References in periodicals archive ?
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.