public void Orbit_generation()
{
//load_orbit_file();
scenarioCheck();
var format = new NumberFormatInfo();
format.NegativeSign = "-";
format.NumberDecimalSeparator = ".";
// planetodetic.Lat = Double.Parse(lat2[i], format);
for (int i = 0; i < orbitmissioncount; i++)
{
//debug infomation///////
if (orbitdata[i].misnum == orbitdata[i].cod_id && orbitdata[i].used == 1 && orbitdata[i].efileused == false)
{
//generate the timeline file
TL_file_generator(orbitdata[i].name, orbitdata[i].name);
Console.Write("Misnum == cod_id\n");
Console.Write("Mission= " + orbitdata[i].name + "\n" + orbitdata[i].epoch + " " + orbitdata[i].epoch_time + " ");
Console.Write(orbitdata[i].sma + " " + orbitdata[i].ecc + " " + orbitdata[i].inc + " " + orbitdata[i].raan + " " + orbitdata[i].aop + " " + orbitdata[i].ma + "\n");
string centerbodyname;
if (orbitdata[i].centerbody == 1)
{
centerbodyname = "Earth";
}
else if (orbitdata[i].centerbody == 2)
{
centerbodyname = "Moon";
}
else
{
centerbodyname = "Earth";
}
// AGI.STKObjects.IAgSatellite sat = (IAgSatellite)m_oApplication.CurrentScenario.Children.New(AGI.STKObjects.AgESTKObjectType.eSatellite, mission2[i]);
//sat.SetPropagatorType(AGI.STKObjects.AgEVePropagatorType.ePropagatorTwoBody);
try
{
//create a new sat with the cod orbit details;
orbitdata[i].MisSat = (IAgSatellite)m_oApplication.CurrentScenario.Children.NewOnCentralBody(AGI.STKObjects.AgESTKObjectType.eSatellite, orbitdata[i].name, centerbodyname);
//AGI.STKObjects.IAgSatellite sat = (IAgSatellite)m_oApplication.CurrentScenario.Children.NewOnCentralBody(AGI.STKObjects.AgESTKObjectType.eSatellite, orbitdata[i].name, centerbodyname);
}catch
{
//sat already exists reset the scenario;
this.m_oApplication.CloseScenario();
scenarioCheck();
Orbit_generation();
return;
}
//disable the leading ground track
groundtrack_set(orbitdata[i].MisSat, groundtrack_displayed);
//set the propagator type to HPOP
orbitdata[i].MisSat.SetPropagatorType(AGI.STKObjects.AgEVePropagatorType.ePropagatorHPOP);
//TODO update below code to use sat not hpop;
AGI.STKObjects.IAgVePropagatorHPOP hpop = (AGI.STKObjects.IAgVePropagatorHPOP)orbitdata[i].MisSat.Propagator;
IAgOrbitState orbit = hpop.InitialState.Representation;
//create the string to hold the missions epoch date & time
string cmb_epoch = orbitdata[i].epoch;
cmb_epoch += " ";
cmb_epoch += orbitdata[i].epoch_time;
DateTime epochDT = Convert.ToDateTime(orbitdata[i].epoch);
DateTime startDT = Convert.ToDateTime(orbitdata[i].start_date);
DateTime endDT;
if (orbitdata[i].endopt == 0)
{
endDT = startDT;
endDT = endDT.AddDays((double)orbitdata[i].duration);
orbitdata[i].end_time = orbitdata[i].start_time;
}
else
{
endDT = Convert.ToDateTime(orbitdata[i].end_date);
}
//hpop.ForceModel.EclipsingBodies.AssignEclipsingBody( centerbodyname);
//check the centerbody of the provided orbit data;
if (orbitdata[i].centerbody == 1)
{// centerbody == EARTH
Console.Write("centerbody2[i]) == 1 \n");
Console.Write("\n Centralbodyfile=" + hpop.ForceModel.CentralBodyGravity.File + "\n");
hpop.ForceModel.Drag.Use = false;
hpop.ForceModel.SolarRadiationPressure.Use = false;
}
else if (orbitdata[i].centerbody == 2)
{//CenterBody == Moon
Console.Write("centerbody2[i]) == 2 \n");
hpop.ForceModel.Drag.Use = false;
hpop.ForceModel.SolarRadiationPressure.Use = false;
Console.Write("\n Centralbodyfile=" + hpop.ForceModel.CentralBodyGravity.File + "\n");
//change gravity file for HPOP use with the moon
hpop.ForceModel.CentralBodyGravity.File = "STKData\\CentralBodies\\Moon\\LP100K.grv";
}
