Spacecraft.EquinoctialP Property

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Description

The p component of the Equinoctial element set, defined by: p = tan(i/2)sin(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 Mean of J2000 Earth-Equator coordinate frame.

 

Timing Precision Mode

This page describes functionality in millisecond timing precision mode.

Click here to see the documentation for this object in nanosecond timing precision mode.

 

Attributes

Type:

number

Access:

read/write

Default Value:

-0.734374777448554

 

Syntax

myVariable1 = mySpacecraft1.EquinoctialP;

 

mySpacecraft1.EquinoctialP = myVariable1;

 

See also

Spacecraft Object

Spacecraft Propagation Guide

Coverage and Contact Analysis Guide