public void get_InitStateJx(IAgOrbitStateClassical keplerState)
{
keplerState.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis Orbitsize = keplerState.SizeShape as IAgClassicalSizeShapeSemimajorAxis;
keplerState.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
IAgClassicalLocationTrueAnomaly OrbitLocation = keplerState.Location as IAgClassicalLocationTrueAnomaly;
IAgClassicalOrientation OrbitOrientation = keplerState.Orientation as IAgClassicalOrientation;
OrbitOrientation.AscNodeType = AgEOrientationAscNode.eAscNodeRAAN;
IAgOrientationAscNodeRAAN OrbitAsc = keplerState.Orientation.AscNode as IAgOrientationAscNodeRAAN;
SemiMajorAxis = Orbitsize.SemiMajorAxis;
Eccentricity = Orbitsize.Eccentricity;
Inclination = OrbitOrientation.Inclination;
ArgOfPerigee = OrbitOrientation.ArgOfPerigee;
RAAN = OrbitAsc.Value;
TrueAnomaly = OrbitLocation.Value;
//Console.WriteLine(Orbitsize.SemiMajorAxis);
//IAgQuantity a = OrbitOrientation as IAgQuantity;
//Console.WriteLine(OrbitOrientation.Inclination);
}
// 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);
}
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);
}
}
// 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 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);
}
}
}
/* This code takes a set of Cartesian coordinates in a fixed frame and converts them into Keplerian orbital elements in an inertial frame
* without using a satellite object (using conversion utility within STK Engine). The Keplerian elements you would like to return can be specified
* by changing the enum values near the top of the Main function.
*/
static void Main(string[] args)
{
AgSTKXApplication app = new AgSTKXApplication();
app.NoGraphics = true;
AgStkObjectRoot root = new AgStkObjectRoot();
// Here are some preliminary variables for the classical coordinate elements you would like to obtain
SizeShapeTypes SizeShapeType = SizeShapeTypes.Altitude;
AscNodeTypes AscNodeType = AscNodeTypes.RAAN;
LocationTypes LocationType = LocationTypes.ArgumentOfLatitude;
// Here we create a new AgOrbitState object
IAgConversionUtility ConversionUtility = root.ConversionUtility;
IAgOrbitState cartesianOrbit = ConversionUtility.NewOrbitStateOnEarth();
// Here is how you display and change the epoch
Console.WriteLine("Epoch:");
cartesianOrbit.Epoch = "1 Jun 2003 17:00:00.000";
Console.WriteLine(cartesianOrbit.Epoch);
// Here we assign whatever Cartesian coordinates we would like to in a fixed frame
cartesianOrbit.AssignCartesian(AgECoordinateSystem.eCoordinateSystemFixed, 5598.42, -14988.6, 4.80738, 3.408, 1.27376, 2.60903);
// Now we convert the orbit to a classical orbit state
IAgOrbitStateClassical classicalOrbit = cartesianOrbit.ConvertTo(AgEOrbitStateType.eOrbitStateClassical) as IAgOrbitStateClassical;
Console.WriteLine(classicalOrbit.CoordinateSystemType);
// Prints out the first two classical orbit elements
switch (SizeShapeType)
{
case SizeShapeTypes.Altitude:
classicalOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeAltitude;
IAgClassicalSizeShapeAltitude sizeShapeAltitude = classicalOrbit.SizeShape as IAgClassicalSizeShapeAltitude;
Console.WriteLine("Apogee Altitude:");
Console.WriteLine(sizeShapeAltitude.ApogeeAltitude);
Console.WriteLine("Perigee Altitude:");
Console.WriteLine(sizeShapeAltitude.PerigeeAltitude);
break;
case SizeShapeTypes.MeanMotion:
classicalOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeMeanMotion;
IAgClassicalSizeShapeMeanMotion sizeShapeMeanMotion = classicalOrbit.SizeShape as IAgClassicalSizeShapeMeanMotion;
Console.WriteLine("Mean Motion:");
Console.WriteLine(sizeShapeMeanMotion.MeanMotion);