//hpop.InitialState.Representation.Assign(orbit);
Console.Write("set epochtime = " + epochDT.ToString("dd MMM yyyy ") + orbitdata[i].epoch_time + "\n");
//set the epoch date/time from the orbit bin file
hpop.InitialState.Representation.Epoch = (epochDT.ToString("dd MMM yyyy ") + orbitdata[i].epoch_time);
Console.Write("set start/stop times = " + (startDT.ToString("dd MMM yyyy ") + orbitdata[i].start_time) + " / " + startDT.AddDays(1).ToString("dd MMM yyyy ") + "\n");
//only proagate the orbit 1 day from the start date/time to get the required data to convert to a Fixed coordnate system
hpop.EphemerisInterval.SetStartAndStopTimes((startDT.ToString("dd MMM yyyy ") + orbitdata[i].start_time), startDT.AddDays(1).ToString("dd MMM yyyy "));
//hpop.EphemerisInterval.SetStartAndStopTimes((startDT.ToString("dd MMM yyyy ") + orbitdata[i].start_time), (endDT.ToString("dd MMM yyyy ") + orbitdata[i].end_time));
hpop.InitialState.Representation.AssignClassical(AgECoordinateSystem.eCoordinateSystemJ2000, orbitdata[i].sma, orbitdata[i].ecc, orbitdata[i].inc, orbitdata[i].aop, orbitdata[i].raan, orbitdata[i].ma);
hpop.Propagate();
//check if the orbit is earth centered and that the
// orbit start date is different from the Mission model date
if (orbitdata[i].centerbody == 1 && orbitdata[i].start_date != startdate)
{
Console.Write("Startdate != orbit_start date converting to Cartesian elements for fixed system" + "\n");
IAgStkObject sat = m_oApplication.CurrentScenario.Children[orbitdata[i].name];
// Get the satellite's ICRF cartesian position at 180 EpSec using the data provider interface
IAgDataProviderGroup dpGroup = sat.DataProviders["Cartesian Position"] as IAgDataProviderGroup;
Array elements = new object[] { "x", "y", "z" };
//***TODO*** find J2000 group instead of ICRF
IAgDataPrvTimeVar dp = dpGroup.Group["ICRF"] as IAgDataPrvTimeVar;
//get the elements at the start date/time of the orbit using in NPAS
IAgDrResult dpResult = dp.ExecSingleElements(hpop.StartTime, ref elements);
Console.Write("hpop.startTime=" + hpop.StartTime + "\n");
double xICRF = (double)dpResult.DataSets[0].GetValues().GetValue(0);
double yICRF = (double)dpResult.DataSets[1].GetValues().GetValue(0);
double zICRF = (double)dpResult.DataSets[2].GetValues().GetValue(0);
// Get the satellite's ICRF cartesian velocity at 180 EpSec using the data provider interface
dpGroup = sat.DataProviders["Cartesian Velocity"] as IAgDataProviderGroup;
//***TODO*** find J2000 group instead of ICRF
dp = dpGroup.Group["ICRF"] as IAgDataPrvTimeVar;
//get the elements at the start date/time of the orbit using in NPAS
dpResult = dp.ExecSingleElements(hpop.StartTime, ref elements);
double xvelICRF = (double)dpResult.DataSets[0].GetValues().GetValue(0);
double yvelICRF = (double)dpResult.DataSets[1].GetValues().GetValue(0);
double zvelICRF = (double)dpResult.DataSets[2].GetValues().GetValue(0);
Console.Write("J2000 cartesian vectors\n");
Console.Write("X=" + xICRF + " Y=" + yICRF + " Z=" + zICRF + "\n");
Console.Write("Xd=" + xvelICRF + " Yd=" + yvelICRF + " Zd=" + zvelICRF + "\n");
// Create a position vector using the ICRF coordinates
IAgCrdnAxes axesICRF = sat.Vgt.WellKnownAxes.Earth.ICRF;
IAgCartesian3Vector vectorICRF = m_oApplication.ConversionUtility.NewCartesian3Vector();
vectorICRF.Set(xICRF, yICRF, zICRF);
// Create a velocity vector using the ICRF coordinates
IAgCartesian3Vector vectorvelICRF = m_oApplication.ConversionUtility.NewCartesian3Vector();
vectorvelICRF.Set(xvelICRF, yvelICRF, zvelICRF);
// Use the TransformWithRate method to transform ICRF to Fixed
