private void DisplaySelected_Click(object sender, EventArgs e)
{
if (listView1.FocusedItem != null && listView1.FocusedItem.Index != -1)
{
if (CommonData.HasManeuvers)
{
IAgStkObject passiveSatObj = CreatorFunctions.GetCreateSatellite("PassiveCheck");
IAgSatellite passiveSat = passiveSatObj as IAgSatellite;
passiveSat.VO.OrbitSystems.InertialByWindow.IsVisible = false;
passiveSat.VO.OrbitSystems.RemoveAll();
passiveSat.VO.OrbitSystems.Add("Satellite/" + CommonData.TargetName + " VVLH System");
passiveSat.SetPropagatorType(AgEVePropagatorType.ePropagatorAstrogator);
IAgVADriverMCS passiveDriver = passiveSat.Propagator as IAgVADriverMCS;
IAgVAMCSInitialState intState = passiveDriver.MainSequence[0] as IAgVAMCSInitialState;
IAgVAMCSPropagate prop = passiveDriver.MainSequence[1] as IAgVAMCSPropagate;
IAgVAStoppingConditionElement sc1 = prop.StoppingConditions[0];
IAgVAStoppingCondition sc = sc1.Properties as IAgVAStoppingCondition;
sc.Trip = CommonData.RunList[listView1.FocusedItem.Index].PropTime;
AgVAElementCartesian element = intState.Element as AgVAElementCartesian;
intState.OrbitEpoch = CommonData.RunList[listView1.FocusedItem.Index].ManeuverTime;
element.Vx = CommonData.RunList[listView1.FocusedItem.Index].Vx;
element.Vy = CommonData.RunList[listView1.FocusedItem.Index].Vy;
element.Vz = CommonData.RunList[listView1.FocusedItem.Index].Vz;
element.X = CommonData.RunList[listView1.FocusedItem.Index].X;
element.Y = CommonData.RunList[listView1.FocusedItem.Index].Y;
element.Z = CommonData.RunList[listView1.FocusedItem.Index].Z;
passiveDriver.RunMCS();
}
else
{
MessageBox.Show("Actor satellite has no maneuvers. Visualization is simply the Actor's current trjectory");
}
}
}
//Main Function
private void Generate_Click(object sender, EventArgs e)
{
int check = FieldCheck();
if (check == 0)
{
RemoveProximityGeometry();
try
{
CommonData.StkRoot.UnitPreferences.SetCurrentUnit("Distance", "km");
CommonData.RunList.Clear();
CommonData.TargetName = TargetSat.Text;
CommonData.ActorName = ActorSat.Text;
//Set user bounds for safety
double userMinRange = Double.Parse(SphericalMag.Text) / 1000;
double userMinR = Double.Parse(RMag.Text) / 1000;
double userMinI = Double.Parse(IMag.Text) / 1000;
double userMinC = Double.Parse(CMag.Text) / 1000;
IAgScenario scenario = CommonData.StkRoot.CurrentScenario as IAgScenario;
IAgStkObject satObj = CommonData.StkRoot.GetObjectFromPath("Satellite/" + ActorSat.Text);
IAgSatellite sat = satObj as IAgSatellite;
//Get all maneuver end times for actor satellite
IAgDataProviderGroup maneuverDpGroup = satObj.DataProviders["Astrogator Maneuver Ephemeris Block Final"] as IAgDataProviderGroup;
IAgDataPrvTimeVar maneuverDp = maneuverDpGroup.Group["Cartesian Elems"] as IAgDataPrvTimeVar;
IAgDrResult result = maneuverDp.Exec(scenario.StartTime, scenario.StopTime, 60);
IAgDrDataSetCollection maneuverData = result.DataSets;
//If there is maneuvers, run iterations for each maneuver. If no maneuvers then just pull closest RIC data for entire trajectory
if (maneuverData.Count != 0)
{
CommonData.HasManeuvers = true;
//Get maneuver numbers
IAgDataPrvInterval summaryDp = satObj.DataProviders["Maneuver Summary"] as IAgDataPrvInterval;
