Spacecraft.NonSingularE2 Property

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Description

The e2 component of the Nonsingular Keplerian element set, defined by e2 = e*sin(RAAN + w), where e, w, and RAAN are the Keplerian Eccentricity, Argument of Perigee and Right Ascension of the Ascending Node respectively. 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:	1.4185020636563E-06

Syntax

myVariable1 = mySpacecraft1.NonSingularE2;

mySpacecraft1.NonSingularE2 = myVariable1;