@Article{Rocco:2015:GrDiGe,
               author = "Rocco, Evandro Marconi",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)}",
                title = "Gravitational disturbances generated by the Sun, Phobos and Deimos 
                         in orbital maneuvers around Mars with automatic correction of the 
                         semi-major axis",
              journal = "Journal of Physics: Conference Series",
                 year = "2015",
               volume = "641",
                pages = "012027",
             keywords = "Astrodynamics, Orbital Maneuvers, Orbital Transfer.",
             abstract = "The objective of this work is to analyze orbital maneuvers of a 
                         spacecraft orbiting Mars, considering disturbance effects due to 
                         the gravitational attraction of the Sun, Phobos and Deimos, beyond 
                         the disturbances due to the gravitational potential of Mars. To 
                         simulate the trajectory, constructive aspects of the propulsion 
                         system were considered. Initially ideal thrusters, capable of 
                         applying infinite magnitude of the thrust, were used. Thus, 
                         impulsive optimal maneuvers were obtained by scanning the 
                         solutions of the Lamberts problem in order to select the maneuver 
                         of minimum fuel consumption. Due to the impossibility of applying 
                         an impulse, the orbital maneuver must be distributed in a 
                         propulsive arc around the position of the impulse given by the 
                         solution of the Lamberts problem. However the effect of the 
                         propulsive arc is not exactly equivalent to the application of an 
                         impulse due to the errors in magnitude and direction of applied 
                         thrust. Therefore, the influence of the thrusters capacity in the 
                         trajectory was evaluated for a more realistic model instead of the 
                         ideal case represented by the impulsive approach. Beyond the 
                         evaluation of the deviation in the orbital path, was considered an 
                         automatic correction of the semi-major axis using continuous low 
                         thrust controlled in closed loop to minimize the error in the 
                         trajectory after the application of the main thrust.",
                  doi = "10.1088/1742-6596/641/1/012027",
                  url = "http://dx.doi.org/10.1088/1742-6596/641/1/012027",
                 issn = "1742-6588",
                label = "lattes: 0088337156908774 1 Rocco:2015:GrDiGe",
             language = "pt",
           targetfile = "1_rocco2.pdf",
        urlaccessdate = "27 abr. 2024"
}