private void CreateSat1TwoBody()
{
try
{
try
{ root.ExecuteCommand("Unload / */Satellite/Sat1"); }
catch
{ }
IAgSatellite sat1 = root.CurrentScenario.Children.New(AgESTKObjectType.eSatellite, "Sat1") as IAgSatellite;
sat1.SetPropagatorType(AgEVePropagatorType.ePropagatorTwoBody);
IAgVePropagatorTwoBody propSat1 = sat1.Propagator as IAgVePropagatorTwoBody;
propSat1.Step = 60;
IAgVeGfxAttributesOrbit sat1Graph = sat1.Graphics.Attributes as IAgVeGfxAttributesOrbit;
sat1Graph.Color = Color.LimeGreen;
sat1Graph.Line.Width = AgELineWidth.e2;
//'Definisco i parametri Kepleriani classici del satellite
IAgOrbitStateClassical classical2B = propSat1.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
classical2B.CoordinateSystemType = AgECoordinateSystem.eCoordinateSystemJ2000;
//'Uso il semiasse maggiore e l'eccentricità per definire la forma e la dimensione dell'orbita
classical2B.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis semi2B = classical2B.SizeShape as IAgClassicalSizeShapeSemimajorAxis;
semi2B.SemiMajorAxis = semimajorAxisSat1;
semi2B.Eccentricity = eccentricitySat1;
//'Per definire l'orientamento dell'orbita nello spazio uso l'inclinazione, l'argomento del perigeo e la RAAN
classical2B.Orientation.Inclination = inclinationSat1;
classical2B.Orientation.ArgOfPerigee = argOfPerigeeSat1;
classical2B.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeRAAN;
IAgOrientationAscNodeRAAN raan = classical2B.Orientation.AscNode as IAgOrientationAscNodeRAAN;
raan.Value = raanSat1;
//'uso l'anomalia vera per definire la posizione iniziale del satellite lungo la sua orbita
classical2B.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
IAgClassicalLocationTrueAnomaly trueAnomaly = classical2B.Location as IAgClassicalLocationTrueAnomaly;
trueAnomaly.Value = trueAnomSat1;
//'Infine assegno i parametri orbtali così definiti al satellite e lo propago
propSat1.InitialState.Representation.Assign(classical2B);
propSat1.Propagate();
}
catch (Exception ex)
{
MessageBox.Show(ex.Message);
}
}
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 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);
}
}
}
/// <summary>
/// 新建一个SARSYS在当前sc文件中
/// 需要建立最基础的系统
/// 参数大多数有默认值
/// </summary>
public void newsarsys()
{
#region 写入信息
AGI.STKX.IAgExecCmdResult resultmsg = rootapp.ExecuteCommand("SetDescription * long SARSYS");
#endregion
#region 设定单位、仿真时间
// Reset the units to the STK defaults
dimensions = root.UnitPreferences;
dimensions.ResetUnits();
// Set the date unit, acquire an interface to the scenario and use
// it to set the time period and epoch
dimensions.SetCurrentUnit("DateFormat", "UTCG");
scene = (IAgScenario)root.CurrentScenario;
scene.StartTime = simstarttime;
scene.StopTime = simstoptime;
scene.Epoch = simstarttime;
// Set new preference for Temperature
dimensions.SetCurrentUnit("Temperature", "degC");
#endregion
#region 放置发射站
//SATELLITE #1: TDRS
//Assign a two-body propagator to propagate it
tdrs = (IAgSatellite)root.CurrentScenario.Children.New(AgESTKObjectType.