Console.WriteLine("Eccentricity:");
Console.WriteLine(sizeShapeMeanMotion.Eccentricity);
break;
case SizeShapeTypes.Period:
classicalOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapePeriod;
IAgClassicalSizeShapePeriod sizeShapePeriod = classicalOrbit.SizeShape as IAgClassicalSizeShapePeriod;
Console.WriteLine("Period:");
Console.WriteLine(sizeShapePeriod.Period);
Console.WriteLine("Eccentricity:");
Console.WriteLine(sizeShapePeriod.Eccentricity);
break;
case SizeShapeTypes.Radius:
classicalOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeRadius;
IAgClassicalSizeShapeRadius sizeShapeRadius = classicalOrbit.SizeShape as IAgClassicalSizeShapeRadius;
Console.WriteLine("Apogee Radius:");
Console.WriteLine(sizeShapeRadius.ApogeeRadius);
Console.WriteLine("Perigee Radius:");
Console.WriteLine(sizeShapeRadius.PerigeeRadius);
break;
case SizeShapeTypes.SemimajorAxis:
classicalOrbit.SizeShapeType = AgEClassicalSizeShape.eSizeShapeSemimajorAxis;
IAgClassicalSizeShapeSemimajorAxis sizeShapeSemimajorAxis = classicalOrbit.SizeShape as IAgClassicalSizeShapeSemimajorAxis;
Console.WriteLine("Semimajor Axis:");
Console.WriteLine(sizeShapeSemimajorAxis.SemiMajorAxis);
Console.WriteLine("Eccentricity:");
Console.WriteLine(sizeShapeSemimajorAxis.Eccentricity);
break;
}
// Prints the inclination and argument of perigee
IAgClassicalOrientation orientation = classicalOrbit.Orientation;
Console.WriteLine("Inclination:");
Console.WriteLine(orientation.Inclination);
Console.WriteLine("Argument of Perigee:");
Console.WriteLine(orientation.ArgOfPerigee);
// This section prints the ascending node value
Console.WriteLine("Ascending Node:");
switch (AscNodeType)
{
case AscNodeTypes.RAAN:
orientation.AscNodeType = AgEOrientationAscNode.eAscNodeRAAN;
IAgOrientationAscNodeRAAN ascNodeRAAN = orientation.AscNode as IAgOrientationAscNodeRAAN;
Console.WriteLine(ascNodeRAAN.Value);
break;
case AscNodeTypes.LAN:
orientation.AscNodeType = AgEOrientationAscNode.eAscNodeLAN;
IAgOrientationAscNodeLAN ascNodeLAN = orientation.AscNode as IAgOrientationAscNodeLAN;
Console.WriteLine(ascNodeLAN.Value);
break;
}
// This section prints the location of the satellite along the orbit in terms of whatever you would like
Console.WriteLine("Location:");
switch (LocationType)
{
case LocationTypes.ArgumentOfLatitude:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationArgumentOfLatitude;
IAgClassicalLocationArgumentOfLatitude locationArgumentOfLatitude = classicalOrbit.Location as IAgClassicalLocationArgumentOfLatitude;
Console.WriteLine(locationArgumentOfLatitude.Value);
break;
case LocationTypes.EccentricAnomaly:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationEccentricAnomaly;
IAgClassicalLocationEccentricAnomaly locationSpecificEccentricAnomaly = classicalOrbit.Location as IAgClassicalLocationEccentricAnomaly;
Console.WriteLine(locationSpecificEccentricAnomaly.Value);
break;
case LocationTypes.MeanAnomaly:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationMeanAnomaly;
IAgClassicalLocationMeanAnomaly locationSpecificMeanAnomaly = classicalOrbit.Location as IAgClassicalLocationMeanAnomaly;
Console.WriteLine(locationSpecificMeanAnomaly.Value);
break;
case LocationTypes.TimePastAN:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationTimePastAN;
IAgClassicalLocationTimePastAN locationSpecificTimePastAN = classicalOrbit.Location as IAgClassicalLocationTimePastAN;
Console.WriteLine(locationSpecificTimePastAN.Value);
break;
case LocationTypes.TimePastPerigee:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationTimePastPerigee;
