//! SGP4 constructor.
/*!
\param tle Two Line Elements
\param int GravConst 0 = WGS72, 1 = WGS82
initializes the Orbit-Calculation model
*/
public Sgp4(Tle data, int wgsConstant)
{
setGrav(wgsConstant);
tleElementData = data;
satCalcData = new Sgp4Rec();
resultOrbitData = new List<Sgp4Data>();
//Load TLE Data in sg4Rec Class for calculation
satCalcData.rec_satnum = data.getSatNumber();
satCalcData.rec_epochyr = data.getEpochYear();
satCalcData.rec_epochdays = data.getEpochDay();
satCalcData.rec_bstar = data.getDrag();
satCalcData.rec_inclo = data.getInclination();
satCalcData.rec_omegao = data.getRightAscendingNode();
satCalcData.rec_ecco = data.getEccentriciy();
satCalcData.rec_argpo = data.getPerigee();
satCalcData.rec_mo = data.getMeanAnomoly();
satCalcData.rec_no = data.getMeanMotion();
satCalcData.rec_no = satCalcData.rec_no / xpdotp;
satCalcData.rec_a = Math.Pow(satCalcData.rec_no * tumin, (-2.0 / 3.0));
satCalcData.rec_ndot = satCalcData.rec_ndot / (xpdotp * 1440.0);
satCalcData.rec_nddot = satCalcData.rec_nddot / (xpdotp * 1440.0 * 1440);
satCalcData.rec_inclo = satCalcData.rec_inclo / rad;
satCalcData.rec_omegao = satCalcData.rec_omegao / rad;
satCalcData.rec_argpo = satCalcData.rec_argpo / rad;
satCalcData.rec_mo = satCalcData.rec_mo / rad;
//Initalize newton rhapson iteration
newtonm(satCalcData.rec_ecco, satCalcData.rec_mo, e1, nuo);
satCalcData.rec_alta = satCalcData.rec_a *
(1.0 + satCalcData.rec_ecco * satCalcData.rec_ecco) - 1.0;
satCalcData.rec_altp = satCalcData.rec_a *
(1.0 - satCalcData.rec_ecco * satCalcData.rec_ecco) - 1.0;
//check Yeahr to find the the right Date
//Currently will only work until 2058
//Currently oldest man made object Vangard1 Launched 1958
if (satCalcData.rec_epochyr < 58)
year = satCalcData.rec_epochyr + 2000;
else
year = satCalcData.rec_epochyr + 1900;
// Epoch time
satCalcData.rec_eptime = (year - 1950) * 365 + (year - 1949) / 4
+ satCalcData.rec_epochdays;
EpochTime satTime = new EpochTime(satCalcData.rec_epochyr,
satCalcData.rec_epochdays);
satCalcData.rec_mjdsatepoch = satTime.toJulianDate();
satCalcData.rec_mjdsatepoch = satCalcData.rec_mjdsatepoch - 2400000.5;
satCalcData.rec_init = 1;
satCalcData.neo.neo_t = 0.0;
sgp4Init(satCalcData.rec_satnum, year, satCalcData.rec_mjdsatepoch - 33281.0);
//end;
}