eSatellite, "TDRS");
tdrs.SetPropagatorType(AgEVePropagatorType.ePropagatorTwoBody);
twobody = (IAgVePropagatorTwoBody)tdrs.Propagator;
//Define the TDRS satellite's orbit using
//classical (Keplerian) orbital elements
classical = (IAgOrbitStateClassical)twobody.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical);
//Set J2000 as the coordinate system
//and set the time period and time step
classical.CoordinateSystemType = AgECoordinateSystem.eCoordinateSystemJ2000;
twobody.EphemerisInterval.SetStartAndStopTimes(simstarttime, simstoptime);
twobody.Step = 60;
//定义半主轴长度，离心率
//Use period and eccentricity to define the size
//and shape of the orbit
classical.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis semi = (IAgClassicalSizeShapeSemimajorAxis)classical.SizeShape;
semi.SemiMajorAxis = 35860;
semi.Eccentricity = 0.0;
//定义轨道倾角，升交点赤经，近地点幅角
//Use argument of perigee, inclination
//and longitude of ascending node to
//define the orientation of the orbit
classical.Orientation.ArgOfPerigee = 15.0;
classical.Orientation.Inclination = 40.0;
classical.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeLAN;
IAgOrientationAscNodeLAN lan = (IAgOrientationAscNodeLAN)classical.Orientation.AscNode;
lan.Value = 259.999982;
//定义真近点角（？）来定义初始位置
//Use true anomaly to specify the position of
//the satellite in orbit
classical.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
IAgClassicalLocationTrueAnomaly trueAnomaly = (IAgClassicalLocationTrueAnomaly)classical.Location;
trueAnomaly.Value = 178.845262;
//Assign the orbital elements to the TDRS
//satellite's propagator and propagate the orbit
twobody.InitialState.Representation.Assign(classical);
twobody.Propagate();
root.Rewind();
#endregion
#region 放置接收站
cruise = (IAgAircraft)root.CurrentScenario.Children.New(AgESTKObjectType.eAircraft, "Cruise");
cruise.SetRouteType(AgEVePropagatorType.ePropagatorGreatArc);
greatArc = (IAgVePropagatorGreatArc)cruise.Route;
greatArc.EphemerisInterval.SetStartAndStopTimes(simstarttime, simstoptime);
greatArc.Method = AgEVeWayPtCompMethod.eDetermineTimeAccFromVel;
((IAgVOModelFile)cruise.VO.Model.ModelData).Filename = @"\STKData\VO\Models\Air\e-3a_sentry_awacs.mdl";
cruise.VO.Offsets.Rotational.Enable = true;
cruise.VO.Offsets.Rotational.X = 180;
//Use the convenience method defined above
//to add waypoints specifying the ship's route
AddWaypoint(greatArc.Waypoints, -42.1, -121.5, 3.0, .15, 0.0);
AddWaypoint(greatArc.Waypoints, 62.0, -56.6, 3.0, .15, 0.0);
cruise.SetAttitudeType(AgEVeAttitude.eAttitudeStandard);
IAgVeRouteAttitudeStandard attitude = (IAgVeRouteAttitudeStandard)cruise.Attitude;
attitude.Basic.SetProfileType(AgEVeProfile.
eProfileECFVelocityAlignmentWithRadialConstraint);
cruise.Graphics.WaypointMarker.IsWaypointMarkersVisible = true;
cruise.Graphics.WaypointMarker.IsTurnMarkersVisible = true;
greatArc.Propagate();
root.Rewind();
#endregion
#region 放置发射站雷达
horizon = (IAgSensor)root.CurrentScenario.Children["TDRS"].Children.
New(AgESTKObjectType.eSensor, "Horizon");
horizon.SetPatternType(AgESnPattern.eSnSimpleConic);
IAgSnSimpleConicPattern simpleConic = (IAgSnSimpleConicPattern)horizon.Pattern;
simpleConic.ConeAngle = 0.1;
//Select a Fixed pointing type and the Az-El
//orientation type, and set the elevation angle to
//90 deg, so that the sensor points straight down
//with reference to the satellite
horizon.SetPointingType(AgESnPointing.eSnPtFixed);
IAgSnPtFixed fixedPt = (IAgSnPtFixed)horizon.Pointing;
IAgOrientationAzEl azEl = (IAgOrientationAzEl)fixedPt.Orientation.ConvertTo(AgEOrientationType.eAzEl);
azEl.Elevation = 89.2;
azEl.AboutBoresight = AgEAzElAboutBoresight.eAzElAboutBoresightRotate;
fixedPt.Orientation.Assign(azEl);
root.Rewind();
#endregion
}
/// <summary>
/// 读出当前sc文件中已经存在的SARSYS
/// </summary>
public void readsarsys()
{
AGI.STKX.IAgExecCmdResult resultmsg = rootapp.ExecuteCommand("GetDescription * long");
dimensions = root.UnitPreferences;
scene = (IAgScenario)root.CurrentScenario;
tdrs = (IAgSatellite)root.CurrentScenario.Children["TDRS"];
twobody = (IAgVePropagatorTwoBody)tdrs.Propagator;
classical = (IAgOrbitStateClassical)twobody.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical);
cruise = (IAgAircraft)root.CurrentScenario.Children["Cruise"];
greatArc = (IAgVePropagatorGreatArc)cruise.Route;
radar_t = (IAgSensor)root.CurrentScenario.Children["TDRS"].Children["radar_t"];
radar_r = (IAgSensor)root.CurrentScenario.Children["Cruise"].Children["radar_r"];
target = (IAgSensor)root.CurrentScenario.Children["TDRS"].Children["target"];
simstarttime = scene.StartTime;
simstoptime = scene.StopTime;
simstep = scene.Animation.AnimStepValue;
