coef, coef1, cosio4,
			eeta, etasq, perige, pinvsq, psisq, qzms24,
            sfour,tc, temp, temp1, temp2, temp3, tsi, xpidot,
			xhdot1,qzms2t, ss, x2o3, r[], v[],
			delmotemp, qzms2ttemp, qzms24temp;
		
		               
		double epoch = (satrec.jdsatepoch + satrec.jdsatepochF) - 2433281.5;

		/* ------------------------ initialization --------------------- */
		// sgp4fix divisor for divide by zero check on inclination
		// the old check used 1.0 + cos(pi-1.0e-9), but then compared it to
		// 1.5 e-12, so the threshold was changed to 1.5e-12 for consistency
		final double temp4 = 1.5e-12;

		/* ----------- set all near earth variables to zero ------------ */
		satrec.isimp = 0;   satrec.method = 'n'; satrec.aycof = 0.0;
		satrec.con41 = 0.0; satrec.cc1 = 0.0; satrec.cc4 = 0.0;
		satrec.cc5 = 0.0; satrec.d2 = 0.0; satrec.d3 = 0.0;
		satrec.d4 = 0.0; satrec.delmo = 0.0; satrec.eta = 0.0;
		satrec.argpdot = 0.0; satrec.omgcof = 0.0; satrec.sinmao = 0.0;
		satrec.t = 0.0; satrec.t2cof = 0.0; satrec.t3cof = 0.0;
		satrec.t4cof = 0.0; satrec.t5cof = 0.0; satrec.x1mth2 = 0.0;
		satrec.x7thm1 = 0.0; satrec.mdot = 0.0; satrec.nodedot = 0.0;
		satrec.xlcof = 0.0; satrec.xmcof = 0.0; satrec.nodecf = 0.0;

		/* ----------- set all deep space variables to zero ------------ */
		satrec.irez = 0;   satrec.d2201 = 0.0; satrec.d2211 = 0.0;
		satrec.d3210 = 0.0; satrec.d3222 = 0.0; satrec.d4410 = 0.0;
		satrec.d4422 = 0.0; satrec.d5220 = 0.0; satrec.d5232 = 0.0;
		satrec.d5421 = 0.0; satrec.d5433 = 0.0; satrec.dedt = 0.0;
		satrec.del1 = 0.0; satrec.del2 = 0.0; satrec.del3 = 0.0;
		satrec.didt = 0.0; satrec.dmdt = 0.0; satrec.dnodt = 0.0;
		satrec.domdt = 0.0; satrec.e3 = 0.0; satrec.ee2 = 0.0;
		satrec.peo = 0.0; satrec.pgho = 0.0; satrec.pho = 0.0;
		satrec.pinco = 0.0; satrec.plo = 0.0; satrec.se2 = 0.0;
		satrec.se3 = 0.0; satrec.sgh2 = 0.0; satrec.sgh3 = 0.0;
		satrec.sgh4 = 0.0; satrec.sh2 = 0.0; satrec.sh3 = 0.0;
		satrec.si2 = 0.0; satrec.si3 = 0.0; satrec.sl2 = 0.0;
		satrec.sl3 = 0.0; satrec.sl4 = 0.0; satrec.gsto = 0.0;
		satrec.xfact = 0.0; satrec.xgh2 = 0.0; satrec.xgh3 = 0.0;
		satrec.xgh4 = 0.0; satrec.xh2 = 0.0; satrec.xh3 = 0.0;
		satrec.xi2 = 0.0; satrec.xi3 = 0.0; satrec.xl2 = 0.0;
		satrec.xl3 = 0.0; satrec.xl4 = 0.0; satrec.xlamo = 0.0;
		satrec.zmol = 0.0; satrec.zmos = 0.0; satrec.atime = 0.0;
		satrec.xli = 0.0; satrec.xni = 0.0;

		/* ------------------------ earth constants ----------------------- */
		// sgp4fix identify constants and allow alternate values
		// this is now the only call for the constants
		getgravconst(satrec.whichconst, satrec);

		//-------------------------------------------------------------------------

		satrec.error = 0;
		satrec.operationmode = opsmode;


		// single averaged mean elements
		satrec.am = satrec.em = satrec.im = satrec.Om = satrec.mm = satrec.nm = 0.0;

