Optimal finite thrust geostationary satellite positioning with operational constraints

Abstract This paper is concerned with minimum cost, finite thrust, geostationary satellite positioning strategies. Initial satellite orbit is an Ariane transfer one and the apogee motor is supposed able to deliver multiple burns. Operational constraints such as fixed number of satellite revolutions or ground station visibility during manoeuvres are taken into account. A numerical iterative projected gradient type method, using multiple adjoint vectors, is carried on. Algorithm aptitude to build up optimal solutions for realistic transfer and rendezvous manoeuvres is demonstrated.