public static double[] GetRICDifferenceAtTCA(string sat1Path, string sat2Path, string epochISOYMD)
{
IAgStkObject primary, secondary;
try
{
primary = StkAssistant.Root.GetObjectFromPath(sat1Path);
secondary = StkAssistant.Root.GetObjectFromPath(sat2Path);
}
catch
{
return(null);
}
IAgDataProviderInfo dpInfo = primary.DataProviders["RIC Coordinates"];
IAgDataProvider dataProvider = primary.DataProviders["RIC Coordinates"] as IAgDataProvider;
dataProvider.PreData = secondary.Path.Replace(StkAssistant.Root.CurrentScenario.Path, "");
IAgDataPrvTimeVar dpTimeVarying = dataProvider as IAgDataPrvTimeVar;
Array elements = new object[] { "Radial", "In-Track", "Cross-Track" };
IAgDrResult dpResult = dpTimeVarying.ExecSingleElements(epochISOYMD, elements);
double[] ric = new double[3];
ric[0] = (double)dpResult.DataSets[0].GetValues().GetValue(0);
ric[1] = (double)dpResult.DataSets[1].GetValues().GetValue(0);
ric[2] = (double)dpResult.DataSets[2].GetValues().GetValue(0);
return(ric);
}
public static double GetSatellitePerigee(string satPath, string dateISOYMD)
{
IAgDataPrvTimeVar dpTimeVarying = GetClassicalElementsDP(satPath);
Array elements = new object[] { "Perigee Radius" };
IAgDrResult dpResult = dpTimeVarying.ExecSingleElements(dateISOYMD, elements);
double perigee = (double)dpResult.DataSets.GetDataSetByName(elements.GetValue(0).ToString()).GetValues().GetValue(0);
return(perigee);
}
void Root_OnAnimUpdate(double timeEpSec)
{
// Gather data and update the text boxes
IAgDrResult result = m_accessProviderIntervals.ExecSingleElements(timeEpSec, ref m_dataProviderElements);
if (result.Intervals.Count > 0)
{
Array azimuth = result.Intervals[0].DataSets.GetDataSetByName("Azimuth").GetValues();
Array elevation = result.Intervals[0].DataSets.GetDataSetByName("Elevation").GetValues();
SetResponseText(textBoxAzimuth, azimuth.GetValue(0).ToString());
SetResponseText(textBoxElevation, elevation.GetValue(0).ToString());
}
else
{
SetResponseText(textBoxAzimuth, "No Values");
SetResponseText(textBoxElevation, "No Values");
}
}
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");
}
}
}
