public List <Satellite> GetSatellites(string[] Norad)
{
string predicateValues = "/class/tle_latest/ORDINAL/1/NORAD_CAT_ID/" + string.Join(",", Norad) + "/orderby/NORAD_CAT_ID%20ASC/format/3le";
string request = uriBase + requestController + requestAction + predicateValues;
// Create new WebClient object to communicate with the service
using (var client = new WebClientEx())
{
if (Auth(client))
{
var response4 = client.DownloadData(request);
var stringData = (System.Text.Encoding.Default.GetString(response4)).Split('\n');
List <Satellite> result = new List <Satellite>();
for (Int32 i = 0; i < stringData.Length - 1; i += 3)
{
Tle tle = new Tle(stringData[i], stringData[i + 1], stringData[i + 2]);
Satellite sat = new Satellite(tle);
result.Add(sat);
OnProgress(new ProgressEventArgs(i, stringData.Length - 1));
}
return(result);
}
else
{
throw new NoAuthException();
}
}
}
public List <SurfaceSgp4Pair> GetCoordinatePairs(Tle satalite, DateTime from, DateTime to, int resolution)
{
Sgp4 sgp4Propagator = new Sgp4(satalite, 1);
var epochFrom = new EpochTime(from);
var epochTo = new EpochTime(to);
var stepSize = (to - from).TotalMinutes / resolution;
sgp4Propagator.runSgp4Cal(epochFrom, epochTo, stepSize);
var results = sgp4Propagator.getRestults()
.Select((sgp, i) => {
var time = from.AddMinutes(i * stepSize);
return(new SurfaceSgp4Pair
{
TimePointUtc = time,
SatalitePoint = sgp,
SurfacePoint = this.GetMePosition(time)
});
})
.ToList();
return(results);
}
/// <summary>
/// Creates a new numerical orbital element descriptor set for the provided two-line element set
/// </summary>
/// <param name="tle">The set to extract numerical values from</param>
public Orbit(Tle tle)
{
// extract and format tle data
MeanAnomoly = tle.MeanAnomaly;
AscendingNode = tle.RightAscendingNode;
ArgumentPerigee = tle.ArgumentPerigee;
Eccentricity = tle.Eccentricity;
Inclination = tle.Inclination;
MeanMotion = tle.MeanMotionRevPerDay * SgpConstants.TwoPi / SgpConstants.MinutesPerDay;
BStar = tle.BStarDragTerm;
Epoch = tle.Epoch;
// recover original mean motion (xnodp) and semimajor axis (aodp) from input elements
var a1 = Math.Pow(SgpConstants.ReciprocalOfMinutesPerTimeUnit / MeanMotion, SgpConstants.TwoThirds);
var cosio = Math.Cos(Inclination.Radians);
var theta2 = cosio * cosio;
var x3Thm1 = 3.0 * theta2 - 1.0;
var eosq = Eccentricity * Eccentricity;
var betao2 = 1.0 - eosq;
var betao = Math.Sqrt(betao2);
var temp = 1.5 * SgpConstants.Ck2 * x3Thm1 / (betao * betao2);
var del1 = temp / (a1 * a1);
var a0 = a1 * (1.0 - del1 * (1.0 / 3.0 + del1 * (1.0 + del1 * 134.0 / 81.0)));
var del0 = temp / (a0 * a0);
RecoveredMeanMotion = MeanMotion / (1.0 + del0);
RecoveredSemiMajorAxis = a0 / (1.0 - del0);
// find perigee and period
Perigee = (RecoveredSemiMajorAxis * (1.0 - Eccentricity) - SgpConstants.DistanceUnitsPerEarthRadii) *
SgpConstants.EarthRadiusKm;
