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 millisecond timing precision mode. Millisecond timing precision mode is deprecated and will be removed in a future release. We recommend that you migrate your Mission Plans to nanosecond timing precision mode.
Attributes
Type: |
number |
Access: |
read |
Units: |
deg/day |
Syntax
myVariable1 = mySpacecraft1.NodeRate; |
See also
Coverage and Contact Analysis Guide