public static bool Is_Error_Propagator(IAgVePropagatorJ2Perturbation prop, ref string type)
{
// returns true if there is an error with propagator and "type" what was issue
// returns false if there isn't an error and will propagate
if (IsCircular(prop) && IsApogeeAboveGround(prop) && IsPerigeePositive(prop))
{
prop.Propagate();
return(false);
}
else if (!IsCircular(prop))
{
type = "Parabolic or hyperbolic orbit";
}
else if (!IsApogeeAboveGround(prop))
{
type = "Apogee too low";
}
else
{
type = "Perigee too low";
}
return(true);
}
public static bool UpdateDelaunayOrbit(IAgSatellite sat, double lD, double gD, double hD, double LD, double GD, double HD, ref string error)
{
IAgVePropagatorJ2Perturbation prop = sat.Propagator as IAgVePropagatorJ2Perturbation;
// there is no AssignDelaunay so we need to do this one at a time
IAgOrbitStateDelaunay delaunay = prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateDelaunay) as IAgOrbitStateDelaunay;
delaunay.MeanAnomaly = lD;
delaunay.ArgOfPeriapsis = gD;
delaunay.RAAN = hD;
delaunay.LType = AgEDelaunayLType.eL;
IAgDelaunayL delaunayL = delaunay.L as IAgDelaunayL;
delaunayL.L = LD;
delaunay.GType = AgEDelaunayGType.eG;
IAgDelaunayG delaunayG = delaunay.G as IAgDelaunayG;
delaunayG.G = GD;
delaunay.HType = AgEDelaunayHType.eH;
IAgDelaunayH delaunayH = delaunay.H as IAgDelaunayH;
delaunayH.H = HD;
prop.InitialState.Representation.Assign(delaunay);
return(Is_Error_Propagator(prop, ref error));
}
public static bool UpdateCartesianOrbit(IAgSatellite sat, double x, double y, double z, double dx, double dy, double dz, ref string error)
{
IAgVePropagatorJ2Perturbation prop = sat.Propagator as IAgVePropagatorJ2Perturbation;
prop.InitialState.Representation.AssignCartesian(AgECoordinateSystem.eCoordinateSystemICRF, x, y, z, dx, dy, dz);
return(Is_Error_Propagator(prop, ref error));
}
public static bool UpdateMixedSphericalOrbit(IAgSatellite sat, double lonM, double latM, double altM, double fpaM, double azM, double velM, ref string error)
{
IAgVePropagatorJ2Perturbation prop = sat.Propagator as IAgVePropagatorJ2Perturbation;
prop.InitialState.Representation.AssignMixedSpherical(AgECoordinateSystem.eCoordinateSystemICRF, latM, lonM, altM, fpaM, azM, velM);
return(Is_Error_Propagator(prop, ref error));
}
public static bool UpdateSphericalOrbit(IAgSatellite sat, double raS, double decS, double radS, double fpaS, double azS, double velS, ref string error)
{
IAgVePropagatorJ2Perturbation prop = sat.Propagator as IAgVePropagatorJ2Perturbation;
prop.InitialState.Representation.AssignSpherical(AgECoordinateSystem.eCoordinateSystemICRF, raS, decS, radS, fpaS, azS, velS);
return(Is_Error_Propagator(prop, ref error));
}
//Uses a satellite object to create a time component if AWB is not available
public static void CreateTimelineComponentNoAwb(GroundEvent currentGroundEvent)
{
IAgSatellite sat;
string mes = null;
bool error = false;
string satName = "z" + currentGroundEvent.Id + "-TimelineObject";
try
{
string cmd1 = "Timeline * TimeComponent Remove ContentView \"Event_Timeline\" \"Satellite/" + satName + " AvailabilityTimeSpan Interval\"";
CommonData.StkRoot.ExecuteCommand(cmd1);
}
catch (Exception)
{
}
IAgExecCmdResult result = CommonData.StkRoot.ExecuteCommand("DoesObjExist / */Satellite/" + satName);
if (result[0] == "0")
{
sat = CommonData.StkRoot.CurrentScenario.Children.New(AgESTKObjectType.eSatellite, satName) as IAgSatellite;
}
else
{
sat = CommonData.StkRoot.GetObjectFromPath("Satellite/" + satName) as IAgSatellite;
}
try
{
