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 millisecond timing precision mode.

 

Attributes

Type:

number

Access:

read/write

Default Value:

-0.979230283604418

 

Syntax

myVariable1 = mySpacecraft1.NoradEquinoctialP;

 

mySpacecraft1.NoradEquinoctialP = myVariable1;

 

See also

Spacecraft Object

Spacecraft Propagation Guide

Coverage and Contact Analysis Guide