Spacecraft.GetKeplerianState(Variable, Variable) Method

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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. 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

Spacecraft.GetKeplerianState(	Variable referenceFrame,
	Variable frameEpoch)

Arguments

referenceFrame

Description:

The reference frame in which the state elements will be evaluated.

Valid Values:

Value	Label
1	ICRF
2	Mean of J2000 Earth Ecliptic
3	Mean of 1950 Earth Equator
4	Mean of Date Earth Equator
5	True Equator Mean Equinox
6	True of Date Earth Equator
7	Moon Principle Axis - Inertial at J2000
8	Moon Principle Axis - Inertial at Epoch
9	Moon Mean Earth - Inertial at J2000
10	Moon Mean Earth - Inertial at Epoch
11	CIRF
12	Specify any Inertial CelestialObject.ReferenceFrameId

frameEpoch
Description:	The epoch at which the Reference Frame will be evaluated.

Return Value

Type:

Array of number (size = 6)

Returns the Keplerian state.

Syntax

myArray1 = mySpacecraft1.GetKeplerianState(myVariable1, myVariable2);