((IAgSatellite)sat).SetPropagatorType(AgEVePropagatorType.ePropagatorJ2Perturbation);
IAgVePropagatorJ2Perturbation prop = sat.Propagator as IAgVePropagatorJ2Perturbation;
prop.EphemerisInterval.SetExplicitInterval(currentGroundEvent.StartTime, currentGroundEvent.StopTime);
prop.Propagate();
}
catch (Exception)
{
error = true;
mes = "Error with " + currentGroundEvent.Id + ": Could not update or create time component- Error with Start or Stop Time";
}
sat.Graphics.IsObjectGraphicsVisible = false;
try
{
string cmd = "Timeline * TimeComponent Add ContentView \"Event_Timeline\" DisplayName \"" + currentGroundEvent.Id + "-Interval\" \"Satellite/" + satName + " AvailabilityTimeSpan Interval\"";
CommonData.StkRoot.ExecuteCommand(cmd);
}
catch (Exception)
{
error = true;
mes = "Error with " + currentGroundEvent.Id + ": Could not update or create time component- Error with Start or Stop Time";
}
CommonData.StkRoot.ExecuteCommand("Timeline * Refresh");
if (error)
{
MessageBox.Show(mes);
}
}
// check if the resulting orbit is circular or parabolic/hyperbolic
private static bool IsCircular(IAgVePropagatorJ2Perturbation prop)
{
IAgOrbitStateClassical testOrbit = prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
testOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis testSizeShape = testOrbit.SizeShape as IAgClassicalSizeShapeSemimajorAxis;
if (testSizeShape.Eccentricity < 1.0)
{
return(true);
}
return(false);
}
public void set_InitStateJx(object InitStateObj, string name, double value)
{
if (name == "SemiMajorAxis")
{
SemiMajorAxis = value;
}
else if (name == "Eccentricity")
{
Eccentricity = value;
}
else if (name == "Inclination")
{
Inclination = value;
}
else if (name == "ArgOfPerigee")
{
ArgOfPerigee = value;
}
else if (name == "RAAN")
{
RAAN = value;
}
else if (name == "TrueAnomaly")
{
TrueAnomaly = value;
}
IAgSatellite sat = InitStateObj as IAgSatellite;
if (sat.PropagatorType == AgEVePropagatorType.ePropagatorJ2Perturbation)
{
IAgVePropagatorJ2Perturbation prop = sat.Propagator as IAgVePropagatorJ2Perturbation;
prop.InitialState.Representation.AssignClassical(AgECoordinateSystem.eCoordinateSystemICRF, SemiMajorAxis, Eccentricity, Inclination, ArgOfPerigee, RAAN, TrueAnomaly);
prop.Propagate();
}
if (sat.PropagatorType == AgEVePropagatorType.ePropagatorJ4Perturbation)
{
IAgVePropagatorJ4Perturbation prop = sat.Propagator as IAgVePropagatorJ4Perturbation;
prop.InitialState.Representation.AssignClassical(AgECoordinateSystem.eCoordinateSystemICRF, SemiMajorAxis, Eccentricity, Inclination, ArgOfPerigee, RAAN, TrueAnomaly);
prop.Propagate();
}
if (sat.PropagatorType == AgEVePropagatorType.ePropagatorTwoBody)
{
IAgVePropagatorTwoBody prop = sat.Propagator as IAgVePropagatorTwoBody;
prop.InitialState.Representation.AssignClassical(AgECoordinateSystem.eCoordinateSystemICRF, SemiMajorAxis, Eccentricity, Inclination, ArgOfPerigee, RAAN, TrueAnomaly);
prop.Propagate();
}
}
public static void CreateSat(IAgSatellite m_satellite)
{
if (StkRoot.CurrentScenario.Children.Contains(AgESTKObjectType.eSatellite, "OrbitTunerSat"))
{
return;
}
m_satellite = StkRoot.CurrentScenario.Children.New(AgESTKObjectType.eSatellite, "OrbitTunerSat") as IAgSatellite;
// set prop. to J2 pertubation
m_satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorJ2Perturbation);
STKHelper.SetMaxViewing(m_satellite);
// get the j2 perturbation propagator
IAgVePropagatorJ2Perturbation prop = m_satellite.Propagator as IAgVePropagatorJ2Perturbation;
prop.Propagate();
}
// check if perigee radius is positive
private static bool IsPerigeePositive(IAgVePropagatorJ2Perturbation prop)
