CelestialObject.SetCartesianState(Variable, Array, Variable) Method

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Description

Sets the Cartesian state of the CelestialObject in the specified frame, referenced from the CentralBody. This requires that the CelestialObject uses a TwoBody propagator, and will error if other propagators are used.

 

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

CelestialObject.SetCartesianState(

Variable epoch,


Array state,


Variable referenceFrame)

 

 

Arguments

epoch


Description:

The epoch at which the CelestialObject's state is evaluated.

 

 

state


Description:

array containing the Cartesian Elements

Required Size:

6

 

 

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

TIRF

8

Earth Fixed

9

Moon Fixed (Principle Axis Rotating)

10

Moon Principle Axis - Inertial at J2000

11

Moon Principle Axis - Inertial at Epoch

12

Moon Mean Earth - Rotating

13

Moon Mean Earth - Inertial at J2000

14

Moon Mean Earth - Inertial at Epoch

15

CIRF

16

Specify any CelestialObject.ReferenceFrameId

 

 

 

 

Syntax

myCelestialObject1.SetCartesianState(myVariable1, myArray1, myVariable2);

 

 

See also

CelestialObject Object

CelestialObject.SetCartesianState

CelestialObjects Guide