IAgClassicalSizeShapeSemimajorAxis semi = (IAgClassicalSizeShapeSemimajorAxis)classical.SizeShape;
sasem = semi.SemiMajorAxis;
saecc = semi.Eccentricity;
saaop = classical.Orientation.ArgOfPerigee;
sainc = classical.Orientation.Inclination;
salan = ((IAgOrientationAscNodeLAN)classical.Orientation.AscNode).Value;
satra = ((IAgClassicalLocationTrueAnomaly)classical.Location).Value;
racoang = ((IAgSnSimpleConicPattern)radar_t.Pattern).ConeAngle;
IAgSnPtFixed fixedPt = (IAgSnPtFixed)radar_t.Pointing;
IAgOrientationAzEl azEl = (IAgOrientationAzEl)fixedPt.Orientation.ConvertTo(AgEOrientationType.eAzEl);
raeleva = azEl.Elevation;
plwaypoints = new double[5 * greatArc.Waypoints.Count];
for(int ii=0;ii<greatArc.Waypoints.Count;ii++)
{
plwaypoints[ii * 5] = greatArc.Waypoints[ii].Latitude;
plwaypoints[ii * 5 + 1] = greatArc.Waypoints[ii].Longitude;
plwaypoints[ii * 5 + 2] = greatArc.Waypoints[ii].Altitude;
plwaypoints[ii * 5 + 3] = greatArc.Waypoints[ii].Speed;
plwaypoints[ii * 5 + 4] = greatArc.Waypoints[ii].TurnRadius;
}
}
/// <summary>
/// 新建一个SARSYS在当前sc文件中
/// 需要建立最基础的系统
/// 参数大多数有默认值
/// </summary>
public void newsarsys()
{
#region 写入信息
AGI.STKX.IAgExecCmdResult resultmsg = rootapp.ExecuteCommand("SetDescription * long SARSYS");
#endregion
#region 设定单位、仿真时间
// Reset the units to the STK defaults
dimensions = root.UnitPreferences;
dimensions.ResetUnits();
// Set the date unit, acquire an interface to the scenario and use
// it to set the time period and epoch
dimensions.SetCurrentUnit("DateFormat", "UTCG");
scene = (IAgScenario)root.CurrentScenario;
scene.StartTime = simstarttime;
scene.StopTime = simstoptime;
scene.Epoch = simstarttime;
//rootapp.ExecuteCommand("MapTracking * UTM");
// Set new preference for Temperature
dimensions.SetCurrentUnit("Temperature", "degC");
#endregion
#region 放置发射站
//SATELLITE #1: TDRS
//Assign a two-body propagator to propagate it
tdrs = (IAgSatellite)root.CurrentScenario.Children.New(AgESTKObjectType.
eSatellite, "TDRS");
tdrs.SetPropagatorType(AgEVePropagatorType.ePropagatorTwoBody);
twobody = (IAgVePropagatorTwoBody)tdrs.Propagator;
//Define the TDRS satellite's orbit using
//classical (Keplerian) orbital elements
classical = (IAgOrbitStateClassical)twobody.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical);
//Set J2000 as the coordinate system
//and set the time period and time step
classical.CoordinateSystemType = AgECoordinateSystem.eCoordinateSystemJ2000;
twobody.EphemerisInterval.SetStartAndStopTimes(simstarttime, simstoptime);
twobody.Step = 60;
//定义半主轴长度，离心率
//Use period and eccentricity to define the size
//and shape of the orbit
classical.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis semi = (IAgClassicalSizeShapeSemimajorAxis)classical.SizeShape;
semi.SemiMajorAxis = sasem;
semi.Eccentricity = saecc;
//定义轨道倾角，升交点赤经，近地点幅角
//Use argument of perigee, inclination
//and longitude of ascending node to
//define the orientation of the orbit
classical.Orientation.ArgOfPerigee = saaop;
classical.Orientation.Inclination = sainc;
classical.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeLAN;
IAgOrientationAscNodeLAN lan = (IAgOrientationAscNodeLAN)classical.Orientation.AscNode;
lan.Value = salan;
//定义真近点角（？）来定义初始位置
//Use true anomaly to specify the position of
//the satellite in orbit
classical.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
IAgClassicalLocationTrueAnomaly trueAnomaly = (IAgClassicalLocationTrueAnomaly)classical.Location;
trueAnomaly.Value = satra;
//Assign the orbital elements to the TDRS
//satellite's propagator and propagate the orbit
twobody.InitialState.Representation.Assign(classical);
twobody.Propagate();
root.Rewind();
#endregion
#region 放置接收站
cruise = (IAgAircraft)root.CurrentScenario.Children.New(AgESTKObjectType.eAircraft, "Cruise");
cruise.SetRouteType(AgEVePropagatorType.ePropagatorGreatArc);
greatArc = (IAgVePropagatorGreatArc)cruise.Route;
greatArc.EphemerisInterval.SetStartAndStopTimes(simstarttime, simstoptime);
greatArc.Method = AgEVeWayPtCompMethod.eDetermineTimeAccFromVel;
((IAgVOModelFile)cruise.VO.Model.ModelData).Filename = @"\STKData\VO\Models\Air\rq-4a_globalhawk.mdl";
cruise.VO.Offsets.Rotational.Enable = true;
cruise.VO.Offsets.Rotational.X = 180;
//Use the convenience method defined above
//to add waypoints specifying the ship's route
for (int ii = 0; ii < plwaypoints.Length; ii += 5)
{
AddWaypoint(greatArc.Waypoints, plwaypoints[ii], plwaypoints[ii + 1], plwaypoints[ii + 2], plwaypoints[ii + 3], plwaypoints[ii + 4]);
}
cruise.SetAttitudeType(AgEVeAttitude.eAttitudeStandard);
IAgVeRouteAttitudeStandard attitude = (IAgVeRouteAttitudeStandard)cruise.Attitude;
attitude.Basic.SetProfileType(AgEVeProfile.