Apogee = (RecoveredSemiMajorAxis * (1.0 + Eccentricity) - SgpConstants.DistanceUnitsPerEarthRadii) *
SgpConstants.EarthRadiusKm;
Period = SgpConstants.TwoPi / RecoveredMeanMotion;
}
/// <summary>
/// Constructor
/// </summary>
/// <param name="tle">The two-line representation of the satellite</param>
public Satellite(Tle tle)
{
Tle = tle;
_sgp4 = new Sgp4(tle);
Name = tle.Name;
}
public List <Satellite> GetSatellites(string LanuchYaer)
{
string predicateValues = "/class/tle_latest/LAUNCH_YEAR/=" + LanuchYaer + "/orderby/INTLDES asc/metadata/false";
string request = uriBase + requestController + requestAction + predicateValues;
// Create new WebClient object to communicate with the service
using (var client = new WebClientEx())
{
if (Auth(client))
{
var response4 = client.DownloadData(request);
var stringData = (System.Text.Encoding.Default.GetString(response4)).Split('\n');
List <Satellite> result = new List <Satellite>();
for (Int32 i = 0; i < stringData.Length - 1; i += 3)
{
Tle tle = new Tle(stringData[i], stringData[i + 1], stringData[i + 2]);
Satellite sat = new Satellite(tle);
result.Add(sat);
OnProgress(new ProgressEventArgs(i, stringData.Length - 1));
}
return(result);
}
else
{
throw new NoAuthException();
}
}
}
//Returns the azimuth and elevation from a TLE
private double[] getSkyCoords(Tle tle)
{
double[] array = { -1, -1 };
//create a viewing site
Site site = new Site(latitude, longitude, 0.240949);
//make an orbit out of the tle
Orbit orbit = new Orbit(tle);
//get the date
DateTime dt = DateTime.UtcNow;
//get the time since the epoch
TimeSpan ts = orbit.TPlusEpoch(dt);
//then calculate the position
try
{
EciTime eci = orbit.GetPosition(dt);
Topo topoLook = site.GetLookAngle(eci);
array[0] = topoLook.AzimuthDeg;
array[1] = topoLook.ElevationDeg;
return(array);
}
catch
{
return(array);
}
}
public static Tle[] TlesFromTxt(string filename)
{
ArrayList list1 = new ArrayList();
StreamReader sr = new StreamReader(filename);
int i = 1;
string line1 = "", line2 = "", line3 = "";
while (sr.Peek() >= 0)
{
switch (i)
{
case 1:
line1 = sr.ReadLine();
i++;
break;
case 2:
line2 = sr.ReadLine();
i++;
break;
case 3:
line3 = sr.ReadLine();
Tle tle0 = new Tle(line1, line2, line3);
list1.Add(tle0);
i = 1;
break;
}
}
Tle[] tles = (Tle[])(list1).ToArray(typeof(Tle));
return(tles);
}
IEnumerator LoadDebris()
{
spaceCraft = GameObject.Find("SpaceCraft");
attribute = spaceCraft.GetComponent <attributeDefiner>();
Loading.text = "Downloading Game Debris Data";
yield return(new WaitForSeconds(1));
string jsonURL = @"https://worldwind.arc.nasa.gov/spacebirds/data/TLE.json";
WWW download = new WWW(jsonURL);
while (!download.isDone)
{
Progress.fillAmount = download.progress;
float prog = download.progress * 100;
ProgressText.text = "" + (int)prog + "%";
yield return(null);
}
yield return(download);
List <Debris> debrisData = JsonConvert.DeserializeObject <List <Debris> >(download.text);
Loading.text = "Loading Game Debris.";
