Spacecraft.NonSingularE4 Property

Top

Description

The e4 component of the NonSingular Keplerian element set, defined by: e4 = sin(i/2) cos(RAAN), where i is the orbit inclination and RAAN is the Keplerian Right Ascension of the Ascending Node. These orbit properties are with respect to the ICRF.

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.

Attributes

Type:	number
Access:	read/write
Default Value:	0.40040647790312

Syntax

myVariable1 = mySpacecraft1.NonSingularE4;

mySpacecraft1.NonSingularE4 = myVariable1;