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; } }