		/* ------------------------ earth constants ----------------------- */
		// sgp4fix identify constants and allow alternate values no longer needed
		// getgravconst( whichconst, tumin, mu, radiusearthkm, xke, j2, j3, j4, j3oj2 );
		ss = 78.0 / satrec.radiusearthkm + 1.0;
		// sgp4fix use multiply for speed instead of pow
		qzms2ttemp = (120.0 - 78.0) / satrec.radiusearthkm;
		qzms2t = qzms2ttemp * qzms2ttemp * qzms2ttemp * qzms2ttemp;
		x2o3 = 2.0 / 3.0;

		satrec.init = 'y';
		satrec.t = 0.0;

		// sgp4fix remove satn as it is not needed in initl
		
		initl(epoch,satrec);
		
		satrec.a = Math.pow(satrec.no_unkozai * satrec.tumin, (-2.0 / 3.0));
		satrec.alta = satrec.a * (1.0 + satrec.ecco) - 1.0;
		satrec.altp = satrec.a * (1.0 - satrec.ecco) - 1.0;
		satrec.error = 0;

		// sgp4fix remove this check as it is unnecessary
		// the mrt check in sgp4 handles decaying satellite cases even if the starting
		// condition is below the surface of te earth
		//     if (rp < 1.0)
		//       {
		//         satrec.error = 5;
		//       }

		if ((satrec.omeosq >= 0.0) || (satrec.no_unkozai >= 0.0))
		{
			satrec.isimp = 0;
			if (satrec.rp < (220.0 / satrec.radiusearthkm + 1.0))
				satrec.isimp = 1;
			sfour = ss;
			qzms24 = qzms2t;
			perige = (satrec.rp - 1.0) * satrec.radiusearthkm;

			/* - for perigees below 156 km, s and qoms2t are altered - */
			if (perige < 156.0)
			{
				sfour = perige - 78.0;
				if (perige < 98.0)
					sfour = 20.0;
				// sgp4fix use multiply for speed instead of pow
				qzms24temp = (120.0 - sfour) / satrec.radiusearthkm;
				qzms24 = qzms24temp * qzms24temp * qzms24temp * qzms24temp;
				sfour = sfour / satrec.radiusearthkm + 1.0;
			}
			pinvsq = 1.0 / satrec.posq;

			tsi = 1.0 / (satrec.ao - sfour);
			satrec.eta = satrec.ao * satrec.ecco * tsi;
			etasq = satrec.eta * satrec.eta;
			eeta = satrec.ecco * satrec.eta;
			psisq = Math.abs(1.0 - etasq);
			coef = qzms24 * Math.pow(tsi, 4.0);
			coef1 = coef / Math.pow(psisq, 3.5);
			cc2 = coef1 * satrec.no_unkozai * (satrec.ao * (1.0 + 1.5 * etasq + eeta *
				(4.0 + etasq)) + 0.375 * satrec.j2 * tsi / psisq * satrec.con41 *
				(8.0 + 3.0 * etasq * (8.0 + etasq)));
			satrec.cc1 = satrec.bstar * cc2;
			cc3 = 0.0;
			if (satrec.ecco > 1.0e-4)
				cc3 = -2.0 * coef * tsi * satrec.j3oj2 * satrec.no_unkozai * satrec.sinio / satrec.ecco;
			satrec.x1mth2 = 1.0 - satrec.cosio2;
			satrec.cc4 = 2.0* satrec.no_unkozai * coef1 * satrec.ao * satrec.omeosq *
				(satrec.eta * (2.0 + 0.5 * etasq) + satrec.ecco *
				(0.5 + 2.0 * etasq) - satrec.j2 * tsi / (satrec.ao * psisq) *
				(-3.0 * satrec.con41 * (1.0 - 2.0 * eeta + etasq *
				(1.5 - 0.5 * eeta)) + 0.75 * satrec.x1mth2 *
				(2.0 * etasq - eeta * (1.0 + etasq)) * Math.cos(2.0 * satrec.argpo)));
			satrec.cc5 = 2.0 * coef1 * satrec.ao * satrec.omeosq * (1.0 + 2.75 *
				(etasq + eeta) + eeta * etasq);
			cosio4 = satrec.cosio2 * satrec.cosio2;
			temp1 = 1.5 * satrec.j2 * pinvsq * satrec.no_unkozai;
			temp2 = 0.5 * temp1 * satrec.j2 * pinvsq;
			temp3 = -0.46875 * satrec.j4 * pinvsq * pinvsq * satrec.no_unkozai;
			satrec.mdot = satrec.no_unkozai + 0.5 * temp1 * satrec.rteosq * satrec.con41 + 0.0625 *
				temp2 * satrec.rteosq * (13.0 - 78.0 * satrec.cosio2 + 137.0 * cosio4);
			satrec.argpdot = -0.5 * temp1 * satrec.con42 + 0.0625 * temp2 *
				(7.0 - 114.0 * satrec.cosio2 + 395.0 * cosio4) +
				temp3 * (3.0 - 36.0 * satrec.cosio2 + 49.0 * cosio4);
			xhdot1 = -temp1 * satrec.cosio;
			satrec.nodedot = xhdot1 + (0.5 * temp2 * (4.0 - 19.0 * satrec.cosio2) +
				2.0 * temp3 * (3.0 - 7.0 * satrec.cosio2)) * satrec.cosio;
			xpidot = satrec.argpdot + satrec.nodedot;
			satrec.omgcof = satrec.bstar * cc3 * Math.cos(satrec.argpo);
			satrec.xmcof = 0.0;
			if (satrec.ecco > 1.0e-4)
				satrec.xmcof = -x2o3 * coef * satrec.bstar / eeta;
			satrec.nodecf = 3.5 * satrec.omeosq * xhdot1 * satrec.cc1;
			satrec.t2cof = 1.5 * satrec.cc1;
			// sgp4fix for divide by zero with xinco = 180 deg
			if (Math.abs(satrec.cosio + 1.0) > 1.5e-12)
				satrec.xlcof = -0.25 * satrec.j3oj2 * satrec.sinio * (3.0 + 5.0 * satrec.cosio) / (1.0 + satrec.cosio);
			else
				satrec.xlcof = -0.25 * satrec.j3oj2 * satrec.sinio * (3.0 + 5.0 * satrec.cosio) / temp4;
			satrec.aycof = -0.5 * satrec.j3oj2 * satrec.sinio;
			// sgp4fix use multiply for speed instead of pow
			delmotemp = 1.0 + satrec.eta * Math.cos(satrec.mo);
			satrec.delmo = delmotemp * delmotemp * delmotemp;
			satrec.sinmao = Math.sin(satrec.mo);
			satrec.x7thm1 = 7.0 * satrec.cosio2 - 1.0;