foreach (var item in debrisData)
{
if (item.OBJECT_TYPE == "DEBRIS")
{
Tle tle = new Tle(item.OBJECT_ID, item.TLE_LINE1, item.TLE_LINE2);
Satellite sat = new Satellite(tle);
List <Eci> coords = new List <Eci>();
Eci eci = sat.PositionEci(900);
Vector3 pos = new Vector3((float)eci.Position.X, (float)eci.Position.Y, (float)eci.Position.Z);
Debug.Log(pos);
float decider = Random.value;
if (decider <= 0.33)
{
DebrisGenerator(bolt, pos);
}
else if (decider > 0.33 && decider <= 0.66)
{
DebrisGenerator(nut, pos);
}
else
{
DebrisGenerator(sheet, pos);
}
}
}
yield return(new WaitForSeconds(1));
LoadingScreen.SetActive(false);
attribute.IsLoading = false;
}
public SGP4Thread(Tle tleData,
TimeDate starttime, TimeDate stoptime, double step)
{
satTleData = tleData;
startTime = starttime;
stopTime = stoptime;
tick = step;
}
public satObjData(string satName, Tle tle, Vector3 scale, Quaternion rot)
{
this.satName = satName;
this.tle = tle;
this.scale = scale;
this.rot = rot;
updatePos();
}
public SGP4Thread(SatelliteDataVector dataVector, Tle tleData,
TimeDate starttime, TimeDate stoptime, double step)
{
satTleData = tleData;
startTime = starttime;
stopTime = stoptime;
tick = step;
dataVectorRes = dataVector;
}
// /////////////////////////////////////////////////////////////////////
static void Main(string[] args)
{
// Sample code to test the SGP4 and SDP4 implementation. The test
// TLEs come from the NORAD document "Space Track Report No. 3".
// Test SGP4
string str1 = "SGP4 Test";
string str2 = "1 88888U 80275.98708465 .00073094 13844-3 66816-4 0 8";
string str3 = "2 88888 72.8435 115.9689 0086731 52.6988 110.5714 16.05824518 105";
Tle tle1 = new Tle(str1, str2, str3);
PrintPosVel(tle1);
Console.WriteLine();
// Test SDP4
str1 = "SDP4 Test";
str2 = "1 11801U 80230.29629788 .01431103 00000-0 14311-1 8";
str3 = "2 11801 46.7916 230.4354 7318036 47.4722 10.4117 2.28537848 6";
Tle tle2 = new Tle(str1, str2, str3);
PrintPosVel(tle2);
Console.WriteLine("\nExample output:");
// Example: Define a location on the earth, then determine the look-angle
// to the SDP4 satellite defined above.
// Create an orbit object using the SDP4 TLE object.
Satellite satSDP4 = new Satellite(tle2);
// Get the location of the satellite from the Orbit object. The
// earth-centered inertial information is placed into eciSDP4.
// Here we ask for the location of the satellite 90 minutes after
// the TLE epoch.
EciTime eciSDP4 = satSDP4.PositionEci(90.0);
// Now create a site object. Site objects represent a location on the
// surface of the earth. Here we arbitrarily select a point on the
// equator.
Site siteEquator = new Site(0.0, -100.0, 0); // 0.00 N, 100.00 W, 0 km altitude
// Now get the "look angle" from the site to the satellite.
// Note that the ECI object "eciSDP4" has a time associated
// with the coordinates it contains; this is the time at which
// the look angle is valid.
