@Article{VendittiAlmePrad:2020:UsInIn,
               author = "Venditti, Flaviane C. F. and Almeida J{\'u}nior, Allan K. de and 
                         Prado, Antonio Fernando Bertachini de Almeida",
          affiliation = "{University of Central Florida} and {University of Central 
                         Florida} and {Instituto Nacional de Pesquisas Espaciais (INPE)}",
                title = "Using an integral index to search for orbits around oblate 
                         spheroids",
              journal = "Planetary and Space Science",
                 year = "2020",
               volume = "192",
                pages = "e105063",
                month = "Nov.",
             keywords = "Asteroids, Orbital perturbation, Oblate spheroids, Orbit 
                         stability, Astrodynamics.",
             abstract = "An integral index is used in this manuscript to search for the 
                         least gravitationally perturbed orbits around an oblate spheroid. 
                         Although there are missions where perturbations are desired, such 
                         as Sun-synchronous orbits, near Keplerian orbits can be useful in 
                         some cases during the whole mission or partially, helping to keep 
                         the oscillations of the orbital parameters in the minimum possible 
                         level, which can be interesting to observe celestial bodies. These 
                         orbits are also good candidates to require a lower number of 
                         station-keeping maneuvers, helping to simplify the logistic of the 
                         mission. The index used is available in the literature and it is 
                         based on the integration of the accelerations suffered by a 
                         spacecraft over time. An oblate spheroid is used to represent the 
                         approximate shape of non-spherical bodies because it has a closed 
                         equation for the potential, which makes it ideal for the analysis 
                         proposed, and because it is a shape similar to what is found for 
                         several objects in the small bodies population. The Lagrange 
                         planetary equations are also used to map orbits that have a 
                         minimum rate of variation in their orbital elements, and compared 
                         with the results obtained with the integral index. The results 
                         show a very good agreement between the index and the variations of 
                         the orbital elements of the spacecraft, in particular in terms of 
                         locating the least perturbed orbits to place the spacecraft.",
                  doi = "10.1016/j.pss.2020.105063",
                  url = "http://dx.doi.org/10.1016/j.pss.2020.105063",
                 issn = "0032-0633",
             language = "en",
           targetfile = "venditti_using.pdf",
        urlaccessdate = "25 abr. 2024"
}