			/* --------------- deep space initialization ------------- */
			if ((2 * pi / satrec.no_unkozai) >= 225.0)
			{
				satrec.method = 'd';
				satrec.isimp = 1;
				tc = 0.0;
				satrec.inclm = satrec.inclo;

                dscom(epoch, satrec.ecco, satrec.argpo, tc, satrec.inclo, satrec.nodeo, satrec.no_unkozai,satrec);				
                
				satrec.ep=satrec.ecco;
				satrec.inclp=satrec.inclo;
				satrec.nodep=satrec.nodeo;
				satrec.argpp=satrec.argpo;
				satrec.mp=satrec.mo;

                
				dpper(satrec.e3, satrec.ee2, satrec.peo, satrec.pgho,
					satrec.pho, satrec.pinco, satrec.plo, satrec.se2,
					satrec.se3, satrec.sgh2, satrec.sgh3, satrec.sgh4,
					satrec.sh2, satrec.sh3, satrec.si2, satrec.si3,
					satrec.sl2, satrec.sl3, satrec.sl4, satrec.t,
					satrec.xgh2, satrec.xgh3, satrec.xgh4, satrec.xh2,
					satrec.xh3, satrec.xi2, satrec.xi3, satrec.xl2,
					satrec.xl3, satrec.xl4, satrec.zmol, satrec.zmos, satrec.init,satrec,
					satrec.operationmode);


				satrec.ecco=satrec.ep;
				satrec.inclo=satrec.inclp;
				satrec.nodeo=satrec.nodep;
				satrec.argpo=satrec.argpp;
				satrec.mo=satrec.mp;

				satrec.argpm = 0.0;
				satrec.nodem = 0.0;
				satrec.mm = 0.0;
				
				dsinit(tc, xpidot, satrec);
			}

			/* ----------- set variables if not deep space ----------- */
			if (satrec.isimp != 1)
			{
				cc1sq = satrec.cc1 * satrec.cc1;
				satrec.d2 = 4.0 * satrec.ao * tsi * cc1sq;
				temp = satrec.d2 * tsi * satrec.cc1 / 3.0;
				satrec.d3 = (17.0 * satrec.ao + sfour) * temp;
				satrec.d4 = 0.5 * temp * satrec.ao * tsi * (221.0 * satrec.ao + 31.0 * sfour) * satrec.cc1;
				satrec.t3cof = satrec.d2 + 2.0 * cc1sq;
				satrec.t4cof = 0.25 * (3.0 * satrec.d3 + satrec.cc1 *
					(12.0 * satrec.d2 + 10.0 * cc1sq));
				satrec.t5cof = 0.2 * (3.0 * satrec.d4 +
					12.0 * satrec.cc1 * satrec.d3 +
					6.0 * satrec.d2 * satrec.d2 +
					15.0 * cc1sq * (2.0 * satrec.d2 + cc1sq));
			}
		} // if omeosq = 0 ...

