Spacecraft.NodeRate Property

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Description

Returns an estimate of the rate of change of the ascending node with respect to time. This estimate is based on the Gauss VOP equation, where:

J2= geopotential coefficient for the oblateness of the Earth

n = mean motion of the Spacecraft

Re= equatorial radius of the Earth

a = Spacecraft's osculating semi-major axis

e = Spacecraft's osculating eccentricity

i = Spacecraft's osculating inclination

 

 

Timing Precision Mode

This page describes functionality in nanosecond timing precision mode.

 

Attributes

Type:

number

Access:

read

Units:

deg/day

 

Syntax

myVariable1 = mySpacecraft1.NodeRate;

 

See also

Spacecraft Object

Spacecraft Propagation Guide

Coverage and Contact Analysis Guide