IAgCrdnAxes axesFixed = sat.Vgt.WellKnownAxes.Earth.Fixed;
IAgCrdnAxesTransformWithRateResult result = axesICRF.TransformWithRate(hpop.StartTime, axesFixed, vectorICRF, vectorvelICRF);
// Get the Fixed position and velocity coordinates
double xFixed = result.Vector.X;
double yFixed = result.Vector.Y;
double zFixed = result.Vector.Z;
double xvelFixed = result.Velocity.X;
double yvelFixed = result.Velocity.Y;
double zvelFixed = result.Velocity.Z;
Console.Write("converted cartesian vectors" + "\n");
Console.Write("X=" + xFixed + " Y=" + yFixed + " Z=" + zFixed + "\n");
Console.Write("Xd=" + xvelFixed + " Yd=" + yvelFixed + " Zd=" + zvelFixed + "\n");
DateTime start, stop;
start = Convert.ToDateTime(startdate);
stop = Convert.ToDateTime(enddate);
//set the epoch and start date/time to the selected scenario date/time
hpop.InitialState.Representation.Epoch = (start.ToString("dd MMM yyyy "));
hpop.EphemerisInterval.SetStartAndStopTimes((start.ToString("dd MMM yyyy ")), (stop.ToString("dd MMM yyyy ")));
hpop.InitialState.Representation.AssignCartesian(AgECoordinateSystem.eCoordinateSystemFixed, xFixed, yFixed, zFixed, xvelFixed, yvelFixed, zvelFixed);
hpop.InitialState.Representation.Epoch = (start.ToString("dd MMM yyyy "));
hpop.EphemerisInterval.SetStartAndStopTimes((start.ToString("dd MMM yyyy ")), (stop.ToString("dd MMM yyyy ")));
//propagate new orbit
hpop.Propagate();
}
orbitdata[i].Missensor = generate_sensor(orbitdata[i].name, "Stations");
orbitdata[i].MisChain = generate_chain(orbitdata[i].name, "Stations", orbitdata[i].name + "_sensor");
}
else if (orbitdata[i].used == 1 && orbitdata[i].efileused == false)
{
//generate the missions timeline file inside the orignial cod mis name
//don't generate multiple orbits on top of each other;
TL_file_generator(orbitdata[i].name, missionindex[orbitdata[i].cod_id]);
orbitdata[i].MisChain = null;
Console.Write("Misnum != cod_id && orbitdata[i].used == 1 for " + orbitdata[i].name + "\n");
}
else if (orbitdata[i].used == 1 && orbitdata[i].efileused == true)
{
TL_file_generator(orbitdata[i].name, missionindex[orbitdata[i].cod_id]);
orbitdata[i].MisSat = (IAgSatellite)m_oApplication.CurrentScenario.Children.New(AGI.STKObjects.AgESTKObjectType.eSatellite, orbitdata[i].name);
//disable the leading ground track
groundtrack_set(orbitdata[i].MisSat, groundtrack_displayed);
//set the propagator type to STK E file
orbitdata[i].MisSat.SetPropagatorType(AGI.STKObjects.AgEVePropagatorType.ePropagatorStkExternal);
AGI.STKObjects.IAgVePropagatorStkExternal EFileProp = (AGI.STKObjects.IAgVePropagatorStkExternal)orbitdata[i].MisSat.Propagator;
//strip the file name from the entire director name;
EFileProp.Filename = (Efile_directory + orbitdata[i].efilename.Split('/').Last().ToString());
//propagate the efile orbit
EFileProp.Propagate();
//add new sensor to the current sat and change the sensor type to target
orbitdata[i].Missensor = generate_sensor(orbitdata[i].name, "Stations");
//add a new chain for the current sat
orbitdata[i].MisChain = generate_chain(orbitdata[i].name, "Stations", orbitdata[i].name + "_sensor");
}
else
{
orbitdata[i].MisChain = null;
Console.Write("Misnum != cod_id for " + orbitdata[i].name + "\n");
}
}
}
/* This code takes a set of Cartesian coordinates in a fixed frame and converts them into Keplerian orbital elements in an inertial frame
* without using a satellite object (using conversion utility within STK Engine). The Keplerian elements you would like to return can be specified
* by changing the enum values near the top of the Main function.