		/* finally propogate to zero epoch to initialize all others. */
		// sgp4fix take out check to let satellites process until they are actually below earth surface
		//       if(satrec.error == 0)
		
		r = new double[3];
		v = new double[3];

		
		sgp4(satrec, 0.0, r, v);

		satrec.init = 'n';

		//sgp4fix return boolean. satrec.error contains any error codes
		return true;
	}  // sgp4init

	/*-----------------------------------------------------------------------------
	*
	*                             procedure sgp4
	*
	*  this procedure is the sgp4 prediction model from space command. this is an
	*    updated and combined version of sgp4 and sdp4, which were originally
	*    published separately in spacetrack report #3. this version follows the
	*    methodology from the aiaa paper (2006) describing the history and
	*    development of the code.
	*
	*  author        : david vallado                  719-573-2600   28 jun 2005
	*
	*  inputs        :
	*    satrec	 - initialised structure from sgp4init() call.
	*    tsince	 - time since epoch (minutes)
	*
	*  outputs       :
	*    r           - position vector                     km
	*    v           - velocity                            km/sec
	*  return code - non-zero on error.
	*                   1 - mean elements, ecc >= 1.0 or ecc < -0.001 or a < 0.95 er
	*                   2 - mean motion less than 0.0
	*                   3 - pert elements, ecc < 0.0  or  ecc > 1.0
	*                   4 - semi-latus rectum < 0.0
	*                   5 - epoch elements are sub-orbital
	*                   6 - satellite has decayed
	*
	*  locals        :
	*    am          -
	*    axnl, aynl        -
	*    betal       -
	*    cosim   , sinim   , cosomm  , sinomm  , cnod    , snod    , cos2u   ,
	*    sin2u   , coseo1  , sineo1  , cosi    , sini    , cosip   , sinip   ,
	*    cosisq  , cossu   , sinsu   , cosu    , sinu
	*    delm        -
	*    delomg      -
	*    dndt        -
	*    eccm        -
	*    emsq        -
	*    ecose       -
	*    el2         -
	*    eo1         -
	*    eccp        -
	*    esine       -
	*    argpm       -
	*    argpp       -
	*    omgadf      -c
	*    pl          -
	*    r           -
	*    rtemsq      -
	*    rdotl       -
	*    rl          -
	*    rvdot       -
	*    rvdotl      -
	*    su          -
	*    t2  , t3   , t4    , tc
	*    tem5, temp , temp1 , temp2  , tempa  , tempe  , templ
	*    u   , ux   , uy    , uz     , vx     , vy     , vz
	*    inclm       - inclination
	*    mm          - mean anomaly
	*    nm          - mean motion
	*    nodem       - right asc of ascending node
	*    xinc        -
	*    xincp       -
	*    xl          -
	*    xlm         -
	*    mp          -
	*    xmdf        -
	*    xmx         -
	*    xmy         -
	*    nodedf      -
	*    xnode       -
	*    nodep       -
	*    np          -
	*
	*  coupling      :
	*    getgravconst- no longer used. Variables are conatined within satrec
	*    dpper
	*    dpspace
	*
	*  references    :
	*    hoots, roehrich, norad spacetrack report #3 1980
	*    hoots, norad spacetrack report #6 1986
	*    hoots, schumacher and glover 2004
	*    vallado, crawford, hujsak, kelso  2006
	----------------------------------------------------------------------------*/

	public static boolean sgp4
		(
		ElsetRec satrec, double tsince,
		double r[], double v[]
		)
	{
		
		double axnl, aynl, betal, cnod,
			cos2u, coseo1, cosi, cosip, cosisq, cossu, cosu,
			delm, delomg, ecose, el2, eo1,
			esine, argpdf, pl, mrt = 0.0,
			mvt, rdotl, rl, rvdot, rvdotl,
			sin2u, sineo1, sini, sinip, sinsu, sinu,
			snod, su, t2, t3, t4, tem5, temp,
			temp1, temp2, tempa, tempe, templ, u, ux,
			uy, uz, vx, vy, vz,
			xinc, xincp, xl, xlm,
			xmdf, xmx, xmy, nodedf, xnode, tc,
			x2o3, vkmpersec, delmtemp;
		
		int ktr;

