Description

HPOP propagator interface.

Public Methods

Propagates the satellite's path using the specified time interval.

Public Properties

Covariance	Get the covariance parameters.
EphemerisInterval	Get the propagator's ephemeris interval.
ForceModel	Get the force model parameters.
InitialState	Get the satellite's initial state.
Integrator	Get the integrator parameters.
Step	Step size. Uses Time Dimension.

Interfaces

Implemented Interface
IAgVePropagator

CoClasses that Implement IAgVePropagatorHPOP

Name
AgVePropagatorHPOP

Example

Set the satellite to use the HPOP propagator

[C#]

// Set satellite propagator to HPOP
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorHPOP);

// Get the HPOP propagator
IAgVePropagatorHPOP propagator = satellite.Propagator as IAgVePropagatorHPOP;

Configure the HPOP propagator

[C#]

// 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]

' 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]

' 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

[Python - STK API]

# IAgSatellite satellite: Satellite object
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorHPOP)
satellite.Propagator.Step = 60
satellite.Propagator.InitialState.Representation.AssignCartesian(AgECoordinateSystem.eCoordinateSystemFixed, 6406.92, -1787.59, -506.422, 2.10185, 6.48871, 3.64041)

forceModel = satellite.Propagator.ForceModel
forceModel.CentralBodyGravity.File = r'C:\Program Files\AGI\STK 12\STKData\CentralBodies\Earth\WGS84_EGM96.grv'
forceModel.CentralBodyGravity.MaxDegree = 21
forceModel.CentralBodyGravity.MaxOrder = 21
forceModel.Drag.Use = True
forceModel.Drag.DragModel.Cd = 0.01
forceModel.Drag.DragModel.AreaMassRatio = 0.01
forceModel.SolarRadiationPressure.Use = False

integrator = satellite.Propagator.Integrator
integrator.DoNotPropagateBelowAlt = -1e6
integrator.IntegrationModel = AgEVeIntegrationModel.eRKF78
integrator.StepSizeControl.Method = AgEVeMethod.eRelativeError
integrator.StepSizeControl.ErrorTolerance = 1e-13
integrator.StepSizeControl.MinStepSize = 0.1
integrator.StepSizeControl.MaxStepSize = 30
integrator.Interpolation.Method = AgEVeInterpolationMethod.eLagrange
integrator.Interpolation.Order = 7

satellite.Propagator.Propagate()

Set satellite propagator to HPOP and set force model properties

[MATLAB]

% 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 12\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();

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IAgVePropagatorHPOP Interface