RotatingPulsatingSystem.ReferenceVector Property

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Description

The second vector used in establishing the frame. For a closed, bounded orbit (such as Earth-Moon), this should be the velocity vector of the Secondary Object. For alternately retro- and prograde motion (such as Earth-Mars), this should be a nearly constant vector, such as Mean of J000 Earth Ecliptic North.

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.

Attributes

Type:

integer

Access:

read/write

Default Value:

0 ( Relative Velocity at the Instantaneous Time )

Valid Values:

Value	Label
0	Relative Velocity at the Instantaneous Time
1	ICRF North
2	Mean of J2000 Earth Ecliptic North

Syntax

myVariable1 = myRotatingPulsatingSystem1.ReferenceVector;

myRotatingPulsatingSystem1.ReferenceVector = myVariable1;