Spacecraft.NoradEquinoctialP Property

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Description

This property has been Deprecated. Please use the SGP4.EquinoctialP property instead.

The p component of the Norad based Equinoctial element set, defined by: p = tan(i/2)sin(RAAN), where i is the orbit inclination and RAAN is the Norad Right Ascension of the Ascending Node. These orbit properties are with respect to the True Equator Mean Equinox coordinate frame.

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:	-0.979230283604418

Syntax

myVariable1 = mySpacecraft1.NoradEquinoctialP;

mySpacecraft1.NoradEquinoctialP = myVariable1;