AGI STK Objects 11 Send comments on this topic.
IAgVePropagatorHPOP Interface
Windows






Windows & Linux

Description

HPOP propagator interface.

Object Model





Public Methods

Public Method PropagatePropagates the satellite's path using the specified time interval.

Public Properties

Public Property CovarianceGet the covariance parameters.
Public Property EphemerisIntervalThe propagator's ephemeris interval.
Public Property ForceModelGet the force model parameters.
Public Property InitialStateGet the satellite's initial state.
Public Property IntegratorGet the integrator parameters.
Public Property StartTimeThis property is deprecated. Use EphemerisInterval to configure the propagation interval. Start time. Uses DateFormat Dimension.
Public Property StepStep size. Uses Time Dimension.
Public Property StopTimeThis property is deprecated. Use EphemerisInterval to configure the propagation interval. Stop time. Uses DateFormat Dimension.

Interfaces

Implemented Interface
IAgVePropagator

Example

Set the satellite to use the HPOP propagator
[C#]Copy Code
// Set satellite propagator to HPOP 
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorHPOP); 
 
// Get the HPOP propagator 
IAgVePropagatorHPOP propagator = satellite.Propagator as IAgVePropagatorHPOP; 
 

Configure the HPOP propagator
[C#]Copy Code
// Set satellite propagator to HPOP 
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorHPOP); 
 
// Get IAgVePropagatorLOP interface 
IAgVePropagatorHPOP hpopProp = satellite.Propagator as IAgVePropagatorHPOP; 
 
// Configure force model 
IAgVeHPOPForceModel hpopForceModel = hpopProp.ForceModel; 
hpopForceModel.CentralBodyGravity.File = @"STKData\CentralBodies\Earth\GGM02C.grv"; 
hpopForceModel.CentralBodyGravity.MaxDegree = 45; 
hpopForceModel.CentralBodyGravity.MaxOrder = 10; 
hpopForceModel.CentralBodyGravity.UseOceanTides = true; 
 
hpopForceModel.Drag.Use = true; 
IAgVeHPOPDragModelSpherical hpopDragModel = hpopForceModel.Drag.DragModel as IAgVeHPOPDragModelSpherical; 
hpopDragModel.Cd = 1.890000; 
hpopDragModel.AreaMassRatio = 0.05; 
hpopForceModel.Drag.AtmosphericDensityModel = AgEAtmosphericDensityModel.eMSIS90; 
 
hpopForceModel.ThirdBodyGravity.RemoveThirdBody("Moon"); 
 
// Propagate 
hpopProp.Propagate(); 
 

Configure the HPOP propagator
[Visual Basic .NET]Copy Code
' Set satellite propagator to HPOP
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorHPOP)

' Get IAgVePropagatorLOP interface
Dim hpopProp As IAgVePropagatorHPOP = TryCast(satellite.Propagator, IAgVePropagatorHPOP)

' Configure force model
Dim hpopForceModel As IAgVeHPOPForceModel = hpopProp.ForceModel
hpopForceModel.CentralBodyGravity.File = "STKData\CentralBodies\Earth\GGM02C.grv"
hpopForceModel.CentralBodyGravity.MaxDegree = 45
hpopForceModel.CentralBodyGravity.MaxOrder = 10
hpopForceModel.CentralBodyGravity.UseOceanTides = True

hpopForceModel.Drag.Use = True
Dim hpopDragModel As IAgVeHPOPDragModelSpherical = TryCast(hpopForceModel.Drag.DragModel, IAgVeHPOPDragModelSpherical)
hpopDragModel.Cd = 1.89
hpopDragModel.AreaMassRatio = 0.05
hpopForceModel.Drag.AtmosphericDensityModel = AgEAtmosphericDensityModel.eMSIS90

hpopForceModel.ThirdBodyGravity.RemoveThirdBody("Moon")

' Propagate
hpopProp.Propagate()

Set the satellite to use the HPOP propagator
[Visual Basic .NET]Copy Code
' Set satellite propagator to HPOP
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorHPOP)

' Get the HPOP propagator
Dim propagator As IAgVePropagatorHPOP = TryCast(satellite.Propagator, IAgVePropagatorHPOP)

Set satellite propagator to HPOP and set force model properties
[MATLAB]Copy Code
% IAgSatellite satellite: Satellite object 
satellite.SetPropagatorType('ePropagatorHPOP'); 
set(satellite.Propagator,'Step',60); 
satellite.Propagator.InitialState.Representation.AssignCartesian('eCoordinateSystemFixed',6406.92,-1787.59,-506.422,2.10185,6.48871,3.64041); 
 
forceModel = satellite.Propagator.ForceModel; 
forceModel.CentralBodyGravity.File = 'C:\Program Files\AGI\STK 11\STKData\CentralBodies\Earth\WGS84_EGM96.grv'; 
forceModel.CentralBodyGravity.MaxDegree = 21; 
forceModel.CentralBodyGravity.MaxOrder = 21; 
forceModel.Drag.Use=1; 
forceModel.Drag.DragModel.Cd=0.01; 
forceModel.Drag.DragModel.AreaMassRatio=0.01; 
forceModel.SolarRadiationPressure.Use=0; 
 
integrator = satellite.Propagator.Integrator; 
integrator.DoNotPropagateBelowAlt=-1e6; 
integrator.IntegrationModel=3; 
integrator.StepSizeControl.Method=1; 
integrator.StepSizeControl.ErrorTolerance=1e-13; 
integrator.StepSizeControl.MinStepSize=0.1; 
integrator.StepSizeControl.MaxStepSize=30; 
integrator.Interpolation.Method=1; 
integrator.Interpolation.Order=7; 
 
satellite.Propagator.Propagate; 
 
 
Set satellite propagator to HPOP and set force model properties
[Python]Copy Code
# IAgSatellite satellite: Satellite object 
satellite.SetPropagatorType(0) # ePropagatorHPOP 
satellite.Propagator.Step = 60 
satellite.Propagator.InitialState.Representation.AssignCartesian(2,6406.92,-1787.59,-506.422,2.10185,6.48871,3.64041) # eCoordinateSystemFixed 
 
forceModel = satellite.Propagator.ForceModel 
forceModel.CentralBodyGravity.File = r'C:\Program Files\AGI\STK 11\STKData\CentralBodies\Earth\WGS84_EGM96.grv' 
forceModel.CentralBodyGravity.MaxDegree = 21 
forceModel.CentralBodyGravity.MaxOrder = 21 
forceModel.Drag.Use=1 
forceModel.Drag.DragModel.Cd=0.01 
forceModel.Drag.DragModel.AreaMassRatio=0.01 
forceModel.SolarRadiationPressure.Use=0 
 
integrator = satellite.Propagator.Integrator 
integrator.DoNotPropagateBelowAlt=-1e6 
integrator.IntegrationModel=3 
integrator.StepSizeControl.Method=1 
integrator.StepSizeControl.ErrorTolerance=1e-13 
integrator.StepSizeControl.MinStepSize=0.1 
integrator.StepSizeControl.MaxStepSize=30 
integrator.Interpolation.Method=1 
integrator.Interpolation.Order=7 
 
satellite.Propagator.Propagate() 
 
 

CoClasses that Implement IAgVePropagatorHPOP

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