IAgDrResult summaryResult = summaryDp.Exec(scenario.StartTime, scenario.StopTime);
Array maneuverNumbers = summaryResult.DataSets.GetDataSetByName("Maneuver Number").GetValues();
int maxManeuverNum = maneuverNumbers.Length;
//Get handles to cartesian position and velocity to seed passive safety runs
IAgDataProviderGroup cartPos = satObj.DataProviders["Cartesian Position"] as IAgDataProviderGroup;
IAgDataPrvTimeVar cartPosDP = cartPos.Group["ICRF"] as IAgDataPrvTimeVar;
IAgDataProviderGroup cartVel = satObj.DataProviders["Cartesian Velocity"] as IAgDataProviderGroup;
IAgDataPrvTimeVar cartVelDP = cartVel.Group["ICRF"] as IAgDataPrvTimeVar;
//Create passive safety satellite. Set to Astrogator and pull handles to initial state and propagate segments
IAgStkObject passiveSatObj = CreatorFunctions.GetCreateSatellite("PassiveCheck");
IAgSatellite passiveSat = passiveSatObj as IAgSatellite;
passiveSat.SetPropagatorType(AgEVePropagatorType.ePropagatorAstrogator);
IAgVADriverMCS passiveDriver = passiveSat.Propagator as IAgVADriverMCS;
IAgVAMCSInitialState intState = passiveDriver.MainSequence[0] as IAgVAMCSInitialState;
IAgVAMCSPropagate prop = passiveDriver.MainSequence[1] as IAgVAMCSPropagate;
IAgVAStoppingConditionElement sc1 = prop.StoppingConditions[0];
IAgVAStoppingCondition sc = sc1.Properties as IAgVAStoppingCondition;
sc.Trip = PropTime.Text;
AgVAElementCartesian element = intState.Element as AgVAElementCartesian;
Array epoch;
Array vx;
Array vy;
Array vz;
Array x;
Array y;
Array z;
String epochCur;
DateTime dateCur;
//Assign cartesian elements to PassiveCheck satellite from actor maneuver maneuver data. Run each iteration to see if resulting trajectory violates constraints
for (int i = 0; i < maxManeuverNum; i++)
{
//Get maneuver time and offset in time by 0.25 sec to account for boundrary conditions around impulsive maneuvers
epoch = maneuverData[0 + (i * 7)].GetValues();
epochCur = epoch.GetValue(0).ToString();
dateCur = DateTime.Parse(epochCur);
dateCur = dateCur.AddMilliseconds(250);
//dateCur = DateTime.ParseExact(epochCur, "dd MMM yyyy HH:mm:ss.fff", CultureInfo.InvariantCulture);
epochCur = dateCur.ToString("dd MMM yyyy HH:mm:ss.fff");
//Get cartesian state vector for given time
result = cartPosDP.ExecSingle(epochCur);
x = result.DataSets.GetDataSetByName("x").GetValues();
y = result.DataSets.GetDataSetByName("y").GetValues();
z = result.DataSets.GetDataSetByName("z").GetValues();
result = cartVelDP.ExecSingle(epochCur);
vx = result.DataSets.GetDataSetByName("x").GetValues();
vy = result.DataSets.GetDataSetByName("y").GetValues();
vz = result.DataSets.GetDataSetByName("z").GetValues();
//Create passive run output to be used in visualization
PassiveRun run = new PassiveRun();
run.UserMinRange = Double.Parse(SphericalMag.Text) / 1000;
run.UserMinR = Double.Parse(RMag.Text) / 1000;
run.UserMinI = Double.Parse(IMag.Text) / 1000;
run.UserMinC = Double.Parse(CMag.Text) / 1000;
intState.OrbitEpoch = epochCur;
element.Vx = Double.Parse(vx.GetValue(0).ToString());
element.Vy = Double.Parse(vy.GetValue(0).ToString());
element.Vz = Double.Parse(vz.GetValue(0).ToString());
element.X = Double.Parse(x.GetValue(0).ToString());
element.Y = Double.Parse(y.GetValue(0).ToString());
