public GeoCoordinate GetGeodeticCoordinateNow()
{
var tleISS = ParserTLE.parseTle(TleLine1, TleLine2, TleLine0);
var currentTime = new EpochTime(DateTime.UtcNow);
// TODO: use sdp4 for satellites with medium/high orbit.
var data = SatFunctions.getSatPositionAtTime(tleISS, currentTime, Sgp4.wgsConstant.WGS_84);
var secondsFromStart = (currentTime.getEpoch() - Math.Truncate(currentTime.getEpoch())) * 24 * 60 * 60;
var omega = OMEGA_E * secondsFromStart;
var C = MathNet.Numerics.LinearAlgebra.Double.DenseMatrix.OfArray(
new double[, ] {
{ Math.Cos(omega), Math.Sin(omega), 0 },
{ -Math.Sin(omega), Math.Cos(omega), 0 },
{ 0, 0, 1 }
});
var p = MathNet.Numerics.LinearAlgebra.Double.DenseMatrix.OfArray(
new double[, ] {
{ data.getX() * 1000 },
{ data.getY() * 1000 },
{ data.getZ() * 1000 }
});
var ecr = C * p;
GpsUtils.EcefToGeodetic(ecr[0, 0], ecr[1, 0], ecr[2, 0], out var lat, out var lon, out var h);
return(new GeoCoordinate(lat, lon, h));
}
public bool IsVisibleFromPointNow(GeoCoordinate observer)
{
var tleISS = ParserTLE.parseTle(TleLine1, TleLine2, TleLine0);
var currentTime = new EpochTime(DateTime.UtcNow);
var data = One_Sgp4.SatFunctions.getSatPositionAtTime(tleISS, currentTime, Sgp4.wgsConstant.WGS_84);
return(SatFunctions.isSatVisible(new Coordinate(observer.Latitude, observer.Longitude, observer.Altitude), 0, currentTime, data));
}
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));
}
public Satellite(long id, string name, string line1, string line2)
{
ID = id;
Name = name;
TleLine1 = line1;
TleLine2 = line2;
Tle = ParserTLE.parseTle(
line1,
line2,
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"));
}
}
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);
}
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"));
}
}
/*****************************************************************************
* @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);
}
static void Main(string[] args)
{
//Parse three line element
Tle tleISS = ParserTLE.parseTle(
"1 25544U 98067A 19132.30925117 .00001081 00000-0 24694-4 0 9993",
"2 25544 51.6426 179.4820 0001363 344.4861 92.2261 15.52657683169680",
"ISS 1");
//Parse tle from file
if (System.IO.File.Exists("tleData.txt"))
{
List <Tle> tleList = ParserTLE.ParseFile("tleData.txt");
}
//Get TLE from Space-Track.org
//list of satellites by their NORAD ID
string[] noradIDs = { "8709", "43572" };
try
{
One_Sgp4.SpaceTrack.GetSpaceTrack(noradIDs, "USERNAME", "PASSWORD");
}
catch { Console.Out.WriteLine("Error could not retrive TLE's from Space-Track, Login credentials might be wrong"); }
//Create Time points
EpochTime startTime = new EpochTime(DateTime.UtcNow);
EpochTime anotherTime = new EpochTime(2018, 100.5); //(Year 2018, 100 day at 12:00 HH)
EpochTime stopTime = new EpochTime(DateTime.UtcNow.AddHours(1));
//get time difference
double daysSince = startTime - anotherTime;
//throws exception if first time > second time
//double daysSince = anotherTime - startTime;
//compare Time points
EpochTime compareTime = new EpochTime(2018, 100.5); //(Year 2018, 100 day at 12:00 HH)
bool equals = anotherTime == compareTime;
bool notequals = startTime != anotherTime;
bool greater = startTime > anotherTime;
bool smaler = anotherTime < startTime;
//Add 15 Seconds to EpochTime
anotherTime.addTick(15);
//Add 20 Min to EpochTime
anotherTime.addMinutes(15);
//Add 1 hour to EpochTime
anotherTime.addHours(1);
//Add 2 Days to EpochTime
anotherTime.addDays(2);
Console.Out.WriteLine(anotherTime.ToString());
//Calculate Satellite Position and Speed
One_Sgp4.Sgp4 sgp4Propagator = new Sgp4(tleISS, Sgp4.wgsConstant.WGS_84);
//set calculation parameters StartTime, EndTime and caclulation steps in minutes
sgp4Propagator.runSgp4Cal(startTime, stopTime, 1 / 30.0); // 1/60 => caclulate sat points every 2 seconds
List <One_Sgp4.Sgp4Data> resultDataList = new List <Sgp4Data>();
//Return Results containing satellite Position x,y,z (ECI-Coordinates in Km) and Velocity x_d, y_d, z_d (ECI-Coordinates km/s)
resultDataList = sgp4Propagator.getRestults();
//Coordinate of an observer on Ground lat, long, height(in meters)
One_Sgp4.Coordinate observer = new Coordinate(35.00, 18.0, 0);
//Convert to ECI coordinate system
One_Sgp4.Point3d eci = observer.toECI(startTime.getLocalSiderealTime());
//Get Local SiderealTime for Observer
double localSiderealTime = startTime.getLocalSiderealTime(observer.getLongitude());
//Calculate if Satellite is Visible for a certain Observer on ground at certain timePoint
bool satelliteIsVisible = One_Sgp4.SatFunctions.isSatVisible(observer, 0.0, startTime, resultDataList[0]);