		/* ------------------ set mathematical constants --------------- */
		// sgp4fix divisor for divide by zero check on inclination
		// the old check used 1.0 + cos(pi-1.0e-9), but then compared it to
		// 1.5 e-12, so the threshold was changed to 1.5e-12 for consistency
		final double temp4 = 1.5e-12;
		x2o3 = 2.0 / 3.0;
		// sgp4fix identify constants and allow alternate values
		// getgravconst( whichconst, tumin, mu, radiusearthkm, xke, j2, j3, j4, j3oj2 );
		vkmpersec = satrec.radiusearthkm * satrec.xke / 60.0;

		/* --------------------- clear sgp4 error flag ----------------- */
		satrec.t = tsince;
		satrec.error = 0;

		/* ------- update for secular gravity and atmospheric drag ----- */
		xmdf = satrec.mo + satrec.mdot * satrec.t;
		argpdf = satrec.argpo + satrec.argpdot * satrec.t;
		nodedf = satrec.nodeo + satrec.nodedot * satrec.t;
		satrec.argpm = argpdf;
		satrec.mm = xmdf;
		t2 = satrec.t * satrec.t;
		satrec.nodem = nodedf + satrec.nodecf * t2;
		tempa = 1.0 - satrec.cc1 * satrec.t;
		tempe = satrec.bstar * satrec.cc4 * satrec.t;
		templ = satrec.t2cof * t2;

		delomg = 0;
		delmtemp = 0;
		delm = 0;
		temp = 0;
		t3 = 0;
		t4 = 0;
		mrt = 0;
		
		if (satrec.isimp != 1)
		{
			delomg = satrec.omgcof * satrec.t;
			// sgp4fix use mutliply for speed instead of pow
			delmtemp = 1.0 + satrec.eta * Math.cos(xmdf);
			delm = satrec.xmcof *
				(delmtemp * delmtemp * delmtemp -
				satrec.delmo);
			temp = delomg + delm;
			satrec.mm = xmdf + temp;
			satrec.argpm = argpdf - temp;
			t3 = t2 * satrec.t;
			t4 = t3 * satrec.t;
			tempa = tempa - satrec.d2 * t2 - satrec.d3 * t3 -
				satrec.d4 * t4;
			tempe = tempe + satrec.bstar * satrec.cc5 * (Math.sin(satrec.mm) -satrec.sinmao);
			templ = templ + satrec.t3cof * t3 + t4 * (satrec.t4cof + satrec.t * satrec.t5cof);
		}

		tc = 0;
		satrec.nm = satrec.no_unkozai;
		satrec.em = satrec.ecco;
		satrec.inclm = satrec.inclo;
		if (satrec.method == 'd')
		{
			tc = satrec.t;
			dspace(tc,satrec);		
		} // if method = d

		if (satrec.nm <= 0.0)
		{
			satrec.error = 2;
			// sgp4fix add return
			return false;
		}
		
		satrec.am = Math.pow((satrec.xke / satrec.nm), x2o3) * tempa * tempa;
		satrec.nm = satrec.xke / Math.pow(satrec.am, 1.5);
		satrec.em = satrec.em - tempe;
		// fix tolerance for error recognition
		// sgp4fix am is fixed from the previous nm check
		if ((satrec.em >= 1.0) || (satrec.em < -0.001)/* || (am < 0.95)*/)
		{
			satrec.error = 1;
			// sgp4fix to return if there is an error in eccentricity
			return false;
		}
		// sgp4fix fix tolerance to avoid a divide by zero
		if (satrec.em < 1.0e-6)
			satrec.em = 1.0e-6;
		satrec.mm = satrec.mm + satrec.no_unkozai * templ;
		xlm = satrec.mm + satrec.argpm + satrec.nodem;
		satrec.emsq = satrec.em * satrec.em;
		temp = 1.0 - satrec.emsq;

		satrec.nodem = fmod(satrec.nodem, twopi);
		satrec.argpm = fmod(satrec.argpm, twopi);
		xlm = fmod(xlm, twopi);
		satrec.mm = fmod(xlm - satrec.argpm - satrec.nodem, twopi);

		// sgp4fix recover singly averaged mean elements
		satrec.am = satrec.am;
		satrec.em = satrec.em;
		satrec.im = satrec.inclm;
		satrec.Om = satrec.nodem;
		satrec.om = satrec.argpm;
		satrec.mm = satrec.mm;
		satrec.nm = satrec.nm;
		