element.Z = Double.Parse(z.GetValue(0).ToString());
passiveDriver.RunMCS();
run.Vx = Double.Parse(vx.GetValue(0).ToString());
run.Vy = Double.Parse(vy.GetValue(0).ToString());
run.Vz = Double.Parse(vz.GetValue(0).ToString());
run.X = Double.Parse(x.GetValue(0).ToString());
run.Y = Double.Parse(y.GetValue(0).ToString());
run.Z = Double.Parse(z.GetValue(0).ToString());
run.PropTime = Double.Parse(PropTime.Text);
//Pull closest point to target for each iteration and save to passive run output
IAgDataProvider psatDp = passiveSatObj.DataProviders["RIC Coordinates"] as IAgDataProvider;
psatDp.PreData = "Satellite/" + TargetSat.Text;
IAgDataPrvTimeVar psatDpTimeVar = psatDp as IAgDataPrvTimeVar;
IAgDrResult psatDp2 = psatDpTimeVar.Exec(scenario.StartTime, scenario.StopTime, Double.Parse(TimeStep.Text));
run.Range = psatDp2.DataSets.GetDataSetByName("Range").GetValues();
run.Intrack = psatDp2.DataSets.GetDataSetByName("In-Track").GetValues();
run.Crosstrack = psatDp2.DataSets.GetDataSetByName("Cross-Track").GetValues();
run.Radial = psatDp2.DataSets.GetDataSetByName("Radial").GetValues();
run.MinRange = MathFunctions.ArrayMin(run.Range);
run.MinIntrack = MathFunctions.ArrayMinAbs(run.Intrack);
run.MinCrosstrack = MathFunctions.ArrayMinAbs(run.Crosstrack);
run.MinRadial = MathFunctions.ArrayMinAbs(run.Radial);
//run.ManeuverTime = epoch.GetValue(0).ToString();
run.ManeuverTime = epochCur;
//spherical
if (radioButton1.Checked)
{
run.IsSpherical = true;
if (run.MinRange < userMinRange)
{
run.Safe = false;
}
else
{
run.Safe = true;
}
}
//independent axis
else
{
run.IsSpherical = false;
if (Math.Abs(run.MinIntrack) < userMinI && Math.Abs(run.MinRadial) < userMinR && Math.Abs(run.MinCrosstrack) < userMinC)
{
bool tripped = false;
for (int j = 0; j < run.Range.Length; j++)
{
if (Math.Abs(Double.Parse(run.Intrack.GetValue(j).ToString())) < userMinI && Math.Abs(Double.Parse(run.Radial.GetValue(j).ToString())) < userMinR && Math.Abs(Double.Parse(run.Crosstrack.GetValue(j).ToString())) < userMinC)
{
run.Safe = false;
tripped = true;
break;
}
}
if (!tripped)
{
run.Safe = true;
}
}
else
{
run.Safe = true;
}
}
CommonData.RunList.Add(run);
}
}
else
{
CommonData.HasManeuvers = false;
PassiveRun run = new PassiveRun();
IAgDataProvider satDp = satObj.DataProviders["RIC Coordinates"] as IAgDataProvider;
satDp.PreData = "Satellite/" + TargetSat.Text;
IAgDataPrvTimeVar satDpTimeVar = satDp as IAgDataPrvTimeVar;
IAgDrResult satDp2 = satDpTimeVar.Exec(scenario.StartTime, scenario.StopTime, Double.Parse(TimeStep.Text));
run.Range = satDp2.DataSets.GetDataSetByName("Range").GetValues();
run.Intrack = satDp2.DataSets.GetDataSetByName("In-Track").GetValues();
run.Crosstrack = satDp2.DataSets.GetDataSetByName("Cross-Track").GetValues();
run.Radial = satDp2.DataSets.GetDataSetByName("Radial").GetValues();
run.MinRange = MathFunctions.ArrayMin(run.Range);
run.MinIntrack = MathFunctions.ArrayMinAbs(run.Intrack);
run.MinCrosstrack = MathFunctions.ArrayMinAbs(run.Crosstrack);
run.MinRadial = MathFunctions.ArrayMinAbs(run.Radial);
run.ManeuverTime = "N/A";
//spherical
if (radioButton1.Checked)
{
run.IsSpherical = true;
if (run.MinRange < userMinRange)
{
run.Safe = false;
}
else
{
