@Article{OliveiraPrad:2014:MaOrLo,
               author = "Oliveira, Thais Carneiro and Prado, Antonio Fernando Bertachini de 
                         Almeida",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)}",
                title = "Mapping orbits with low station keeping costs for constellations 
                         of satellites based on the integral over the time of the 
                         perturbing forces",
              journal = "Acta Astronautica",
                 year = "2014",
               volume = "104",
               number = "1",
                pages = "350--361",
             keywords = "Orbits, Trajectories, Orbital maneuvers, Perturbation forces, 
                         Perturbing forces, Spacecraft dynamics, Station keeping, Space 
                         flight.",
             abstract = "The present paper is concerned with the search for orbits that 
                         have potential to require low fuel consumption for station-keeping 
                         maneuvers for constellations of satellites. The method used to 
                         study this problem is based on the integral over the time of the 
                         undesired perturbing forces. This integral measures the change of 
                         velocity caused by the perturbation forces acting on the 
                         satellite, so mapping orbits that are less perturbed, which 
                         generates good candidates for orbits that requires low fuel 
                         consumption for station-keeping maneuvers. The integral over the 
                         time depends only on the orbit of the spacecraft and the dynamical 
                         system considered. The type of engine and the control technique 
                         applied to the spacecraft are not considered to search for those 
                         orbits. It can be a good strategy to be applied for a first 
                         mapping of orbits. For this search, it is analyzed the integral of 
                         orbits with different values of the Keplerian elements in order to 
                         find the best ones with respect to this criterion. The 
                         perturbations considered are the ones caused by the third body, 
                         which includes the Sun and the Moon, and the J2 term of the 
                         geopotential. The results presented here show numerical 
                         simulations to obtain the integral of those perturbing forces for 
                         different orbits. The GPS and the Molniya constellations are used 
                         as examples for those calculations.",
                  doi = "10.1016/j.actaastro.2014.06.035",
                  url = "http://dx.doi.org/10.1016/j.actaastro.2014.06.035",
                 issn = "0094-5765",
                label = "scopus 2014-11 OliveiraPrad:2014:MaOrLo",
             language = "en",
        urlaccessdate = "27 abr. 2024"
}