{
IAgOrbitStateClassical testOrbit = prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
testOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis testSizeShape = testOrbit.SizeShape as IAgClassicalSizeShapeSemimajorAxis;
// perigee radius = a(1-e)
double rPeri = testSizeShape.SemiMajorAxis * (1 - testSizeShape.Eccentricity);
if (rPeri > 3000.0)
{
return(true);
}
return(false);
}
private void CreateSat2J2()
{
try
{
try
{ root.ExecuteCommand("Unload / */Satellite/Sat2"); }
catch
{ }
IAgSatellite sat2 = root.CurrentScenario.Children.New(AgESTKObjectType.eSatellite, "Sat2") as IAgSatellite;
sat2.SetPropagatorType(AgEVePropagatorType.ePropagatorJ2Perturbation);
IAgVePropagatorJ2Perturbation propSat2 = sat2.Propagator as IAgVePropagatorJ2Perturbation;
propSat2.Step = 60;
IAgVeGfxAttributesOrbit sat2Graph = sat2.Graphics.Attributes as IAgVeGfxAttributesOrbit;
sat2Graph.Color = Color.Orange;
sat2Graph.Line.Width = AgELineWidth.e2;
IAgOrbitStateClassical classicalJ2 = propSat2.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
classicalJ2.CoordinateSystemType = AgECoordinateSystem.eCoordinateSystemJ2000;
classicalJ2.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis semiJ2 = classicalJ2.SizeShape as IAgClassicalSizeShapeSemimajorAxis;
semiJ2.SemiMajorAxis = semimajorAxisSat2;
semiJ2.Eccentricity = eccentricitySat2;
classicalJ2.Orientation.Inclination = inclinationSat2;
classicalJ2.Orientation.ArgOfPerigee = argOfPerigeeSat2;
classicalJ2.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeRAAN;
IAgOrientationAscNodeRAAN raan = classicalJ2.Orientation.AscNode as IAgOrientationAscNodeRAAN;
raan.Value = raanSat2;
classicalJ2.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
IAgClassicalLocationTrueAnomaly trueAnomaly = classicalJ2.Location as IAgClassicalLocationTrueAnomaly;
trueAnomaly.Value = trueAnomSat2;
propSat2.InitialState.Representation.Assign(classicalJ2);
propSat2.Propagate();
}
catch (Exception ex)
{
MessageBox.Show(ex.Message);
}
}
// check if apogee is above the Earth
private static bool IsApogeeAboveGround(IAgVePropagatorJ2Perturbation prop)
{
IAgOrbitStateClassical testOrbit = prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
testOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis testSizeShape = testOrbit.SizeShape as IAgClassicalSizeShapeSemimajorAxis;
// apogee radius = a(1+e)
double rApo = testSizeShape.SemiMajorAxis * (1 + testSizeShape.Eccentricity);
if (rApo > 6380.0)
{
return(true);
}
return(false);
}
public static void CreateSatellite(string satName, double orbitPeriod, double eccentricity, double inclination, double rightAscension, double meanAnomaly, double argOfPerigee)
{
AgStkObjectRoot root;
AgUiApplication app;
app = System.Runtime.InteropServices.Marshal.GetActiveObject("STK11.Application") as AGI.Ui.Application.AgUiApplication;
root = (AgStkObjectRoot)app.Personality2;
// new satellite
IAgSatellite sat = root.CurrentScenario.Children.New(AgESTKObjectType.eSatellite, satName) as IAgSatellite;
// set the propagator to J2
sat.SetPropagatorType(AgEVePropagatorType.ePropagatorJ2Perturbation);
// get the propagator
IAgVePropagatorJ2Perturbation j2 = (IAgVePropagatorJ2Perturbation) sat.Propagator;
//Define the satellite's orbit using classical (Keplerian) orbital elements
IAgOrbitStateClassical classical = (IAgOrbitStateClassical) j2.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical);
//Use period and eccentricity to define the size and shape of the orbit
classical.SizeShapeType = AgEClassicalSizeShape.eSizeShapePeriod;