run.Safe = true;
}
}
//independent axis
else
{
run.IsSpherical = false;
if (Math.Abs(run.MinIntrack) < userMinI && Math.Abs(run.MinRadial) < userMinR && Math.Abs(run.MinCrosstrack) < userMinC)
{
bool tripped = false;
for (int j = 0; j < run.Range.Length; j++)
{
if (Math.Abs(Double.Parse(run.Intrack.GetValue(j).ToString())) < userMinI && Math.Abs(Double.Parse(run.Radial.GetValue(j).ToString())) < userMinR && Math.Abs(Double.Parse(run.Crosstrack.GetValue(j).ToString())) < userMinC)
{
run.Safe = false;
tripped = true;
break;
}
}
if (!tripped)
{
run.Safe = true;
}
}
else
{
run.Safe = true;
}
}
CommonData.RunList.Add(run);
}
CommonData.BeenRun = true;
}
catch (Exception)
{
MessageBox.Show("Passive Safety Check Failed");
}
}
}
public static PropagationResults PropagateAstrogatorSatellite(AgStkObjectRoot root, AgUiApplication app, InitialState state, TLE tle, Data satData, Uncertainty uncertainty, int runId, int nRuns, string propName)
{
PropagationResults propResults = new PropagationResults();
propResults.RunNumber = runId.ToString().PadLeft(3, '0');
IAgSatellite sat = root.CurrentScenario.Children.New(AgESTKObjectType.eSatellite, tle.GetSatNumber() + "Astrogator") as IAgSatellite;
//Set the propagator to Astrogator
sat.SetPropagatorType(AgEVePropagatorType.ePropagatorAstrogator);
//get the Driver for the Propagator
IAgVADriverMCS driver = sat.Propagator as IAgVADriverMCS;
//Clear all segments from the MCS
driver.MainSequence.RemoveAll();
//// Target Sequence ////
IAgVAMCSTargetSequence ts = driver.MainSequence.Insert(AgEVASegmentType.eVASegmentTypeTargetSequence, "SetupState", "-") as IAgVAMCSTargetSequence;
ts.Action = AgEVATargetSeqAction.eVATargetSeqActionRunActiveProfiles;
// add the initial state segment in the target sequence
IAgVAMCSInitialState initState = ts.Segments.Insert(AgEVASegmentType.eVASegmentTypeInitialState, "InitialState", "-") as IAgVAMCSInitialState;
initState.OrbitEpoch = ((IAgScenario)root.CurrentScenario).StartTime;
// define elements
initState.SetElementType(AgEVAElementType.eVAElementTypeCartesian);
IAgVAElementCartesian cart = initState.Element as IAgVAElementCartesian;
cart.X = Convert.ToDouble(state.CartesianPosX);
cart.Y = Convert.ToDouble(state.CartesianPosY);
cart.Z = Convert.ToDouble(state.CartesianPosZ);
cart.Vx = Convert.ToDouble(state.CartesianVelX);
cart.Vy = Convert.ToDouble(state.CartesianVelY);
cart.Vz = Convert.ToDouble(state.CartesianVelZ);
// spacecraft parameters
IAgVASpacecraftParameters spacecraftParameters = (IAgVASpacecraftParameters)initState.SpacecraftParameters;
spacecraftParameters.DryMass = satData.Mass;
spacecraftParameters.Cd = satData.Cd;
spacecraftParameters.DragArea = satData.DragArea;
spacecraftParameters.Cr = satData.Cr;
spacecraftParameters.SolarRadiationPressureArea = satData.SunArea;
spacecraftParameters.RadiationPressureArea = 1e-10;
IAgVAFuelTank fuelTank = (IAgVAFuelTank)initState.FuelTank;
fuelTank.FuelMass = 0;
// enable the control parameter for the state variables
initState.EnableControlParameter(AgEVAControlInitState.eVAControlInitStateCartesianX);
initState.EnableControlParameter(AgEVAControlInitState.eVAControlInitStateCartesianY);
initState.EnableControlParameter(AgEVAControlInitState.eVAControlInitStateCartesianZ);