		/* ----------------- compute extra mean quantities ------------- */
		satrec.sinim = Math.sin(satrec.inclm);
		satrec.cosim = Math.cos(satrec.inclm);

		/* -------------------- add lunar-solar periodics -------------- */
		satrec.ep = satrec.em;
		xincp = satrec.inclm;
		satrec.inclp = satrec.inclm;
		satrec.argpp = satrec.argpm;
		satrec.nodep = satrec.nodem;
		satrec.mp = satrec.mm;
		sinip = satrec.sinim;
		cosip = satrec.cosim;
				
		if (satrec.method == 'd')
		{
			dpper(satrec.e3, satrec.ee2, satrec.peo, satrec.pgho,
					satrec.pho, satrec.pinco, satrec.plo, satrec.se2,
					satrec.se3, satrec.sgh2, satrec.sgh3, satrec.sgh4,
					satrec.sh2, satrec.sh3, satrec.si2, satrec.si3,
					satrec.sl2, satrec.sl3, satrec.sl4, satrec.t,
					satrec.xgh2, satrec.xgh3, satrec.xgh4, satrec.xh2,
					satrec.xh3, satrec.xi2, satrec.xi3, satrec.xl2,
					satrec.xl3, satrec.xl4, satrec.zmol, satrec.zmos, 
					'n', satrec, satrec.operationmode);
			
				xincp = satrec.inclp;
			if (xincp < 0.0)
			{
				xincp = -xincp;
				satrec.nodep = satrec.nodep + pi;
				satrec.argpp = satrec.argpp - pi;
			}
			if ((satrec.ep < 0.0) || (satrec.ep > 1.0))
			{
				satrec.error = 3;
				// sgp4fix add return
				return false;
			}
		} // if method = d

		/* -------------------- long period periodics ------------------ */
		if (satrec.method == 'd')
		{
			sinip = Math.sin(xincp);
			cosip = Math.cos(xincp);
			satrec.aycof = -0.5*satrec.j3oj2*sinip;
			// sgp4fix for divide by zero for xincp = 180 deg
			if (Math.abs(cosip + 1.0) > 1.5e-12)
				satrec.xlcof = -0.25 * satrec.j3oj2 * sinip * (3.0 + 5.0 * cosip) / (1.0 + cosip);
			else
				satrec.xlcof = -0.25 * satrec.j3oj2 * sinip * (3.0 + 5.0 * cosip) / temp4;
		}
		axnl = satrec.ep * Math.cos(satrec.argpp);
		temp = 1.0 / (satrec.am * (1.0 - satrec.ep * satrec.ep));
		aynl = satrec.ep* Math.sin(satrec.argpp) + temp * satrec.aycof;
		xl = satrec.mp + satrec.argpp + satrec.nodep + temp * satrec.xlcof * axnl;

		/* --------------------- solve kepler's equation --------------- */
		u = fmod(xl - satrec.nodep, twopi);
		eo1 = u;
		tem5 = 9999.9;
		ktr = 1;
		sineo1 = 0;
		coseo1 = 0;
		//   sgp4fix for kepler iteration
		//   the following iteration needs better limits on corrections
		while ((Math.abs(tem5) >= 1.0e-12) && (ktr <= 10))
		{
			sineo1 = Math.sin(eo1);
			coseo1 = Math.cos(eo1);
			tem5 = 1.0 - coseo1 * axnl - sineo1 * aynl;
			tem5 = (u - aynl * coseo1 + axnl * sineo1 - eo1) / tem5;
			if (Math.abs(tem5) >= 0.95)
				tem5 = tem5 > 0.0 ? 0.95 : -0.95;
			eo1 = eo1 + tem5;
			ktr = ktr + 1;
		}

		/* ------------- short period preliminary quantities ----------- */
		ecose = axnl*coseo1 + aynl*sineo1;
		esine = axnl*sineo1 - aynl*coseo1;
		el2 = axnl*axnl + aynl*aynl;
		pl = satrec.am*(1.0 - el2);
		if (pl < 0.0)
		{
			satrec.error = 4;
			// sgp4fix add return
			return false;
		}
		else
		{
			rl = satrec.am * (1.0 - ecose);
			rdotl = Math.sqrt(satrec.am) * esine / rl;
			rvdotl = Math.sqrt(pl) / rl;
			betal = Math.sqrt(1.0 - el2);
			temp = esine / (1.0 + betal);
			sinu = satrec.am / rl * (sineo1 - aynl - axnl * temp);
			cosu = satrec.am / rl * (coseo1 - axnl + aynl * temp);
			su = Math.atan2(sinu, cosu);
			sin2u = (cosu + cosu) * sinu;
			cos2u = 1.0 - 2.0 * sinu * sinu;
			temp = 1.0 / pl;
			temp1 = 0.5 * satrec.j2 * temp;
			temp2 = temp1 * temp;

