@Article{SantosPradOlivSant:2018:AnImMa,
               author = "Santos, Willer Gomes dos and Prado, Antonio Fernando Bertachini de 
                         Almeida and Oliveira, Geraldo Magela Couto and Santos, Leonardo 
                         Barbosa Torres dos",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {Instituto Nacional de 
                         Pesquisas Espaciais (INPE)} and {Instituto Nacional de Pesquisas 
                         Espaciais (INPE)}",
                title = "Analysis of impulsive maneuvers to keep orbits around the asteroid 
                         2001SN263",
              journal = "Astrophysics and Space Science",
                 year = "2018",
               volume = "363",
             keywords = "Impulsive maneuvers · Near-earth asteroids · Close proximity 
                         operations · Irregular bodies · Astrodynamics.",
             abstract = "The strongly perturbed environment of a small body, such as an 
                         asteroid, can complicate the prediction of orbits used for close 
                         proximity operations. Inaccurate predictions may make the 
                         spacecraft collide with the asteroid or escape to the deep space. 
                         The main forces acting in the dynamics come from the solar 
                         radiation pressure and from the bodys weak gravity field. This 
                         paper investigates the feasibility of using bi-impulsive maneuvers 
                         to avoid the aforementioned non-desired phenomena (collisions and 
                         escapes) by connecting orbits around the triple system asteroid 
                         2001SN263, which is the target of a proposed Brazilian space 
                         mission. In terms of a mathematical formulation, a recently 
                         presented rotating dipole model is considered with oblateness in 
                         both primaries. In addition, a two-point boundary value problem is 
                         solved to find a proper transfer trajectory. The results presented 
                         here give support to identifying the best strategy to find orbits 
                         for close proximity operations, in terms of long orbital lifetimes 
                         and low deltaV consumptions. Numerical results have also 
                         demonstrated the significant influence of the spacecraft orbital 
                         elements (semi-major axis and eccentricity), angular position of 
                         the Sun and spacecraft area-to-mass ratio, in the performance of 
                         the bi-impulsive maneuver.",
                  doi = "10.1007/s10509-017-3234-5",
                  url = "http://dx.doi.org/10.1007/s10509-017-3234-5",
                 issn = "0004-640X",
             language = "en",
           targetfile = "santos_analysis.pdf",
        urlaccessdate = "25 abr. 2024"
}