IAgClassicalSizeShapePeriod period = (IAgClassicalSizeShapePeriod)classical.SizeShape;
period.Eccentricity = eccentricity;
period.Period = orbitPeriod;
//Use argument of perigee, inclination and RAAN to define the orientation of the orbit
classical.Orientation.ArgOfPerigee = argOfPerigee;
classical.Orientation.Inclination = inclination;
classical.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeRAAN;
IAgOrientationAscNodeRAAN raan = (IAgOrientationAscNodeRAAN)classical.Orientation.AscNode;
raan.Value = rightAscension;
//Use mean anomaly to specify the position of the satellite in orbit
classical.LocationType = AgEClassicalLocation.eLocationMeanAnomaly;
IAgClassicalLocationMeanAnomaly ma = (IAgClassicalLocationMeanAnomaly)classical.Location;
ma.Value = meanAnomaly;
//Assign the orbital elements to the satellite's propagator and propagate the orbit
j2.InitialState.Representation.Assign(classical);
j2.Propagate();
}
public static bool UpdateEquinocitalOrbit(IAgSatellite sat, double aE, double hE, double kE, double pE, double qE, double mE, ref string error, string equinBox)
{
IAgVePropagatorJ2Perturbation prop = sat.Propagator as IAgVePropagatorJ2Perturbation;
try
{
if (equinBox == "Posigrade")
{
prop.InitialState.Representation.AssignEquinoctialPosigrade(AgECoordinateSystem.eCoordinateSystemICRF, aE, hE, kE, pE, qE, mE);
}
else
{
prop.InitialState.Representation.AssignEquinoctialRetrograde(AgECoordinateSystem.eCoordinateSystemICRF, aE, hE, kE, pE, qE, mE);
}
}
catch
{
}
return(Is_Error_Propagator(prop, ref error));
}
public static bool UpdateClassicalOrbit(IAgSatellite sat, double a, double e, double i, double aop, double raan, double ta, ref string error)
{
IAgVePropagatorJ2Perturbation prop = sat.Propagator as IAgVePropagatorJ2Perturbation;
// need to set everything individually because true vs mean anomaly
IAgOrbitStateClassical keplerian = prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
keplerian.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis sizeShape = keplerian.SizeShape as IAgClassicalSizeShapeSemimajorAxis;
sizeShape.SemiMajorAxis = a;
sizeShape.Eccentricity = e;
keplerian.Orientation.Inclination = i;
keplerian.Orientation.ArgOfPerigee = aop;
(keplerian.Orientation.AscNode as IAgOrientationAscNodeRAAN).Value = raan;
keplerian.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
(keplerian.Location as IAgClassicalLocationTrueAnomaly).Value = ta;
prop.InitialState.Representation.Assign(keplerian);
return(Is_Error_Propagator(prop, ref error));
}
public Satellite_OrbitData(IAgStkObject Object0)
{
m_ElemsType = "Classical";
if (Object0.ClassName == "Satellite")
{
IAgSatellite sat = Object0 as IAgSatellite;
if (sat.PropagatorType == AgEVePropagatorType.ePropagatorJ2Perturbation)
{
IAgVePropagatorJ2Perturbation prop = sat.Propagator as IAgVePropagatorJ2Perturbation;
m_ObjectTimes = prop.EphemerisInterval as AgCrdnEventIntervalSmartInterval;
Step_Size = prop.Step;
IAgOrbitStateClassical keplerState = prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
m_ultimateObject = Object0;
get_InitStateJx(keplerState);
}
else if (sat.PropagatorType == AgEVePropagatorType.ePropagatorJ4Perturbation)
{
IAgVePropagatorJ4Perturbation prop = sat.Propagator as IAgVePropagatorJ4Perturbation;
m_ObjectTimes = prop.EphemerisInterval as AgCrdnEventIntervalSmartInterval;
Step_Size = prop.Step;
IAgOrbitStateClassical keplerState = prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
m_ultimateObject = keplerState;
get_InitStateJx(keplerState);
}