*/
static void Main(string[] args)
{
AgSTKXApplication app = new AgSTKXApplication();
app.NoGraphics = true;
AgStkObjectRoot root = new AgStkObjectRoot();
// Here are some preliminary variables for the classical coordinate elements you would like to obtain
SizeShapeTypes SizeShapeType = SizeShapeTypes.Altitude;
AscNodeTypes AscNodeType = AscNodeTypes.RAAN;
LocationTypes LocationType = LocationTypes.ArgumentOfLatitude;
// Here we create a new AgOrbitState object
IAgConversionUtility ConversionUtility = root.ConversionUtility;
IAgOrbitState cartesianOrbit = ConversionUtility.NewOrbitStateOnEarth();
// Here is how you display and change the epoch
Console.WriteLine("Epoch:");
cartesianOrbit.Epoch = "1 Jun 2003 17:00:00.000";
Console.WriteLine(cartesianOrbit.Epoch);
// Here we assign whatever Cartesian coordinates we would like to in a fixed frame
cartesianOrbit.AssignCartesian(AgECoordinateSystem.eCoordinateSystemFixed, 5598.42, -14988.6, 4.80738, 3.408, 1.27376, 2.60903);
// Now we convert the orbit to a classical orbit state
IAgOrbitStateClassical classicalOrbit = cartesianOrbit.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
Console.WriteLine(classicalOrbit.CoordinateSystemType);
// Prints out the first two classical orbit elements
switch (SizeShapeType)
{
case SizeShapeTypes.Altitude:
classicalOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeAltitude;
IAgClassicalSizeShapeAltitude sizeShapeAltitude = classicalOrbit.SizeShape as IAgClassicalSizeShapeAltitude;
Console.WriteLine("Apogee Altitude:");
Console.WriteLine(sizeShapeAltitude.ApogeeAltitude);
Console.WriteLine("Perigee Altitude:");
Console.WriteLine(sizeShapeAltitude.PerigeeAltitude);
break;
case SizeShapeTypes.MeanMotion:
classicalOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeMeanMotion;
IAgClassicalSizeShapeMeanMotion sizeShapeMeanMotion = classicalOrbit.SizeShape as IAgClassicalSizeShapeMeanMotion;
Console.WriteLine("Mean Motion:");
Console.WriteLine(sizeShapeMeanMotion.MeanMotion);
Console.WriteLine("Eccentricity:");
Console.WriteLine(sizeShapeMeanMotion.Eccentricity);
break;
case SizeShapeTypes.Period:
classicalOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapePeriod;
IAgClassicalSizeShapePeriod sizeShapePeriod = classicalOrbit.SizeShape as IAgClassicalSizeShapePeriod;
Console.WriteLine("Period:");
Console.WriteLine(sizeShapePeriod.Period);
Console.WriteLine("Eccentricity:");
Console.WriteLine(sizeShapePeriod.Eccentricity);
break;
case SizeShapeTypes.Radius:
classicalOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeRadius;
IAgClassicalSizeShapeRadius sizeShapeRadius = classicalOrbit.SizeShape as IAgClassicalSizeShapeRadius;
Console.WriteLine("Apogee Radius:");
Console.WriteLine(sizeShapeRadius.ApogeeRadius);
Console.WriteLine("Perigee Radius:");
Console.WriteLine(sizeShapeRadius.PerigeeRadius);
break;
case SizeShapeTypes.SemimajorAxis:
classicalOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis sizeShapeSemimajorAxis = classicalOrbit.SizeShape as IAgClassicalSizeShapeSemimajorAxis;
Console.WriteLine("Semimajor Axis:");
