Description
Returns the A, E, I, RAAN, W, TA components of the current state of the Spacecraft in the specified frame, referenced from the CentralBody.
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
Spacecraft.GetKeplerianState(
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Variable referenceFrame)
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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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Moon Principle Axis - Inertial at J2000
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8
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Moon Principle Axis - Inertial at Epoch
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9
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Moon Mean Earth - Inertial at J2000
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10
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Moon Mean Earth - Inertial at Epoch
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11
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CIRF
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12
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Specify any Inertial CelestialObject.ReferenceFrameId
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Return Value
Type:
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Array of number (size = 6)
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Returns the Keplerian state.
Syntax
myArray1 = mySpacecraft1.GetKeplerianState(myVariable1);
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See also
Spacecraft Object
Spacecraft.GetKeplerianState
Spacecraft Propagation Guide
Coverage and Contact Analysis Guide
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