public void PassPrediction()
{
List <PassDetails> knownPasses = SetupKnownPasses();
CoordGeodetic geo = new CoordGeodetic(41.760612, -111.819384, 1.394);
Tle tle = new Tle("ISS (ZARYA)",
"1 25544U 98067A 15090.55997958 .00016867 00000-0 24909-3 0 9997",
"2 25544 51.6467 111.8303 0006284 156.4629 341.9393 15.55450652935952");
SGP4 sgp4 = new SGP4(tle);
/*
* generate 7 day schedule
*/
DateTime start_date = new DateTime(2015, 4, 13, 0, 0, 0); //DateTime.Now (true);
DateTime end_date = start_date.AddDays(7); //new DateTime (System.DateTime.Now.AddDays (7));
List <PassDetails> pass_list = new List <PassDetails>();
;
//Console.WriteLine("Start time: " + start_date.ToString());
//Console.WriteLine("End time : " + end_date.ToString());
/*
* generate passes
*/
pass_list = GeneratePassList(geo, sgp4, start_date, end_date, 180);
Assert.AreEqual(knownPasses.Count, pass_list.Count);
for (int i = 0; i < pass_list.Count; ++i)
{
Assert.AreEqual(knownPasses[i].ToString(), pass_list[i].ToString());
}
}
public OrbitalElements(Tle tle)
{
/*
* extract and format tle data
*/
mean_anomoly_ = tle.MeanAnomaly(false);
ascending_node_ = tle.RightAscendingNode(false);
argument_perigee_ = tle.ArgumentPerigee(false);
eccentricity_ = tle.Eccentricity();
inclination_ = tle.Inclination(false);
mean_motion_ = tle.MeanMotion() * Global.kTWOPI / Global.kMINUTES_PER_DAY;
bstar_ = tle.BStar();
epoch_ = tle.Epoch();
/*
* recover original mean motion (xnodp) and semimajor axis (aodp)
* from input elements
*/
double a1 = Math.Pow(Global.kXKE / MeanMotion(), Global.kTWOTHIRD);
double cosio = Math.Cos(Inclination());
double theta2 = cosio * cosio;
double x3thm1 = 3.0 * theta2 - 1.0;
double eosq = Eccentricity() * Eccentricity();
double betao2 = 1.0 - eosq;
double betao = Math.Sqrt(betao2);
double temp = (1.5 * Global.kCK2) * x3thm1 / (betao * betao2);
double del1 = temp / (a1 * a1);
double a0 = a1 * (1.0 - del1 * (1.0 / 3.0 + del1 * (1.0 + del1 * 134.0 / 81.0)));
double del0 = temp / (a0 * a0);
recovered_mean_motion_ = MeanMotion() / (1.0 + del0);
/*
* alternative way to calculate
* doesnt affect final results
* recovered_semi_major_axis_ = pow(XKE / RecoveredMeanMotion(), TWOTHIRD);
*/
recovered_semi_major_axis_ = a0 / (1.0 - del0);
/*
* find perigee and period
*/
perigee_ = (RecoveredSemiMajorAxis() * (1.0 - Eccentricity()) - Global.kAE) * Global.kXKMPER;
period_ = Global.kTWOPI / RecoveredMeanMotion();
}
/**
* Copy constructor
* @param[in] tle Tle object to copy from
*/
public Tle(Tle tle)
{
name_ = tle.name_;
line_one_ = tle.line_one_;
line_two_ = tle.line_two_;
norad_number_ = tle.norad_number_;
int_designator_ = tle.int_designator_;
epoch_ = tle.epoch_;
mean_motion_dt2_ = tle.mean_motion_dt2_;
mean_motion_ddt6_ = tle.mean_motion_ddt6_;
bstar_ = tle.bstar_;
inclination_ = tle.inclination_;
right_ascending_node_ = tle.right_ascending_node_;
eccentricity_ = tle.eccentricity_;
argument_perigee_ = tle.argument_perigee_;
mean_anomaly_ = tle.mean_anomaly_;
mean_motion_ = tle.mean_motion_;
orbit_number_ = tle.orbit_number_;
}