Spacecraft.P Property

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Description

Represents the osculating value of the semi-latus rectum of the Spacecraft's orbit. The value of the semi-latus rectum is equal to the square of the specific angular momentum of the orbit (angular momentum per unit mass) divided by the central body's gravity constant m.

 

 

 

Timing Precision Mode

This page describes functionality in nanosecond timing precision mode.

 

Attributes

Type:

number

Access:

read

Units:

km

 

Syntax

myVariable1 = mySpacecraft1.P;

 

See also

Spacecraft Object

Spacecraft Propagation Guide

Coverage and Contact Analysis Guide