//Calculate Sperical Coordinates from an Observer to Satellite
//returns 3D-Point with range(km), azimuth(radians), elevation(radians) to the Satellite
One_Sgp4.Point3d spherical = One_Sgp4.SatFunctions.calcSphericalCoordinate(observer, startTime, resultDataList[0]);
//Calculate the Next 5 Passes over a point
//for a location, Satellite, StartTime, Accuracy in Seconds = 15sec, MaxNumber of Days = 5 Days, Wgs constant = WGS_84
//Returns pass with Location, StartTime of Pass, EndTime Of Pass, Max Elevation in Degrees
List <Pass> passes = One_Sgp4.SatFunctions.CalculatePasses(observer, tleISS, new EpochTime(DateTime.UtcNow), 15, 5, Sgp4.wgsConstant.WGS_84);
foreach (var p in passes)
{
Console.Out.WriteLine(p.ToString());
}
Console.Out.WriteLine("Done");
}
static void Main(string[] args)
{
//Parse three line element
Tle tleISS = ParserTLE.parseTle(
"1 25544U 98067A 19097.23063721 -.00000469 00000-0 00000+0 0 9999",
"2 25544 51.6449 353.9503 0002279 151.1697 290.4275 15.52495932164239",
"ISS 1");
//Parse tle from file
if (System.IO.File.Exists("tleData.txt"))
{
List <Tle> tleList = ParserTLE.ParseFile("tleData.txt");
}
//Get TLE from Space-Track.org
//list of satellites by their NORAD ID
string[] noradIDs = { "8709", "43572" };
try
{
One_Sgp4.SpaceTrack.GetSpaceTrack(noradIDs, "USERNAME", "PASSWORD");
}
catch { Console.Out.WriteLine("Error could not retrive TLE's from Space-Track, Login credentials might be wrong"); }
//Create Time points
EpochTime startTime = new EpochTime(DateTime.UtcNow);
EpochTime anotherTime = new EpochTime(2018, 100.5); //(Year 2017, 100 day at 12:00 HH)
EpochTime stopTime = new EpochTime(DateTime.UtcNow.AddHours(1));
//Add 15 Seconds to EpochTime
anotherTime.addTick(15);
//Add 20 Min to EpochTime
anotherTime.addMinutes(15);
//Add 1 hour to EpochTime
anotherTime.addHours(1);
//Add 2 Days to EpochTime
anotherTime.addDays(2);
Console.Out.WriteLine(anotherTime.ToString());
//Calculate Satellite Position and Speed
One_Sgp4.Sgp4 sgp4Propagator = new Sgp4(tleISS, Sgp4.wgsConstant.WGS_84);
//set calculation parameters StartTime, EndTime and caclulation steps in minutes
sgp4Propagator.runSgp4Cal(startTime, stopTime, 1 / 30.0); // 1/60 => caclulate sat points every 2 seconds
List <One_Sgp4.Sgp4Data> resultDataList = new List <Sgp4Data>();
//Return Results containing satellite Position x,y,z (ECI-Coordinates in Km) and Velocity x_d, y_d, z_d (ECI-Coordinates km/s)
resultDataList = sgp4Propagator.getRestults();
//Coordinate of an observer on Ground lat, long, height(in meters)
One_Sgp4.Coordinate observer = new Coordinate(35.554595, 18.888574, 0);
//Convert to ECI coordinate system
One_Sgp4.Point3d eci = observer.toECI(startTime.getLocalSiderealTime());
//Get Local SiderealTime for Observer
double localSiderealTime = startTime.getLocalSiderealTime(observer.getLongitude());
//TESTING MIR
//TEST ECI
EpochTime T_eciTime = new EpochTime(09, 00, 00, 1995, 10, 1);
//Test GMST
if (T_eciTime.getLocalSiderealTime() == 2.524218)
{
}
Coordinate T_eciCoo = new Coordinate(40, -75);
var t_eci = T_eciCoo.toECI(T_eciTime.getLocalSiderealTime());
//Coordinate equals x' = 1703.295 km, y' = 4586.650 km, z' = 4077.984 km.
EpochTime t_time = new EpochTime(12, 46, 0, 1995, 11, 18);
Coordinate t_cord = new Coordinate(45.0, -93);
Sgp4Data mirPos = new Sgp4Data();
mirPos.setX(-4400.594);
mirPos.setY(1932.870);
mirPos.setZ(4760.712);
var lookAngels = SatFunctions.calcSphericalCoordinate(t_cord, t_time, mirPos);
var onGround = SatFunctions.calcSatSubPoint(t_time, mirPos, Sgp4.wgsConstant.WGS_72);
var r = t_cord.toECI(t_time.getLocalSiderealTime());
//Calculate if Satellite is Visible for a certain Observer on ground at certain timePoint
bool satelliteIsVisible = One_Sgp4.SatFunctions.isSatVisible(observer, 0.0, startTime, resultDataList[0]);
//Calculate Sperical Coordinates from an Observer to Satellite
//returns 3D-Point with range(km), azimuth(radians), elevation(radians) to the Satellite
One_Sgp4.Point3d spherical = One_Sgp4.SatFunctions.calcSphericalCoordinate(observer, startTime, resultDataList[0]);
//Calculate the Next 5 Passes over a point
//for a location, Satellite, StartTime, Accuracy in Seconds = 15sec, MaxNumber of Days = 5 Days, Wgs constant = WGS_84
//Returns pass with Location, StartTime of Pass, EndTime Of Pass, Max Elevation in Degrees
List <Pass> passes = One_Sgp4.SatFunctions.CalculatePasses(observer, tleISS, new EpochTime(DateTime.UtcNow), 15, 5, Sgp4.wgsConstant.WGS_84);
foreach (var p in passes)
{
Console.Out.WriteLine(p.ToString());
}
}