Geostationary Satellites Collocation

Abstract

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

“…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 . m denotes the spacecraft mass.…”

“…The secular and long-periodic variations in inclination due to the lunisolar perturbations are provided in this section. The total variation in the inclination vector is a sum of the secular and the long-periodic terms [14,16]: …”

“…The variational equations governing the change in the eccentricity vector due to the solar radiation pressure are given as [16] = − where C r is the solar radiation pressure coefficient (usually with a value between 1 and 2 [30]), which depends on the reflective properties of the space object surface; P r is the solar radiation pressure per square meter, = × − P 4.65 10 N/m r 6 2 ; S is the average cross-sectional area facing to the Sun and m is the mass of the satellite. The independent variable t is replaced by u s in Eqs.…”

“…However, an electric propulsion satellite usually equips with large-area solar arrays panel to provide the electric power needed for the on-board low thrust propulsion system. The principal effect of solar radiation pressure on a geostationary satellite is to produce a longperiod perturbation in the eccentricity with a period of 1 year [15][16][17]. Therefore, in addition to the effect of Earth's triaxiality on the semimajor axis and longitude as well as the lunisolar effects on the inclination, the effect of the solar radiation pressure on the eccentricity should also be taken into account in the low-thrust transfer between GEO parking slots.…”

Safe rendezvous scenario design for geostationary satellites with collocation constraints

“…The GEO region is very crowded now [1,2] and appropriate remediation measures need to be implemented to protect the future usefulness of this natural resource [3]. On-orbit servicing on GEO, involving life extension, robotic manipulations, inspections, auxiliary reorbiting, and debris removing, is an efficient method to make good use of GEO [4].…”