initState.EnableControlParameter(AgEVAControlInitState.eVAControlInitStateCartesianVx);
initState.EnableControlParameter(AgEVAControlInitState.eVAControlInitStateCartesianVy);
initState.EnableControlParameter(AgEVAControlInitState.eVAControlInitStateCartesianVz);
// add the results
((IAgVAMCSSegment)initState).Results.Add("Relative Motion/InTrack");
IAgVAStateCalcRelMotion intrackRel = ((IAgVAMCSSegment)initState).Results[0] as IAgVAStateCalcRelMotion;
intrackRel.ReferenceSelection = AgEVACalcObjectReference.eVACalcObjectReferenceSpecified;
IAgLinkToObject link_1 = intrackRel.Reference as IAgLinkToObject;
link_1.BindTo("Satellite/" + tle.GetSatNumber().ToString());
((IAgVAMCSSegment)initState).Results.Add("Relative Motion/Radial");
IAgVAStateCalcRelMotion radialRel = ((IAgVAMCSSegment)initState).Results[1] as IAgVAStateCalcRelMotion;
radialRel.ReferenceSelection = AgEVACalcObjectReference.eVACalcObjectReferenceSpecified;
IAgLinkToObject link_2 = radialRel.Reference as IAgLinkToObject;
link_2.BindTo("Satellite/" + tle.GetSatNumber().ToString());
((IAgVAMCSSegment)initState).Results.Add("Relative Motion/CrossTrack");
IAgVAStateCalcRelMotion crosstrackRel = ((IAgVAMCSSegment)initState).Results[2] as IAgVAStateCalcRelMotion;
crosstrackRel.ReferenceSelection = AgEVACalcObjectReference.eVACalcObjectReferenceSpecified;
IAgLinkToObject link_3 = crosstrackRel.Reference as IAgLinkToObject;
link_3.BindTo("Satellite/" + tle.GetSatNumber().ToString());
((IAgVAMCSSegment)initState).Results.Add("Relative Motion/InTrackRate");
IAgVAStateCalcRelMotion intrackrateRel = ((IAgVAMCSSegment)initState).Results[3] as IAgVAStateCalcRelMotion;
intrackrateRel.ReferenceSelection = AgEVACalcObjectReference.eVACalcObjectReferenceSpecified;
IAgLinkToObject link_4 = intrackrateRel.Reference as IAgLinkToObject;
link_4.BindTo("Satellite/" + tle.GetSatNumber().ToString());
((IAgVAMCSSegment)initState).Results.Add("Relative Motion/RadialRate");
IAgVAStateCalcRelMotion radialrateRel = ((IAgVAMCSSegment)initState).Results[4] as IAgVAStateCalcRelMotion;
radialrateRel.ReferenceSelection = AgEVACalcObjectReference.eVACalcObjectReferenceSpecified;
IAgLinkToObject link_5 = radialrateRel.Reference as IAgLinkToObject;
link_5.BindTo("Satellite/" + tle.GetSatNumber().ToString());
((IAgVAMCSSegment)initState).Results.Add("Relative Motion/CrossTrackRate");
IAgVAStateCalcRelMotion crosstrackrateRel = ((IAgVAMCSSegment)initState).Results[5] as IAgVAStateCalcRelMotion;
crosstrackrateRel.ReferenceSelection = AgEVACalcObjectReference.eVACalcObjectReferenceSpecified;
IAgLinkToObject link_6 = crosstrackrateRel.Reference as IAgLinkToObject;
link_6.BindTo("Satellite/" + tle.GetSatNumber().ToString());
/// differential corrector setup ///
IAgVAProfileDifferentialCorrector dc = ts.Profiles["Differential Corrector"] as IAgVAProfileDifferentialCorrector;
// control parameters
IAgVADCControl xControlParam = dc.ControlParameters.GetControlByPaths("InitialState", "InitialState.Cartesian.X");
xControlParam.Enable = true;
xControlParam.MaxStep = 1;
xControlParam.Perturbation = 0.1;
IAgVADCControl yControlParam = dc.ControlParameters.GetControlByPaths("InitialState", "InitialState.Cartesian.Y");