Topo topoLook = siteEquator.GetLookAngle(eciSDP4);
// Print out the results. Note that the Azimuth and Elevation are
// stored in the CoordTopo object as radians. Here we convert
// to degrees using Rad2Deg()
Console.Write("AZ: {0:f3} EL: {1:f3}\n",
topoLook.AzimuthDeg,
topoLook.ElevationDeg);
}
// Use this for initialization
void Start()
{
this._tle = new Tle("sat", TLE1, TLE2);
this._satellite = new Satellite(_tle);
this._site = new Site(Lat, Long, Altitude);
this._detailsCanvas = this.transform.Find("detailsCanvas").gameObject;
mainLabel.text = SatelliteName;
}
public Orbit(Tle tle) //construction using file
: this(tle.GetField(Tle.Field.Inclination),
tle.GetField(Tle.Field.Eccentricity),
tle.GetField(Tle.Field.Raan),
tle.GetField(Tle.Field.MeanMotion),
tle.GetField(Tle.Field.ArgPerigee))
{
_tle = tle;
}
public void TleParseFromLinesShouldSucceed()
{
// 0.........1.........2.........3.........4.........5.........6.........7
string line1 = "1 42784U 17036Vvv 17175.91623346 .00001083 00000-0 52625-4 0 9993";
string line2 = "2 42784 97.4499 235.6602 0011188 243.9018 116.1066 15.20524655 207";
Tle t = ParserTLE.parseTle(line1, line2);
Assert.That(t.isValidData, Is.True);
Assert.That(t.getClassification(), Is.EqualTo(0));
Assert.That(t.getDrag(), Is.EqualTo(0.000052625));
Assert.That(t.getEccentriciy(), Is.EqualTo(0.0011188));
Assert.That(t.getEphemeris(), Is.EqualTo(0));
Assert.That(t.getEpochDay(), Is.EqualTo(175.91623346));
Assert.That(t.getEpochYear(), Is.EqualTo(17));
Assert.That(t.getFirstMeanMotion(), Is.EqualTo(.00001083));
Assert.That(t.getInclination(), Is.EqualTo(97.4499));
Assert.That(t.getMeanAnomoly(), Is.EqualTo(116.1066));
Assert.That(t.getMeanMotion(), Is.EqualTo(15.20524655));
Assert.That(t.getName(), Is.EqualTo("1736Vvv"));
Assert.That(t.getNoradID(), Is.EqualTo("42784"));
Assert.That(t.getPerigee(), Is.EqualTo(243.9018));
Assert.That(t.getPice(), Is.EqualTo("Vvv"));
Assert.That(t.getRelevationNumber(), Is.EqualTo(20));
Assert.That(t.getRightAscendingNode(), Is.EqualTo(235.6602));
Assert.That(t.getSatNumber(), Is.EqualTo(42784));
Assert.That(t.getSecondMeanMotion(), Is.EqualTo(0));
Assert.That(t.getSetNumber(), Is.EqualTo(999));
Assert.That(t.getStartNr(), Is.EqualTo(36));
Assert.That(t.getStartYear(), Is.EqualTo(17));
t = ParserTLE.parseTle(line1, line2, "Pegasus");
Assert.That(t.isValidData, Is.True);
Assert.That(t.getClassification(), Is.EqualTo(0));
Assert.That(t.getDrag(), Is.EqualTo(0.000052625));
Assert.That(t.getEccentriciy(), Is.EqualTo(0.0011188));
Assert.That(t.getEphemeris(), Is.EqualTo(0));
Assert.That(t.getEpochDay(), Is.EqualTo(175.91623346));
Assert.That(t.getEpochYear(), Is.EqualTo(17));
Assert.That(t.getFirstMeanMotion(), Is.EqualTo(.00001083));
Assert.That(t.getInclination(), Is.EqualTo(97.4499));
Assert.That(t.getMeanAnomoly(), Is.EqualTo(116.1066));
Assert.That(t.getMeanMotion(), Is.EqualTo(15.20524655));
Assert.That(t.getName(), Is.EqualTo("Pegasus"));
Assert.That(t.getNoradID(), Is.EqualTo("42784"));
Assert.That(t.getPerigee(), Is.EqualTo(243.9018));
Assert.That(t.getPice(), Is.EqualTo("Vvv"));
Assert.That(t.getRelevationNumber(), Is.EqualTo(20));
Assert.That(t.getRightAscendingNode(), Is.EqualTo(235.6602));
Assert.That(t.getSatNumber(), Is.EqualTo(42784));
Assert.That(t.getSecondMeanMotion(), Is.EqualTo(0));
Assert.That(t.getSetNumber(), Is.EqualTo(999));
Assert.That(t.getStartNr(), Is.EqualTo(36));
Assert.That(t.getStartYear(), Is.EqualTo(17));
}
// //////////////////////////////////////////////////////////////////////////
//
// Routine to output position and velocity information of satellite
// in orbit described by TLE information.
