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Sun Perturbation - RAAN

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Last modified by
on
Nov 6, 2024, 3:31:44 PM
Created by
on
Jun 6, 2014, 2:19:13 AM
.ΩSun=-0.00154⋅cos(i)n
(i)Orbit Inclination
(n)Number of orbit revolutions per day
Tags
Sun Orbital Mechanics Moon Perturbations Lunar Verified Astro
UUID
f37f8f5e-ed20-11e3-b7aa-bc764e2038f2

This equation computes the rate of change of the right ascension of the ascending node  (RAAN) of an orbit where the rate of change in deg/day (.Ω) 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/f37f8f5e-ed20-11e3-b7aa-bc764e2038f2/SunPerturbationRAAN-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 Sun's ecliptic plane.
This equation, Sun Perturbation - RAAN, is used in 1 page
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