Console.WriteLine(sizeShapeSemimajorAxis.SemiMajorAxis);
Console.WriteLine("Eccentricity:");
Console.WriteLine(sizeShapeSemimajorAxis.Eccentricity);
break;
}
// Prints the inclination and argument of perigee
IAgClassicalOrientation orientation = classicalOrbit.Orientation;
Console.WriteLine("Inclination:");
Console.WriteLine(orientation.Inclination);
Console.WriteLine("Argument of Perigee:");
Console.WriteLine(orientation.ArgOfPerigee);
// This section prints the ascending node value
Console.WriteLine("Ascending Node:");
switch (AscNodeType)
{
case AscNodeTypes.RAAN:
orientation.AscNodeType = AgEOrientationAscNode.eAscNodeRAAN;
IAgOrientationAscNodeRAAN ascNodeRAAN = orientation.AscNode as IAgOrientationAscNodeRAAN;
Console.WriteLine(ascNodeRAAN.Value);
break;
case AscNodeTypes.LAN:
orientation.AscNodeType = AgEOrientationAscNode.eAscNodeLAN;
IAgOrientationAscNodeLAN ascNodeLAN = orientation.AscNode as IAgOrientationAscNodeLAN;
Console.WriteLine(ascNodeLAN.Value);
break;
}
// This section prints the location of the satellite along the orbit in terms of whatever you would like
Console.WriteLine("Location:");
switch (LocationType)
{
case LocationTypes.ArgumentOfLatitude:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationArgumentOfLatitude;
IAgClassicalLocationArgumentOfLatitude locationArgumentOfLatitude = classicalOrbit.Location as IAgClassicalLocationArgumentOfLatitude;
Console.WriteLine(locationArgumentOfLatitude.Value);
break;
case LocationTypes.EccentricAnomaly:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationEccentricAnomaly;
IAgClassicalLocationEccentricAnomaly locationSpecificEccentricAnomaly = classicalOrbit.Location as IAgClassicalLocationEccentricAnomaly;
Console.WriteLine(locationSpecificEccentricAnomaly.Value);
break;
case LocationTypes.MeanAnomaly:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationMeanAnomaly;
IAgClassicalLocationMeanAnomaly locationSpecificMeanAnomaly = classicalOrbit.Location as IAgClassicalLocationMeanAnomaly;
Console.WriteLine(locationSpecificMeanAnomaly.Value);
break;
case LocationTypes.TimePastAN:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationTimePastAN;
IAgClassicalLocationTimePastAN locationSpecificTimePastAN = classicalOrbit.Location as IAgClassicalLocationTimePastAN;
Console.WriteLine(locationSpecificTimePastAN.Value);
break;
case LocationTypes.TimePastPerigee:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationTimePastPerigee;
IAgClassicalLocationTimePastPerigee locationSpecificTimePastPerigee = classicalOrbit.Location as IAgClassicalLocationTimePastPerigee;
Console.WriteLine(locationSpecificTimePastPerigee.Value);
break;
case LocationTypes.TrueAnomaly:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
IAgClassicalLocationTrueAnomaly locationTrueAnomaly = classicalOrbit.Location as IAgClassicalLocationTrueAnomaly;
Console.WriteLine(locationTrueAnomaly.Value);
break;
}
Console.ReadLine();
}
//added selected TDRSs into the model
private void add_tdrs(station_str passed)
{
IAgSatellite localtdrs;