//
static void PrintPosVel(Tle tle)
{
const int Step = 360;
Satellite sat = new Satellite(tle);
List <Eci> coords = new List <Eci>();
// Calculate position, velocity
// mpe = "minutes past epoch"
for (int mpe = 0; mpe <= (Step * 4); mpe += Step)
{
// Get the position of the satellite at time "mpe".
// The coordinates are placed into the variable "eci".
Eci eci = sat.PositionEci(mpe);
// Add the coordinate object to the list
coords.Add(eci);
}
// Print TLE data
Console.Write("{0}\n", tle.Name);
Console.Write("{0}\n", tle.Line1);
Console.Write("{0}\n", tle.Line2);
// Header
Console.Write("\n TSINCE X Y Z\n\n");
// Iterate over each of the ECI position objects pushed onto the
// coordinate list, above, printing the ECI position information
// as we go.
for (int i = 0; i < coords.Count; i++)
{
Eci e = coords[i] as Eci;
Console.Write("{0,8}.00 {1,16:f8} {2,16:f8} {3,16:f8}\n",
i * Step,
e.Position.X,
e.Position.Y,
e.Position.Z);
}
Console.Write("\n XDOT YDOT ZDOT\n\n");
// Iterate over each of the ECI position objects in the coordinate
// list again, but this time print the velocity information.
for (int i = 0; i < coords.Count; i++)
{
Eci e = coords[i] as Eci;
Console.Write("{0,24:f8} {1,16:f8} {2,16:f8}\n",
e.Velocity.X,
e.Velocity.Y,
e.Velocity.Z);
}
}
public Satellite(long id, string name, string line1, string line2)
{
ID = id;
Name = name;
TleLine1 = line1;
TleLine2 = line2;
Tle = ParserTLE.parseTle(
line1,
line2,
name);
}
private void ProcessTLE_Click(object sender, RoutedEventArgs e)
{
var lines = TLEedit.Text.Split(new char[] { '\n', '\r' }, 3);
if (lines.Count() < 3)
{
return;
}
var nm = lines[0].TrimEnd(new char[] { ' ' });
tle = new Tle(nm, lines[1], lines[2]);
}
public void testFuckShit2()
{
SGP4.Sgp4 sgp = new SGP4.Sgp4(satTleData, 0);
sgp.runSgp4Cal(startTime, stopTime, tick / 60.0);
results = new List <Sgp4Data>(sgp.getRestults());
sgp.clear();
sgp = null;
satTleData = null;
startTime = null;
stopTime = null;
dataVectorRes = null;
}
public Satellite(Tle tle, string name = "")
{
Orbit = new Orbit(tle);
NoradID = int.Parse(tle.NoradNumber.Trim());
if (name == "")
{
Name = tle.Name;
}
else
{
Name = name;
}
}
public void TleParseFromLinesWithChecksumErrorShouldFail(string line1, string line2)
{
try
{
Tle t = ParserTLE.parseTle(line1, line2);
Assert.Fail("This should raise an exception!");
}
catch (Exception ex)
{
Assert.That(ex, Is.TypeOf <InvalidDataException>());
Assert.That(ex.Message, Contains.Substring("checksum error"));
}
}
private List <Satellite> GetSatellites(bool Cache = true)
{
var CurDir = Path.GetDirectoryName(System.Reflection.Assembly.GetExecutingAssembly().Location);
string predicateValues = "/class/tle_latest/ORDINAL/1/EPOCH/%3Enow-30/orderby/APOGEE%20desc/format/3le/distinct/true";
string request = uriBase + requestController + requestAction + predicateValues;
using (var client = new WebClientEx())
{
if (Auth(client))
{
var response4 = client.DownloadData(request);
var stringData = System.Text.Encoding.Default.GetString(response4).Split('\n');
using (var sw = new StreamWriter(CurDir + "/lastrequest.dat"))
{
sw.Write(System.Text.Encoding.Default.GetString(response4));