			/* -------------- update for short period periodics ------------ */
			if (satrec.method == 'd')
			{
				cosisq = cosip * cosip;
				satrec.con41 = 3.0*cosisq - 1.0;
				satrec.x1mth2 = 1.0 - cosisq;
				satrec.x7thm1 = 7.0*cosisq - 1.0;
			}
			mrt = rl * (1.0 - 1.5 * temp2 * betal * satrec.con41) +
				0.5 * temp1 * satrec.x1mth2 * cos2u;
			su = su - 0.25 * temp2 * satrec.x7thm1 * sin2u;
			xnode = satrec.nodep + 1.5 * temp2 * cosip * sin2u;
			xinc = xincp + 1.5 * temp2 * cosip * sinip * cos2u;
			mvt = rdotl - satrec.nm * temp1 * satrec.x1mth2 * sin2u / satrec.xke;
			rvdot = rvdotl + satrec.nm * temp1 * (satrec.x1mth2 * cos2u +
				1.5 * satrec.con41) / satrec.xke;

			/* --------------------- orientation vectors ------------------- */
			sinsu = Math.sin(su);
			cossu = Math.cos(su);
			snod = Math.sin(xnode);
			cnod = Math.cos(xnode);
			sini = Math.sin(xinc);
			cosi = Math.cos(xinc);
			xmx = -snod * cosi;
			xmy = cnod * cosi;
			ux = xmx * sinsu + cnod * cossu;
			uy = xmy * sinsu + snod * cossu;
			uz = sini * sinsu;
			vx = xmx * cossu - cnod * sinsu;
			vy = xmy * cossu - snod * sinsu;
			vz = sini * cossu;

			/* --------- position and velocity (in km and km/sec) ---------- */
			r[0] = (mrt * ux)* satrec.radiusearthkm;
			r[1] = (mrt * uy)* satrec.radiusearthkm;
			r[2] = (mrt * uz)* satrec.radiusearthkm;
			v[0] = (mvt * ux + rvdot * vx) * vkmpersec;
			v[1] = (mvt * uy + rvdot * vy) * vkmpersec;
			v[2] = (mvt * uz + rvdot * vz) * vkmpersec;
		}  // if pl > 0

		// sgp4fix for decaying satellites
		if (mrt < 1.0)
		{
			satrec.error = 6;
			return false;
		}

		return true;
	}  // sgp4





	/* -----------------------------------------------------------------------------
	*
	*                           function getgravconst
	*
	*  this function gets constants for the propagator. note that mu is identified to
	*    facilitiate comparisons with newer models. the common useage is wgs72.
	*
	*  author        : david vallado                  719-573-2600   21 jul 2006
	*
	*  inputs        :
	*    whichconst  - which set of constants to use  wgs72old, wgs72, wgs84
	*
	*  outputs       :
	*    tumin       - minutes in one time unit
	*    mu          - earth gravitational parameter
	*    radiusearthkm - radius of the earth in km
	*    xke         - reciprocal of tumin
	*    j2, j3, j4  - un-normalized zonal harmonic values
	*    j3oj2       - j3 divided by j2
	*
	*  locals        :
	*
	*  coupling      :
	*    none
	*
	*  references    :
	*    norad spacetrack report #3
	*    vallado, crawford, hujsak, kelso  2006
	--------------------------------------------------------------------------- */

