@InProceedings{GonçalvesRoccMora:2015:OrMaLu,
               author = "Gon{\c{c}}alves, Liana Dias and Rocco, Evandro Marconi and 
                         Moraes, Rodolpho Vilhena de",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {Universidade Federal 
                         de S{\~a}o Paulo (UNIFESP)}",
                title = "Orbital maneuvers of a lunar artificial satellite, under the 
                         action of gravitational and non-gravitational perturbation 
                         forces",
            booktitle = "Proceedings...",
                 year = "2015",
         organization = "International Symposium on Space Flight Dynamics, 25.",
             keywords = "Astrodynamics, Orbital Maneuvers, Continuous Thrust, 
                         Perturbations.",
             abstract = "The objective of this study is to analyze the orbital maneuvers of 
                         an artificial satellite around the Moon surface subject to 
                         perturbative forces of gravitational and not gravitational origin, 
                         such as lunar gravitational potential, gravitational attraction of 
                         the Earth and the Sun, lunar albedo and solar radiation pressure. 
                         Optimal maneuvers were obtained from the Lambert's problem 
                         solution (Two Point Boundary Value Problem) in order that is 
                         minimized the fuel consumption. Then a selected maneuver was 
                         simulated assuming a more realistic model of the propulsion 
                         system. For both cases is analyzed the actions of thrusters, fuel 
                         consumption and deviations in the orbital elements that 
                         characterize the lunar orbit of artificial satellite. The 
                         deviation is obtained by a comparison between the actual state and 
                         the reference state of the vehicle at each step of the simulation. 
                         The actual state is calculated every step of the simulation and 
                         the reference state is determined considering the desired final 
                         orbital elements for the trajectory.",
  conference-location = "Munich, Germany",
      conference-year = "19-23 Oct.",
        urlaccessdate = "01 maio 2024"
}