yControlParam.Enable = true;
yControlParam.MaxStep = 1;
yControlParam.Perturbation = 0.1;
IAgVADCControl zControlParam = dc.ControlParameters.GetControlByPaths("InitialState", "InitialState.Cartesian.Z");
zControlParam.Enable = true;
zControlParam.MaxStep = 1;
zControlParam.Perturbation = 0.1;
IAgVADCControl vxControlParam = dc.ControlParameters.GetControlByPaths("InitialState", "InitialState.Cartesian.Vx");
vxControlParam.Enable = true;
vxControlParam.MaxStep = 0.001;
vxControlParam.Perturbation = 1e-04;
IAgVADCControl vyControlParam = dc.ControlParameters.GetControlByPaths("InitialState", "InitialState.Cartesian.Vy");
vyControlParam.Enable = true;
vyControlParam.MaxStep = 0.001;
vyControlParam.Perturbation = 1e-04;
IAgVADCControl vzControlParam = dc.ControlParameters.GetControlByPaths("InitialState", "InitialState.Cartesian.Vz");
vzControlParam.Enable = true;
vzControlParam.MaxStep = 0.001;
vzControlParam.Perturbation = 1e-04;
// results
double[] deviations = uncertainty.GetRandomDeviation();
IAgVADCResult intrackResult = dc.Results.GetResultByPaths("InitialState", "InTrack");
intrackResult.Enable = true;
intrackResult.DesiredValue = deviations[0];
intrackResult.Tolerance = 0.01;
IAgVADCResult radialResult = dc.Results.GetResultByPaths("InitialState", "Radial");
radialResult.Enable = true;
radialResult.DesiredValue = deviations[1];
radialResult.Tolerance = 0.01;
IAgVADCResult crosstrackResult = dc.Results.GetResultByPaths("InitialState", "CrossTrack");
crosstrackResult.Enable = true;
crosstrackResult.DesiredValue = deviations[2];
crosstrackResult.Tolerance = 0.01;
IAgVADCResult intrackRateResult = dc.Results.GetResultByPaths("InitialState", "InTrackRate");
intrackRateResult.Enable = true;
intrackRateResult.DesiredValue = deviations[3] / 1000;
intrackRateResult.Tolerance = 0.001;
IAgVADCResult radialRateResult = dc.Results.GetResultByPaths("InitialState", "RadialRate");
radialRateResult.Enable = true;
radialRateResult.DesiredValue = deviations[4] / 1000;
radialRateResult.Tolerance = 0.001;
IAgVADCResult crosstrackRateResult = dc.Results.GetResultByPaths("InitialState", "CrossTrackRate");
crosstrackRateResult.Enable = true;
crosstrackRateResult.DesiredValue = deviations[5] / 1000;
crosstrackRateResult.Tolerance = 0.001;
/// Propagator ///
IAgVAMCSPropagate propagate = driver.MainSequence.Insert(AgEVASegmentType.eVASegmentTypePropagate, "ToGround", "-") as IAgVAMCSPropagate;
((IAgVAMCSSegment)propagate).Properties.Color = Color.Red;
//propagate.PropagatorName = "CustomProp";
propagate.PropagatorName = propName;
// add an Epoch stopping condition
IAgVAStoppingConditionCollection propStoppingConditions = propagate.StoppingConditions as IAgVAStoppingConditionCollection;
IAgVAStoppingConditionElement epochElement = propStoppingConditions.Add("Epoch");
IAgVAStoppingCondition epoch = (IAgVAStoppingCondition)epochElement.Properties;
epoch.Trip = ((IAgScenario)root.CurrentScenario).StopTime;
// add an Altitude stopping condition
IAgVAStoppingConditionElement altitudeElement = propStoppingConditions.Add("Altitude");
IAgVAStoppingCondition altitude = (IAgVAStoppingCondition)altitudeElement.Properties;
altitude.Trip = 0;
// remove the original stopping condition