IAgClassicalLocationTimePastPerigee locationSpecificTimePastPerigee = classicalOrbit.Location as IAgClassicalLocationTimePastPerigee;
Console.WriteLine(locationSpecificTimePastPerigee.Value);
break;
case LocationTypes.TrueAnomaly:
classicalOrbit.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
IAgClassicalLocationTrueAnomaly locationTrueAnomaly = classicalOrbit.Location as IAgClassicalLocationTrueAnomaly;
Console.WriteLine(locationTrueAnomaly.Value);
break;
}
Console.ReadLine();
}
/// <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
}
//added selected TDRSs into the model
private void add_tdrs(station_str passed)
{
IAgSatellite localtdrs;
localtdrs = (IAgSatellite)m_oApplication.CurrentScenario.Children.New(AGI.STKObjects.AgESTKObjectType.eSatellite, passed.name);
//AGI.STKObjects.IAgSatellite sat = (IAgSatellite)m_oApplication.CurrentScenario.Children.NewOnCentralBody(AGI.STKObjects.AgESTKObjectType.eSatellite, orbitdata[i].name, centerbodyname);
//disable the leading ground track
localtdrs.Graphics.PassData.GroundTrack.SetLeadDataType(AgELeadTrailData.eDataNone);
//disable trailing ground track
localtdrs.Graphics.PassData.GroundTrack.SetTrailDataType(AgELeadTrailData.eDataNone);
localtdrs.VO.Pass.TrackData.PassData.GroundTrack.SetLeadDataType(AgELeadTrailData.eDataNone);
localtdrs.VO.Pass.TrackData.PassData.GroundTrack.SetTrailDataType(AgELeadTrailData.eDataNone);
localtdrs.VO.Pass.TrackData.PassData.Orbit.SetLeadDataType(AgELeadTrailData.eDataNone);
localtdrs.VO.Pass.TrackData.PassData.Orbit.SetTrailDataType(AgELeadTrailData.eDataNone);
//set the propagator type to HPOP
localtdrs.SetPropagatorType(AGI.STKObjects.AgEVePropagatorType.ePropagatorJ2Perturbation);
AGI.STKObjects.IAgVePropagatorJ2Perturbation hpop = (AGI.STKObjects.IAgVePropagatorJ2Perturbation)localtdrs.Propagator;
IAgOrbitState orbit = hpop.InitialState.Representation;
//create the string to hold the missions epoch date & time
string cmb_epoch = startdate, cmb_end = enddate;
cmb_epoch += " 00:00:00";
DateTime epochDT = Convert.ToDateTime(cmb_epoch);
DateTime endepochDT = Convert.ToDateTime(cmb_end);
//hpop.InitialState.Representation.Assign(orbit);
Console.Write("epochtime = " + epochDT.ToString("dd MMM yyyy ") + "00:00:00" + "\n");
hpop.InitialState.Representation.Epoch = (epochDT.ToString("dd MMM yyyy ") + "00:00:00");
// hpop.InitialState.Representation.Assign(ia)
//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();
IAgOrbitStateClassical classical = (IAgOrbitStateClassical)hpop.InitialState.Representation.ConvertTo(AgEOrbitStateType.eOrbitStateClassical);
classical.CoordinateSystemType = AGI.STKUtil.AgECoordinateSystem.eCoordinateSystemJ2000;
IAgCrdnEventIntervalSmartInterval interval = hpop.EphemerisInterval;
interval.SetExplicitInterval((epochDT.ToString("dd MMM yyyy ") + "00:00:00"), (endepochDT.ToString("dd MMM yyyy ") + "00:00:00"));
hpop.Step = 60;
classical.LocationType = AgEClassicalLocation.eLocationTrueAnomaly;
IAgClassicalLocationTrueAnomaly trueAnomaly = (IAgClassicalLocationTrueAnomaly)classical.Location;
trueAnomaly.Value = 178.845262;
classical.SizeShapeType = AgEClassicalSizeShape.eSizeShapePeriod;
IAgClassicalSizeShapePeriod period = (IAgClassicalSizeShapePeriod)classical.SizeShape;
period.Eccentricity = 0.0;
period.Period = 86164.090540;
classical.Orientation.ArgOfPerigee = 0.0;
classical.Orientation.Inclination = 0.0;
classical.Orientation.AscNodeType = AgEOrientationAscNode.eAscNodeLAN;
IAgOrientationAscNodeLAN lan = (IAgOrientationAscNodeLAN)classical.Orientation.AscNode;
lan.Value = (360 - passed.lon);
hpop.InitialState.Representation.Assign(classical);
hpop.Propagate();
}