Stationkeeping manoeuvres for geostationary satellites using feedback control techniques

Minimum-fuel station-change for geostationary satellites using low-thrust considering perturbations

“…3 that the component i y in these three cases are always greater than zero, and they basically exceed 0.2°for a 100 days transfer and the component i x is relatively small and not necessarily greater than zero. The numerical simulation results are hence consistent with the previous study [27]. The variation in eccentricity vector increases with the transfer duration, and the magnitude of eccentricity reaches 0.001 when the transfer duration is 100 days.…”

“…To avoid singularity issues, a set of nonsingular orbital elements is used in this work [27], where Ω is the right ascension of the ascending node, ω is the argument of perigee, e is the eccentricity, i is the inclination, M is the mean anomaly, and θ G is the Greenwich sidereal time, measured from the instantaneous equinox. When low-thrust propulsion is considered, the equations of motions are given as [16] ( ) ( ) where v represents the velocity of near-circular orbits, v ¼na, n is the mean motion, Ω E is the Earth's rotation rate, l is the right ascension of the satellite, Ω ω = + + l M .…”

Station-Keeping Maneuvers to Control the Inclination Evolution of Areostationary Satellites

“…Taking into account these numerical results, we only consider, in the equation for the inclination vector evolution (1), the dominant effect due to solar attraction. Then we obtain, in degrees per year [27]. The areostationary secular inclination drift is about 10 times lower than the geostationary one and with constant direction due to the Phobos and Deimos negligible effects.…”

A station-keeping control method for GEO spacecraft based on autonomous control architecture

“…(5), the perturbation velocity of inclination vector i P can be obtained [23,24]. Let its maximum value be i P max , and the maximum drift during the control-waiting time is calculated:…”