}
var sats = new List <Satellite>();
using (var sw = new StreamWriter(CurDir + "/satdata.dat"))
{
for (Int32 i = 0; i < stringData.Length - 1; i += 3)
{
try
{
if (stringData[i].Contains("DEB"))
{
continue;
}
//if (sats.Count > c_maxNumber)
// break;
Tle tle = new Tle(stringData[i], stringData[i + 1], stringData[i + 2]);
sw.WriteLine(stringData[i]);
sw.WriteLine(stringData[i + 1]);
sw.WriteLine(stringData[i + 2]);
Satellite sat = new Satellite(tle);
sats.Add(sat);
OnProgress(new ProgressEventArgs(i, stringData.Length - 1));
}
catch { }
}
}
SaveSats(sats);
return(sats);
}
else
{
throw new NoAuthException();
}
}
}
public void TestSatContact()
{
Tle tleISS = ParserTLE.parseTle(
"1 25544U 98067A 19356.46068278 .00000035 00000-0 86431-5 0 9990",
"2 25544 51.6420 147.9381 0007793 61.6458 55.7201 15.50124783204461",
"ISS 1");
Coordinate position = new Coordinate(35, 18, 0);
EpochTime startTime = new EpochTime(0, 0, 0, 2020, 1, 6);
List <Pass> passes = SatFunctions.CalculatePasses(position, tleISS, startTime, 1, 1);
Assert.AreEqual(8, passes.Count);
}
private SataliteGameObject InstantiateSatalite(Tle satalite)
{
var gObject = Instantiate(this.BaseSatalite);
gObject.transform.SetParent(BaseSatalite.transform.parent, false);
gObject.SetActive(true);
var script = gObject.GetComponent <SataliteBehavior>();
script.TLeData = satalite;
return(new SataliteGameObject {
GameObject = gObject,
Script = script
});
}
private void addTLE_Click(object sender, EventArgs e)
{
if (textBox1.Text.Trim().Length == 0 || textBox2.Text.Trim().Length == 0 || textBox3.Text.Trim().Length == 0)
{
MessageBox.Show("Please make sure you filled in ever box.");
return;
}
List <Tle> list = new List <Tle>();
Tle input = new Tle(textBox1.Text, textBox2.Text, textBox3.Text);
list.Add(input);
var mainWindow = Application.OpenForms.OfType <Window>().Single();
mainWindow.updateSatList(list);
this.Close();
}
public void TleParseFromCorruptLinesShouldFail()
{
string line1 = "1 42784U 17036V 17175.91623346 .00001083 00000 - 0 52625 - 4 0 9993";
string line2 = "2 42784 97.4499 235.6602 0011188 243.9018 116.1066 15.20524655 207";
try
{
Tle t = ParserTLE.parseTle(line1, line2);
Assert.Fail("This should raise an exception!");
}
catch (Exception ex)
{
Assert.That(ex, Is.TypeOf <InvalidDataException>());
Assert.That(ex.Message, Contains.Substring("parse error"));
}
}
private void lockButton_Click(object sender, EventArgs e)
{
if (satList.SelectedItem == null)
{
return;
}
//This could probably break depending on the sitituation TODO: FIX
statusText.Text = "Locking onto: " + satList.SelectedItem.ToString();
LockedOn = true;
foreach (Tle tle in Satellites)
{
if (tle.Name == satList.SelectedItem.ToString())
{
Target = tle;
break;
}
}
aimLock = false;
manualAimToggle.CheckState = 0;
/*
* WolframAlpha wolfram = new WolframAlpha(WolframAppId);
*
* QueryResult results = wolfram.Query(Target.Name);
* try
* {
* if (results != null)
* {
* foreach (Pod pod in results.Pods)
* {
* if (pod.Title == "Wikipedia summary")
* {
* Console.WriteLine(pod.SubPods[0].Image.Alt);
* desc.ImageLocation = pod.SubPods[0].Image.Src;
* }
* }
* }
* }