propagate.StoppingConditions.Remove("Duration");
// run the MCS
driver.RunMCS();
driver.ClearDWCGraphics();
// get the stop time
IAgDataPrvInterval dp = ((IAgStkObject)sat).DataProviders.GetDataPrvIntervalFromPath("Astrogator MCS Ephemeris Segments") as IAgDataPrvInterval;
IAgDrResult result = dp.Exec(((IAgScenario)root.CurrentScenario).StartTime, ((IAgScenario)root.CurrentScenario).StopTime);
string satStopTime = result.DataSets[3].GetValues().GetValue(1).ToString();
if (satStopTime.Equals((Convert.ToString(((IAgScenario)root.CurrentScenario).StopTime))))
{
// the satellite does not decay (it is propagated until the scenario stop time)
propResults.IsDecayed = false;
}
else
{
propResults.IsDecayed = true;
propResults.ImpactEpoch = satStopTime;
// remove the millisecond part
satStopTime = satStopTime.Split('.')[0];
//ask for LLA data at stop time
IAgDataPrvTimeVar dpInfo = ((IAgStkObject)sat).DataProviders.GetDataPrvInfoFromPath("LLA State//Fixed") as IAgDataPrvTimeVar;
IAgDrResult resInfo = dpInfo.ExecSingle(satStopTime);
string lat = resInfo.DataSets[1].GetValues().GetValue(0).ToString();
string lon = resInfo.DataSets[2].GetValues().GetValue(0).ToString();
string alt = resInfo.DataSets[3].GetValues().GetValue(0).ToString();
propResults.ImpactLat = lat;
propResults.ImpactLon = lon;
propResults.ImpactAlt = alt;
// create a target object
IAgTarget target = root.CurrentScenario.Children.New(AgESTKObjectType.eTarget, "Target" + (runId).ToString().PadLeft(3, '0')) as IAgTarget;
target.Graphics.Color = Color.Red;
target.Graphics.LabelVisible = false;
IAgPosition pos = target.Position;
pos.AssignGeodetic(lat, lon, 0);
// create and display the time event
IAgCrdnProvider provider = root.CurrentScenario.Children["Target" + (runId).ToString().PadLeft(3, '0')].Vgt;
IAgCrdnEventEpoch eventEpoch = provider.Events.Factory.CreateEventEpoch(runId.ToString().PadLeft(3, '0') + "_Impact", "Impact Epoch") as IAgCrdnEventEpoch;
eventEpoch.Epoch = satStopTime;
try { root.ExecuteCommand("Timeline * TimeComponent Add ContentView \"Scenario Availability\" \"Target/Target" + (runId).ToString().PadLeft(3, '0') + " " + runId.ToString().PadLeft(3, '0') + "_Impact Time Instant\""); }
catch (Exception) { }
root.ExecuteCommand("Timeline * Refresh");
// create a unique ephemeris file for each Astrogator run
DateTime now = DateTime.Now;
string satEphemerisPath = Directory.GetCurrentDirectory() + "\\Ephemeris\\Reentry_run_" + (runId).ToString().PadLeft(3, '0') + ".e";
root.ExecuteCommand("ExportDataFile */Satellite/" + tle.GetSatNumber() + "Astrogator Ephemeris \"" + satEphemerisPath + "\" Type STK CoordSys ICRF CentralBody Earth InterpBoundaries Include");
propResults.EphemerisFilePath = satEphemerisPath;
// unload Astrogator satellite
root.CurrentScenario.Children[tle.GetSatNumber() + "Astrogator"].Unload();
if (runId == nRuns)
{
// remove the TLE sat
// root.CurrentScenario.Children[tle.GetSatNumber()].Unload();
}
}
try
{
AGI.Ui.Core.IAgUiWindowsCollection windows = app.Windows;
foreach (dynamic window in app.Windows)
{
string windowCaption = (string)window.Caption;
if (windowCaption.Contains("Setup"))
{
window.Close();
}
}
}
catch (Exception ex)
{
}
return(propResults);
}