localtdrs = (IAgSatellite)m_oApplication.CurrentScenario.Children.New(AGI.STKObjects.AgESTKObjectType.eSatellite, passed.name);
//AGI.STKObjects.IAgSatellite sat = (IAgSatellite)m_oApplication.CurrentScenario.Children.NewOnCentralBody(AGI.STKObjects.AgESTKObjectType.eSatellite, orbitdata[i].name, centerbodyname);
//disable the leading ground track
localtdrs.Graphics.PassData.GroundTrack.SetLeadDataType(AgELeadTrailData.eDataNone);
//disable trailing ground track
localtdrs.Graphics.PassData.GroundTrack.SetTrailDataType(AgELeadTrailData.eDataNone);
localtdrs.VO.Pass.TrackData.PassData.GroundTrack.SetLeadDataType(AgELeadTrailData.eDataNone);
localtdrs.VO.Pass.TrackData.PassData.GroundTrack.SetTrailDataType(AgELeadTrailData.eDataNone);
localtdrs.VO.Pass.TrackData.PassData.Orbit.SetLeadDataType(AgELeadTrailData.eDataNone);
localtdrs.VO.Pass.TrackData.PassData.Orbit.SetTrailDataType(AgELeadTrailData.eDataNone);
//set the propagator type to HPOP
localtdrs.SetPropagatorType(AGI.STKObjects.AgEVePropagatorType.ePropagatorJ2Perturbation);
AGI.STKObjects.IAgVePropagatorJ2Perturbation hpop = (AGI.STKObjects.IAgVePropagatorJ2Perturbation)localtdrs.Propagator;
IAgOrbitState orbit = hpop.InitialState.Representation;
//create the string to hold the missions epoch date & time
string cmb_epoch = startdate, cmb_end = enddate;
cmb_epoch += " 00:00:00";
DateTime epochDT = Convert.ToDateTime(cmb_epoch);
DateTime endepochDT = Convert.ToDateTime(cmb_end);
//hpop.InitialState.Representation.Assign(orbit);
Console.Write("epochtime = " + epochDT.ToString("dd MMM yyyy ") + "00:00:00" + "\n");
hpop.InitialState.Representation.Epoch = (epochDT.ToString("dd MMM yyyy ") + "00:00:00");
// hpop.InitialState.Representation.Assign(ia)
//hpop.InitialState.Representation.AssignClassical(AgECoordinateSystem.eCoordinateSystemJ2000, orbitdata[i].sma, orbitdata[i].ecc, orbitdata[i].inc, orbitdata[i].aop, orbitdata[i].raan, orbitdata[i].ma);
//hpop.Propagate();
IAgOrbitStateClassical classical = (IAgOrbitStateClassical)hpop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical);
classical.CoordinateSystemType = AGI.STKUtil.AgECoordinateSystem.eCoordinateSystemJ2000;
IAgCrdnEventIntervalSmartInterval interval = hpop.EphemerisInterval;
interval.SetExplicitInterval((epochDT.ToString("dd MMM yyyy ") + "00:00:00"), (endepochDT.ToString("dd MMM yyyy ") + "00:00:00"));
hpop.Step = 60;
classical.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
IAgClassicalLocationTrueAnomaly trueAnomaly = (IAgClassicalLocationTrueAnomaly)classical.Location;
trueAnomaly.Value = 178.845262;
classical.SizeShapeType = AgEClassicalSizeShape.eSizeShapePeriod;
IAgClassicalSizeShapePeriod period = (IAgClassicalSizeShapePeriod)classical.SizeShape;
period.Eccentricity = 0.0;
period.Period = 86164.090540;
classical.Orientation.ArgOfPerigee = 0.0;
classical.Orientation.Inclination = 0.0;
classical.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeLAN;
IAgOrientationAscNodeLAN lan = (IAgOrientationAscNodeLAN)classical.Orientation.AscNode;
lan.Value = (360 - passed.lon);
hpop.InitialState.Representation.Assign(classical);
hpop.Propagate();
}