author = "Venditti, Flaviane Cristine Faria and Prado, Antonio Fernando 
                         Bertachini de Almeida",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)}",
                title = "Mapping orbits regarding perturbations due to the gravitational 
                         field of a cube",
              journal = "Mathematical Problems in Engineering",
                 year = "2015",
               volume = "2015",
                pages = "493903",
             abstract = "The orbital dynamics around irregular shaped bodies is an actual 
                         topic in astrodynamics, because celestial bodies are not perfect 
                         spheres. When it comes to small celestial bodies, like asteroids 
                         and comets, it is even more import to consider the nonspherical 
                         shape. The gravitational field around them may generate 
                         trajectories that are different from Keplerian orbits. Modeling an 
                         irregular body can be a hard task, especially because it is 
                         difficult to know the exact shape when observing it from the 
                         Earth, due to their small sizes and long distances. Some asteroids 
                         have been observed, but it is still a small amount compared to all 
                         existing asteroids in the Solar System. An approximation of their 
                         shape can be made as a sum of several known geometric shapes. Some 
                         three-dimensional figures have closed equations for the potential 
                         and, in this work, the formulation of a cube is considered. The 
                         results give the mappings showing the orbits that are less 
                         perturbed and then have a good potential to be used by spacecrafts 
                         that need to minimize station-keeping maneuvers. Points in the 
                         orbit that minimizes the perturbations are found and they can be 
                         used for constellations of nanosatellites.",
                  doi = "10.1155/2015/493903",
                  url = "http://dx.doi.org/10.1155/2015/493903",
                 issn = "1024-123X",
             language = "en",
        urlaccessdate = "04 dez. 2020"