Description
Sets the Keplerian 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 millisecond timing precision mode. Millisecond timing precision mode is deprecated and will be removed in a future release. We recommend that you migrate your Mission Plans to nanosecond timing precision mode.
Click here to see the documentation for this object in nanosecond timing precision mode.
Method Signature
Arguments
state
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Description:
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array containing the Keplerian Elements in order: {A, E, I, RAAN, W, TA}
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Required Size:
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6
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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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frameEpoch
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Description:
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The epoch at which the Reference Frame will be evaluated.
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Syntax
mySpacecraft1.SetKeplerianState(myArray1, myVariable1, myVariable2);
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See also
Spacecraft Object
Spacecraft.SetKeplerianState
Spacecraft Propagation Guide
Coverage and Contact Analysis Guide
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