	public static void getgravconst(int whichconst, ElsetRec rec)
	{
		rec.whichconst = whichconst;
		switch (whichconst)
		{
			// -- wgs-72 low precision str#3 constants --
		case wgs72old:
			rec.mu = 398600.79964;        // in km3 / s2
			rec.radiusearthkm = 6378.135;     // km
			rec.xke = 0.0743669161;        // reciprocal of tumin
			rec.tumin = 1.0 / rec.xke;
			rec.j2 = 0.001082616;
			rec.j3 = -0.00000253881;
			rec.j4 = -0.00000165597;
			rec.j3oj2 = rec.j3 / rec.j2;
			break;
			// ------------ wgs-72 constants ------------
		case wgs72:
			rec.mu = 398600.8;            // in km3 / s2
			rec.radiusearthkm = 6378.135;     // km
			rec.xke = 60.0 / Math.sqrt(rec.radiusearthkm*rec.radiusearthkm*rec.radiusearthkm / rec.mu);
			rec.tumin = 1.0 / rec.xke;
			rec.j2 = 0.001082616;
			rec.j3 = -0.00000253881;
			rec.j4 = -0.00000165597;
			rec.j3oj2 = rec.j3 / rec.j2;
			break;
		default:
		case wgs84:
			// ------------ wgs-84 constants ------------
			rec.mu = 398600.5;            // in km3 / s2
			rec.radiusearthkm = 6378.137;     // km
			rec.xke = 60.0 / Math.sqrt(rec.radiusearthkm*rec.radiusearthkm*rec.radiusearthkm / rec.mu);
			rec.tumin = 1.0 / rec.xke;
			rec.j2 = 0.00108262998905;
			rec.j3 = -0.00000253215306;
			rec.j4 = -0.00000161098761;
			rec.j3oj2 = rec.j3 / rec.j2;
			break;
		}

	}   // getgravconst

	
	protected static double fmod(double numer, double denom)
	{
		long tquot = (long)Math.floor(numer/denom);
		return numer-tquot*denom;
	}
	
	/* -----------------------------------------------------------------------------
	*
	*                           function gstime
	*
	*  this function finds the greenwich sidereal time.
	*
	*  author        : david vallado                  719-573-2600    1 mar 2001
	*
	*  inputs          description                    range / units
	*    jdut1       - julian date in ut1             days from 4713 bc
	*
	*  outputs       :
	*    gstime      - greenwich sidereal time        0 to 2pi rad
	*
	*  locals        :
	*    temp        - temporary variable for doubles   rad
	*    tut1        - julian centuries from the
	*                  jan 1, 2000 12 h epoch (ut1)
	*
	*  coupling      :
	*    none
	*
	*  references    :
	*    vallado       2013, 187, eq 3-45
	* --------------------------------------------------------------------------- */

	public static double  gstime(double jdut1)
	{
		double       temp, tut1;

		tut1 = (jdut1 - 2451545.0) / 36525.0;
		temp = -6.2e-6* tut1 * tut1 * tut1 + 0.093104 * tut1 * tut1 +
			(876600.0 * 3600 + 8640184.812866) * tut1 + 67310.54841;  // sec
		temp = fmod(temp * deg2rad / 240.0, twopi); //360/86400 = 1/240, to deg, to rad

		// ------------------------ check quadrants ---------------------
		if (temp < 0.0)
			temp += twopi;

		return temp;
	}  // gstime
	
	/* -----------------------------------------------------------------------------
	*
	*                           procedure jday
	*
	*  this procedure finds the julian date given the year, month, day, and time.
	*    the julian date is defined by each elapsed day since noon, jan 1, 4713 bc.
	*
	*  algorithm     : calculate the answer in one step for efficiency
	*
	*  author        : david vallado                  719-573-2600    1 mar 2001
	*
	*  inputs          description                    range / units
	*    year        - year                           1900 .. 2100
	*    mon         - month                          1 .. 12
	*    day         - day                            1 .. 28,29,30,31
	*    hr          - universal time hour            0 .. 23
	*    min         - universal time min             0 .. 59
	*    sec         - universal time sec             0.0 .. 59.999
	*
	*  outputs       :
	*    jd          - julian date                    days from 4713 bc
	*    jdfrac      - julian date fraction into day  days from 4713 bc
	*
	*  locals        :
	*    none.
	*
	*  coupling      :
	*    none.
	*
	*  references    :
	*    vallado       2013, 183, alg 14, ex 3-4
	* --------------------------------------------------------------------------- */

	public static double[] jday(int year, int mon, int day, int hr, int minute, double sec)
	{
		double jd = 0;
		double jdFrac = 0;

		jd = 367.0 * year -
			Math.floor((7 * (year + Math.floor((mon + 9) / 12.0))) * 0.25) +
			Math.floor(275 * mon / 9.0) +
			day + 1721013.5;  // use - 678987.0 to go to mjd directly
		jdFrac = (sec + minute * 60.0 + hr * 3600.0) / 86400.0;

		// check that the day and fractional day are correct
		if (Math.abs(jdFrac) > 1.0)
		{
			double dtt = Math.floor(jdFrac);
			jd = jd + dtt;
			jdFrac = jdFrac - dtt;
		}

		// - 0.5*sgn(100.0*year + mon - 190002.5) + 0.5;
		return new double[]{jd,jdFrac};
	}  // jday
}
