@Article{MurciaPiņerosPradDosSMora:2022:ApPeIn,
               author = "Murcia Piņeros, Jhonathan O. and Prado, Antonio Fernando 
                         Bertachini de Almeida and Dos Santos, Walter Abrah{\~a}o and 
                         Moraes, Rodolpho Vilhena de",
          affiliation = "{Universidade Federal de S{\~a}o Paulo (UNIFESP)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {Instituto Nacional de 
                         Pesquisas Espaciais (INPE)} and {Universidade Federal de S{\~a}o 
                         Paulo (UNIFESP)}",
                title = "Applying the perturbative integral in aeromaneuvers around Mars to 
                         calculate the cost",
              journal = "Scientific Reports",
                 year = "2022",
               volume = "12",
               number = "1",
                pages = "e5022",
                month = "Dec.",
             abstract = "The perturbative integral method was applied to quantify the 
                         contribution of external forces during a specific interval of time 
                         in trajectories of spacecraft around asteroids and under the 
                         Luni-solar influence. However, this method has not been used to 
                         quantify the contributions of drag in aerocapture and aerobraking. 
                         For this reason, the planet Mars is selected to apply this method 
                         during an aerogravity-assisted maneuver. Several trajectories are 
                         analyzed, making use of a drag device with area to mass ratios 
                         varying from 0.0 to 20.0 m2/kg, simulating solar sails or de-orbit 
                         devices. The mathematical model is based in the restricted 
                         three-body problem. The use of this maneuver makes it possible to 
                         obtain the variations of energy in the trajectory, replacing 
                         expensive maneuvers based on fuel consumption. To observe the 
                         effects of the maneuvers, different values of pericenter velocity 
                         and altitude were selected for prograde and retrograde orbits. The 
                         innovation of this research is the application of an integral 
                         method to quantify the delta-V of the aero gravity maneuver, 
                         comparing the cost of the maneuver with the traditional methods of 
                         space propulsion. The results allow the identification of orbits 
                         with conditions to capture, and the perturbative maps show the 
                         velocity variations.",
                  doi = "10.1038/s41598-022-08830-9",
                  url = "http://dx.doi.org/10.1038/s41598-022-08830-9",
                 issn = "2045-2322",
             language = "en",
           targetfile = "Murcia_2022_applying.pdf",
        urlaccessdate = "14 jun. 2024"
}