else if (sat.PropagatorType == AgEVePropagatorType.ePropagatorTwoBody)
{
IAgVePropagatorTwoBody prop = sat.Propagator as IAgVePropagatorTwoBody;
m_ObjectTimes = prop.EphemerisInterval as AgCrdnEventIntervalSmartInterval;
Step_Size = prop.Step;
IAgOrbitStateClassical keplerState = prop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
m_ultimateObject = keplerState;
get_InitStateJx(keplerState);
}
}
}
//Satellite helpers
public static void ChangeSatelliteInterval(IAgSatellite sat, string startTime, string stopTime, bool astgRun)
{
AgEVePropagatorType propType = sat.PropagatorType;
//IAgVePropagator prop = sat.Propagator;
switch (propType)
{
case AgEVePropagatorType.eUnknownPropagator:
break;
case AgEVePropagatorType.ePropagatorHPOP:
IAgVePropagatorHPOP prop = sat.Propagator as IAgVePropagatorHPOP;
prop.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
prop.Propagate();
break;
case AgEVePropagatorType.ePropagatorJ2Perturbation:
IAgVePropagatorJ2Perturbation prop1 = sat.Propagator as IAgVePropagatorJ2Perturbation;
prop1.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
prop1.Propagate();
break;
case AgEVePropagatorType.ePropagatorJ4Perturbation:
IAgVePropagatorJ4Perturbation prop2 = sat.Propagator as IAgVePropagatorJ4Perturbation;
prop2.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
prop2.Propagate();
break;
case AgEVePropagatorType.ePropagatorLOP:
IAgVePropagatorLOP prop3 = sat.Propagator as IAgVePropagatorLOP;
prop3.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
prop3.Propagate();
break;
case AgEVePropagatorType.ePropagatorSGP4:
IAgVePropagatorSGP4 prop4 = sat.Propagator as IAgVePropagatorSGP4;
prop4.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
prop4.Propagate();
break;
case AgEVePropagatorType.ePropagatorSPICE:
IAgVePropagatorSPICE prop5 = sat.Propagator as IAgVePropagatorSPICE;
prop5.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
prop5.Propagate();
break;
case AgEVePropagatorType.ePropagatorStkExternal:
IAgVePropagatorStkExternal prop6 = sat.Propagator as IAgVePropagatorStkExternal;
//prop6.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
break;
case AgEVePropagatorType.ePropagatorTwoBody:
IAgVePropagatorTwoBody prop7 = sat.Propagator as IAgVePropagatorTwoBody;
prop7.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
prop7.Propagate();
break;
case AgEVePropagatorType.ePropagatorUserExternal:
break;
case AgEVePropagatorType.ePropagatorGreatArc:
IAgVePropagatorGreatArc prop8 = sat.Propagator as IAgVePropagatorGreatArc;
prop8.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
prop8.Propagate();
break;
case AgEVePropagatorType.ePropagatorBallistic:
break;
case AgEVePropagatorType.ePropagatorSimpleAscent:
break;
case AgEVePropagatorType.ePropagatorAstrogator:
if (astgRun)
{
IAgVADriverMCS driver = sat.Propagator as IAgVADriverMCS;
driver.RunMCS();
}
break;
case AgEVePropagatorType.ePropagatorRealtime:
break;
case AgEVePropagatorType.ePropagatorGPS:
IAgVePropagatorGPS prop9 = sat.Propagator as IAgVePropagatorGPS;
prop9.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
prop9.Propagate();
break;
case AgEVePropagatorType.ePropagatorAviator:
break;
case AgEVePropagatorType.ePropagator11Param:
IAgVePropagator11Param prop10 = sat.Propagator as IAgVePropagator11Param;
prop10.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
prop10.Propagate();
break;
case AgEVePropagatorType.ePropagatorSP3:
IAgVePropagatorSP3 prop11 = sat.Propagator as IAgVePropagatorSP3;
//prop11.EphemerisInterval.SetExplicitInterval(startTime, stopTime);
break;
default:
break;
}
}
