Description

HPOP propagator interface.

Object Model

Public Methods

Propagate

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

Public Properties

Covariance	Get the covariance parameters.
EphemerisInterval	The propagator's ephemeris interval.
ForceModel	Get the force model parameters.
InitialState	Get the satellite's initial state.
Integrator	Get the integrator parameters.
StartTime	This property is deprecated. Use EphemerisInterval to configure the propagation interval. Start time. Uses DateFormat Dimension.
Step	Step size. Uses Time Dimension.
StopTime	This property is deprecated. Use EphemerisInterval to configure the propagation interval. Stop time. Uses DateFormat Dimension.

Interfaces

Implemented Interface
IAgVePropagator

Example

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();

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

[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;

CoClasses that Implement IAgVePropagatorHPOP

Name
AgVePropagatorHPOP

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