Spacecraft.GetCartesianState(Variable, TimeSpan) Method

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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

Spacecraft.GetCartesianState(

Variable referenceFrame,


TimeSpan 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

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

 

 

 

frameEpoch


Description:

The epoch at which the Reference Frame will be evaluated.

 

 

 

Return Value

Type:

Array of number (size = 6)

 

 

Returns the Cartesian state.

 

Syntax

myArray1 = mySpacecraft1.GetCartesianState(myVariable1, myTimeSpan1);

 

 

See also

Spacecraft Object

Spacecraft.GetCartesianState

Spacecraft Propagation Guide

Coverage and Contact Analysis Guide