eProfileECFVelocityAlignmentWithRadialConstraint);
cruise.Graphics.WaypointMarker.IsWaypointMarkersVisible = true;
cruise.Graphics.WaypointMarker.IsTurnMarkersVisible = true;
greatArc.Propagate();
root.Rewind();
#endregion
#region 放置发射站雷达
radar_t = (IAgSensor)root.CurrentScenario.Children["TDRS"].Children.New(AgESTKObjectType.eSensor, "radar_t");
radar_t.SetPatternType(AgESnPattern.eSnSimpleConic);
((IAgSnSimpleConicPattern)radar_t.Pattern).ConeAngle = racoang;
//Select a Fixed pointing type and the Az-El
//orientation type, and set the elevation angle to
//90 deg, so that the sensor points straight down
//with reference to the satellite
radar_t.SetPointingType(AgESnPointing.eSnPtFixed);
IAgSnPtFixed fixedPt = (IAgSnPtFixed)radar_t.Pointing;
IAgOrientationAzEl azEl = (IAgOrientationAzEl)fixedPt.Orientation.ConvertTo(AgEOrientationType.eAzEl);
azEl.Elevation = raeleva;
azEl.AboutBoresight = AgEAzElAboutBoresight.eAzElAboutBoresightRotate;
fixedPt.Orientation.Assign(azEl);
radar_t.Graphics.FillVisible = true;
radar_t.VO.FillVisible = true;
root.Rewind();
#endregion
#region 放置接收站雷达
target = (IAgSensor)root.CurrentScenario.Children["TDRS"].Children.New(AgESTKObjectType.eSensor, "target");
target.SetLocationType(AgESnLocation.eSnLocationCrdnPoint);
IAgLocationCrdnPoint vgtPoint = target.LocationData as IAgLocationCrdnPoint;
//vgtPoint.PointPath = "TDRS/radar_t BoresightIntersection(Terrain)";
vgtPoint.PointPath = "Satellite/TDRS/Sensor/radar_t BoresightIntersection(Terrain)";
target.SetPatternType(AgESnPattern.eSnSimpleConic);
((IAgSnSimpleConicPattern)target.Pattern).ConeAngle = 0.00001;
IAgSnPtTargeted targetedSensor1 = target.CommonTasks.SetPointingTargetedTracking(
AgETrackModeType.eTrackModeTranspond, AgEBoresightType.eBoresightRotate, "*/Aircraft/Cruise");
target.SetPointingType(AgESnPointing.eSnPtTargeted);
IAgSnPtTargeted rpt1 = (IAgSnPtTargeted)target.Pointing;
rpt1.Boresight = AgESnPtTrgtBsightType.eSnPtTrgtBsightTracking;
root.Rewind();
rootapp.ExecuteCommand("Graphics */Satellite/TDRS/Sensor/target Show Off");
/////////////////////////
radar_r = (IAgSensor)root.CurrentScenario.Children["Cruise"].Children.New(AgESTKObjectType.eSensor, "radar_r");
radar_r.SetPatternType(AgESnPattern.eSnSimpleConic);
((IAgSnSimpleConicPattern)radar_r.Pattern).ConeAngle = 3;
IAgSnPtTargeted targetedSensor = radar_r.CommonTasks.SetPointingTargetedTracking(
AgETrackModeType.eTrackModeTranspond, AgEBoresightType.eBoresightRotate, "*/Satellite/TDRS/Sensor/target");
radar_r.SetPointingType(AgESnPointing.eSnPtTargeted);
IAgSnPtTargeted rpt = (IAgSnPtTargeted)radar_r.Pointing;
rpt.Boresight = AgESnPtTrgtBsightType.eSnPtTrgtBsightTracking;
root.Rewind();
#endregion
}
//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;
}
}
