Description

Object Model

Public Methods

AppendRun	Append the existing ephemeris with another individual segment mode run
AppendRunFromState	Append the existing ephemeris with another individual segment mode run, starting at a specified state. Ephemeris is cleared from time based on clear direction.
AppendRunFromTime	Append the existing ephemeris with another individual segment mode run, starting at a specified time. Ephemeris is cleared from time based on clear direction.
ApplyAllProfileChanges	Applies all active profile changes in all target sequences.
BeginRun	Begins an individual segment mode run.
ClearDWCGraphics	Clears the draw while calculating graphics
EndRun	Ends an individual segment mode run.
ResetAllProfiles	Resets all active profiles in all target sequences.
RunMCS	Runs the current MCS.
RunMCS2	Runs the current MCS and returns an error code.

Public Properties

AutoSequence	The Automatic Sequences.
CalculationGraphs	The calculation graphs.
MainSequence	The Mission Control Sequence.
Options	The Mission Control Sequence options.

Example

Configure the Astrogrator propagator

[C#]

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satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorAstrogator);    IAgVADriverMCS driver = satellite.Propagator as IAgVADriverMCS;    // Remove if necessary  driver.MainSequence.RemoveAll();    // Configure properties as necessarily  driver.Options.DrawTrajectoryIn3D = true;  driver.Options.GraphicsUpdateRate = 0.90;  driver.Options.UpdateAnimationTimeForAllObjects = false;  driver.Options.StoppingConditionTimeTolerance = 0.00000005;  driver.Options.EnableLogging = true;

Configure the Astrogrator propagator

[Visual Basic .NET]

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satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorAstrogator) Dim driver As IAgVADriverMCS = TryCast(satellite.Propagator, IAgVADriverMCS) ' Remove if necessary driver.MainSequence.RemoveAll() ' Configure properties as necessarily driver.Options.DrawTrajectoryIn3D = True driver.Options.GraphicsUpdateRate = 0.9 driver.Options.UpdateAnimationTimeForAllObjects = False driver.Options.StoppingConditionTimeTolerance = 5E-08 driver.Options.EnableLogging = True

Set satellite propagator to Astrogator and clear segments

[MATLAB]	Copy Code
% IAgSatellite satellite: Satellite object  satellite.SetPropagatorType('ePropagatorAstrogator');  driver = satellite.Propagator;  %Clear all segments from the MCS  driver.MainSequence.RemoveAll();

Run the Astrogator MCS

[MATLAB]	Copy Code
% IAgVADriverMCS driver: MCS driver interface  driver.RunMCS;

Create a new component through the Component Browser

[MATLAB]

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% IAgVADriverMCS driver: MCS driver interface  % IAgScenario scenario: Scenario object  %Get the Prop Funct Folder  compBrowser = scenario.ComponentDirectory.GetComponents('eComponentAstrogator').GetFolder('Propagator Functions');  %Get the Atmospheric Models Folder  atmos = compBrowser.GetFolder('Atmospheric Models');  %Grab the Mars Exponential Model  mars = atmos.Item('Exponential - Mars');  %Make a copy of the Model to Edit it  marsClone = mars.CloneObject;    %Grab a handle of the new Mars Model and edit properties  newMars = atmos.Item('Exponential - Mars1');  newMars.Name = 'New Mars';  newMars.ReferenceAltitude = 0; %km  newMars.ReferenceDensity = 20000000; %kg/km^3  newMars.ScaleAltitude = 11.1; %km

CoClasses that Implement IAgVADriverMCS