Description
Returns the X, Y, Z, VX, VY and VZ components of the current state of the Spacecraft in the specified frame, referenced from the CentralBody. The reference frame will be evaluated at the specified frameEpoch.
Timing Precision Mode
This page describes functionality in nanosecond timing precision mode.
Click here to see the documentation for this object in millisecond timing precision mode.
Method Signature
Arguments
referenceFrame
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Description:
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The reference frame in which the state elements will be evaluated.
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Valid Values:
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Value
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Label
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1
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ICRF
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2
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Mean of J2000 Earth Ecliptic
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3
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Mean of 1950 Earth Equator
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4
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Mean of Date Earth Equator
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5
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True Equator Mean Equinox
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6
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True of Date Earth Equator
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7
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TIRF
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8
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Earth Fixed
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9
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Moon Fixed (Principle Axis Rotating)
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10
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Moon Principle Axis - Inertial at J2000
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11
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Moon Principle Axis - Inertial at Epoch
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12
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Moon Mean Earth - Rotating
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13
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Moon Mean Earth - Inertial at J2000
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14
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Moon Mean Earth - Inertial at Epoch
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15
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CIRF
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16
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Specify any CelestialObject.ReferenceFrameId
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frameEpoch
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Description:
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The epoch at which the Reference Frame will be evaluated.
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Return Value
Type:
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Array of number (size = 6)
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Returns the Cartesian state.
Syntax
myArray1 = mySpacecraft1.GetCartesianState(myVariable1, myTimeSpan1);
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See also
Spacecraft Object
Spacecraft.GetCartesianState
Spacecraft Propagation Guide
Coverage and Contact Analysis Guide
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