The angle or arc, as seen from a focus of an elliptical orbit, from the ascending node to the closest approach of the orbiting body to the focus; the angle is measured in the orbital plane in the direction of motion of the orbiting body. Also known as argument of perihelion.
Five out of six orbital elements, semimajor axis a, inclination i, longitude of ascending node [OMEGA], argument of perigee [omega], and mean anomaly M, are used as optimization design variables, while eccentricity e is kept as a constant.
The measured value for the argument of perigee precession can also be used to constrain a non-Newtonian contribution to the satellite dynamics, as discussed in Section 2.1.
As the argument of perigee is 90[degrees], the minimum value grows at the lowest speed, and it has the fastest growth rate when the argument of perigee is 60[degrees].
The semi-major axis and argument of perigee are more sensitive to solar activity, while orbital inclination for the equatorial plane is relatively unaffected.
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