Description

Properties for the Mission Control Sequence.

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	Get the Automatic Sequences.
CalculationGraphs	Get the calculation graphs.
FlightDynamicsRecordCreator	Get the flight dynamics record creator.
MainSequence	Get the Mission Control Sequence.
Options	Get the Mission Control Sequence options.

Interfaces

Implemented Interface
IAgVePropagator

CoClasses that Implement IAgVADriverMCS

Name
AgVADriverMCS

Example

Configure the Astrogrator propagator

[C#]

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]

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

[Python - STK API]

# IAgSatellite satellite: Satellite object
satellite.SetPropagatorType(AgEVePropagatorType.ePropagatorAstrogator)
driver = satellite.Propagator
# Clear all segments from the MCS
driver.MainSequence.RemoveAll()

Run the Astrogator MCS

[Python - STK API]

# IAgVADriverMCS driver: MCS driver interface
driver.RunMCS()

Set satellite propagator to Astrogator and clear segments

[MATLAB]

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

Run the Astrogator MCS

[MATLAB]

% IAgVADriverMCS driver: MCS driver interface
driver.RunMCS;

Create a new component through the Component Browser

[MATLAB]

% 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

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IAgVADriverMCS Interface