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Moon Perturbation - Argument of Perigee

Last modified by
on
Nov 6, 2024, 3:30:57 PM
Created by
on
Jun 6, 2014, 2:27:03 AM
.ωMoon=0.00169⋅4-5⋅sin2(i)n
(i)Orbit Inclination
(n)Number of orbit revolutions per day
Tags
Sun Orbital Mechanics Moon Perturbations Lunar Astro
UUID
0bbe2f83-ed22-11e3-b7aa-bc764e2038f2

This equation computes the rate of change of the argument of perigee, .ω, of an orbit where the rate of change in deg/day results from the Moon's third-body gravitational influence on the orbit.  The inputs to this equation are the orbit inclination (i) and the number of orbit revolutions per day (n).

 

/attachments/0bbe2f83-ed22-11e3-b7aa-bc764e2038f2/MoonPerturbationArgumentofPerigee-illustration.png

Notes

This computation is an approximation, as it neglects the perturbation caused by the change in orientation of the orbital plane relative to the Moon's orbital plane.
This equation, Moon Perturbation - Argument of Perigee, is used in 1 page
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