* catch (NullReferenceException)
* {
* Console.WriteLine("ERROR");
* }
*/
setDescription(Target.Name);
}
private List <Satellite> GetSatellites(Double Perigee, Double Apogee)
{
var CurDir = Path.GetDirectoryName(System.Reflection.Assembly.GetExecutingAssembly().Location);
string predicateValues = "/class/tle_latest/ORDINAL/1/EPOCH/%3Enow-30/APOGEE/>" + Perigee.ToString() + "/PERIGEE/<" + Apogee.ToString() + "/orderby/APOGEE%20asc/format/3le/distinct/true";
string request = uriBase + requestController + requestAction + predicateValues;
using (var client = new WebClientEx())
{
OnStatus("Соединение с базой NORAD...");
if (Auth(client))
{
OnStatus("Загрузка данных из базы...");
var response4 = client.DownloadData(request);
var stringData = System.Text.Encoding.Default.GetString(response4).Split('\n');
using (var sw = new StreamWriter(CurDir + "/lastrequest.dat"))
{
sw.Write(System.Text.Encoding.Default.GetString(response4));
}
OnStatus("Генерация орбитальных данных...");
var sats = new List <Satellite>();
for (Int32 i = 0; i < stringData.Length - 1; i += 3)
{
try
{
if (stringData[i].Contains("DEB"))
{
continue;
}
Tle tle = new Tle(stringData[i], stringData[i + 1], stringData[i + 2]);
Satellite sat = new Satellite(tle);
sats.Add(sat);
OnProgress(new ProgressEventArgs(i, stringData.Length - 1));
}
catch { }
}
OnStatus("Загрузка данных завершена!");
return(sats);
}
else
{
throw new NoAuthException();
}
}
}
/*****************************************************************************
* @function name : calECIDateAndVelocity
* @author : Kaguya
* @date : 2020/12/3 12:38
* @inparam :
* @outparam :
* @last change :
* @usage : 基于one_sgp4项目，计算航天器基于ECI坐标系下的位置和速度
*****************************************************************************/
public void calECIDateAndVelocity()
{
Tle tleISS = ParserTLE.parseTle(first, second, "ISS 1");
DateTime t = new DateTime(data[0], data[1], data[2], data[3], data[4], data[5]);
EpochTime startTime = new EpochTime(t);
Sgp4Data sate = SatFunctions.getSatPositionAtTime(tleISS, startTime, Sgp4.wgsConstant.WGS_84);
One_Sgp4.Point3d position = sate.getPositionData();
ECI = new double[3];
ECI[0] = position.x;
ECI[1] = position.y;
ECI[2] = position.z;
velocity = new double[3];
velocity[0] = sate.getVelocityData().x;
velocity[1] = sate.getVelocityData().y;
velocity[2] = sate.getVelocityData().z;
velocity = getECEF(velocity, data);
}
public void TestSatGroundPosition(int hh, int mm, int ss, int yyyy, int MM, int dd)
{
Tle tleISS = ParserTLE.parseTle(
"1 25544U 98067A 19356.46068278 .00000035 00000-0 86431-5 0 9990",
"2 25544 51.6420 147.9381 0007793 61.6458 55.7201 15.50124783204461",
"ISS 1");
EpochTime testTime = new EpochTime(hh, mm, ss, yyyy, MM, dd);
Sgp4Data data = SatFunctions.getSatPositionAtTime(tleISS, testTime, Sgp4.wgsConstant.WGS_84);
Assert.IsNotNull(data);
Coordinate ground = SatFunctions.calcSatSubPoint(testTime, data, Sgp4.wgsConstant.WGS_84);
Assert.Greater(ground.getHeight(), 0);
Assert.LessOrEqual(ground.getLongitude(), 180.0);
Assert.Greater(ground.getLongitude(), -180.0);
Assert.LessOrEqual(ground.getLatitude(), 90.0);
Assert.Greater(ground.getLatitude(), -90.0);
}
