Description

Properties for an Initial State segment.

Public Methods

DisableControlParameter	Disables a control parameter.
EnableControlParameter	Enables a control parameter.
IsControlParameterEnabled	Sees if a control is enabled.
SetElementType	Selects an coordinate type.

Public Properties

ControlParametersAvailable	Returns whether or not the control parameters can be set.
CoordSystemName	Gets or sets the coordinate system.
Element	Get the elements of the selected coordinate type.
ElementType	Get the coordinate type.
FuelTank	Get the fuel tank parameters.
OrbitEpoch	Gets or sets the orbit epoch. Uses DateFormat Dimension.
SpacecraftParameters	Get the spacecraft parameters.
UserVariables	Interface used to modify user variables for the initial state segment.

Interfaces

Implemented Interface
IAgVAMCSSegment
IAgComponentInfo
IAgCloneable

CoClasses that Implement IAgVAMCSInitialState

Name
AgVAMCSInitialState

Example

Configure initial state segment

[C#]

// Add a new segment and cast the segment to the IAgVAMCSInitialState interface
IAgVAMCSSegment segment = driver.MainSequence.Insert(AgEVASegmentType.eVASegmentTypeInitialState, "Inner Orbit", "-");
IAgVAMCSInitialState initState = segment as IAgVAMCSInitialState;

initState.CoordSystemName = "CentralBody/Earth Fixed";
initState.OrbitEpoch = "1 Jan 2012 12:00:00.000";

// Set element type and cast the Element property to the appropriate interface
// configure the element as necessary
initState.SetElementType(AgEVAElementType.eVAElementTypeCartesian);
IAgVAElementCartesian cartesian = initState.Element as IAgVAElementCartesian;
cartesian.Vx = 8051.21;
cartesian.Y = 55;
cartesian.Z = 0;
cartesian.Vx = 0.45;
cartesian.Vy = 8.10158;
cartesian.Vz = 3.51009;

// Configure fuel tank if necessary
initState.FuelTank.FuelDensity = 1001;
initState.FuelTank.FuelMass = 501;
initState.FuelTank.TankPressure = 5001;
initState.FuelTank.TankTemperature = 292;

// Configure spacecraft parameters
initState.SpacecraftParameters.Cd = 2.3;
initState.SpacecraftParameters.Ck = 1.1;
initState.SpacecraftParameters.Cr = 1.3;
initState.SpacecraftParameters.DragArea = 21;
initState.SpacecraftParameters.DryMass = 501;
initState.SpacecraftParameters.K1 = /*$k1$K1*/2;
initState.SpacecraftParameters.K2 = 3;
initState.SpacecraftParameters.RadiationPressureArea = 23.0;
initState.SpacecraftParameters.SolarRadiationPressureArea = 22.0;

Configure initial state segment

[Visual Basic .NET]

' Add a new segment and cast the segment to the IAgVAMCSInitialState interface
Dim segment As IAgVAMCSSegment = driver.MainSequence.Insert(AgEVASegmentType.eVASegmentTypeInitialState, "Inner Orbit", "-")
Dim initState As IAgVAMCSInitialState = TryCast(segment, IAgVAMCSInitialState)

initState.CoordSystemName = "CentralBody/Earth Fixed"
initState.OrbitEpoch = "1 Jan 2012 12:00:00.000"

' Set element type and cast the Element property to the appropriate interface
' configure the element as necessary
initState.SetElementType(AgEVAElementType.eVAElementTypeCartesian)
Dim cartesian As IAgVAElementCartesian = TryCast(initState.Element, IAgVAElementCartesian)
cartesian.Vx = 8051.21
cartesian.Y = 55
cartesian.Z = 0
cartesian.Vx = 0.45
cartesian.Vy = 8.10158
cartesian.Vz = 3.51009

' Configure fuel tank if necessary
initState.FuelTank.FuelDensity = 1001
initState.FuelTank.FuelMass = 501
initState.FuelTank.TankPressure = 5001
initState.FuelTank.TankTemperature = 292

' Configure spacecraft parameters
initState.SpacecraftParameters.Cd = 2.3
initState.SpacecraftParameters.Ck = 1.1
initState.SpacecraftParameters.Cr = 1.3
initState.SpacecraftParameters.DragArea = 21
initState.SpacecraftParameters.DryMass = 501
initState.SpacecraftParameters.K1 = 2
initState.SpacecraftParameters.K2 = 3
initState.SpacecraftParameters.RadiationPressureArea = 23
initState.SpacecraftParameters.SolarRadiationPressureArea = 22

Insert an Initial State Segment into the MCS and configure

[MATLAB]

% IAgScenario scenario: Scenario object
% IAgVADriverMCS driver: MCS driver interface
initState = driver.MainSequence.Insert('eVASegmentTypeInitialState', 'Inner Orbit', '-');
initState.InitialState.Epoch = scenario.StartTime;
initState.SetElementType('eVAElementTypeKeplerian');
kep = initState.Element;
kep.PeriapsisRadiusSize = 6700;
kep.ArgOfPeriapsis = 0;
kep.Eccentricity = 0;
kep.Inclination = 0;
kep.RAAN = 0;
kep.TrueAnomaly = 0;

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IAgVAMCSInitialState Interface