@Article{Prado:2013:ApLuPe,
               author = "Prado, Antonio Fernando Bertachini de Almeida",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)}",
                title = "Searching for orbits with minimum fuel consumption for 
                         station-keeping maneuvers: An application to lunisolar 
                         perturbations",
              journal = "Mathematical Problems in Engineering",
                 year = "2013",
               volume = "2013",
               number = "ID 415015",
                pages = "1--11",
             keywords = "astrodin{\^a}mica, manobras orbitais.",
             abstract = "The present paper has the goal of developing a new criterion to 
                         search for orbits that minimize the fuel consumption for 
                         stationkeeping maneuvers.This approach is based on the integral 
                         over the time of the perturbing forces.This integral measures the 
                         total variation of velocity caused by the perturbations in the 
                         spacecraft, which corresponds to the equivalent variation of 
                         velocity that an engine should deliver to the spacecraft to 
                         compensate the perturbations and to keep its orbit Keplerian all 
                         the time.This integral is a characteristic of the orbit and the 
                         set of perturbations considered and does not depend on the type of 
                         engine used. In this sense, this integral can be seen as a 
                         criterion to select the orbit of the spacecraft.When this value 
                         becomes larger, more consumption of fuel is required for the 
                         station keeping, and, in this sense, less interesting is the 
                         orbit.This concept can be applied to any perturbation. In the 
                         present research, as an example, the perturbation caused by a 
                         third body is considered. Then, numerical simulations considering 
                         the effects of the Sun and the Moon in a satellite around the 
                         Earth are shown to exemplify the method.",
                  doi = "10.1155/2013/415015",
                  url = "http://dx.doi.org/10.1155/2013/415015",
                 issn = "1024-123X",
                label = "lattes: 7340081273816424 1 Prado:2013:ApLuPe",
             language = "en",
           targetfile = "415015.pdf",
        urlaccessdate = "01 maio 2024"
}