Divided by Time Multiplied

by Qosmic Qey

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COMPUTATION OF SATELLITE PERTURBATIONS

The following notations are used:

n = semimajor axis of satellite orbit
e = eccentricity
i = angle of inclination to equatorial plane
M = argument of perigee
n = right ascension of ascending node
g = mean anomaly
r = position vector
X, y, z = rectangular coordinates
r = radius
f = true anomaly

There is no necessity to perform the actual multiplication; it can be done separately for each case.

The proposed scheme leads to a form of the development which is standard in celestial mechanics. It differs from Kozai's scheme only by arrangement. The following method was used to obtain the development on the automatic computing machine:

G= cos^i- cos2 -y- cos (0. + (9 - g' - CO')
+ sin2Y cos2^ cos (a, - + g' + co')
+ cos^i sin2 Y cos (f^ + + g' + ^' )

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released July 16, 2015

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