@Article{GonçalvesRoccMoraKuga:2015:KaFiAp,
               author = "Gon{\c{c}}alves, Liana Dias and Rocco, Evandro Marconi and 
                         Moraes, Rodolpho Vilhena de and Kuga, H{\'e}lio Koiti",
          affiliation = "{} and {Instituto Nacional de Pesquisas Espaciais (INPE)} and 
                         {Universidade Federal de S{\~a}o Paulo (UNIFESP)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)}",
                title = "Kalman filter application to mitigate the errors in the trajectory 
                         simulations due to the lunar gravitational model uncertainty",
              journal = "Journal of Physics: Conference Series",
                 year = "2015",
               volume = "641",
                pages = "012029",
             keywords = "Astrodynamics, Kalman Filter, Orbital Motion, Orbit 
                         Perturbation.",
             abstract = "his paper aims to simulate part of the orbital trajectory of Lunar 
                         Prospector mission to analyze the relevance of using a Kalman 
                         filter to estimate the trajectory. For this study it is considered 
                         the disturbance due to the lunar gravitational potential using one 
                         of the most recent models, the LP100K model, which is based on 
                         spherical harmonics, and considers the maximum degree and order up 
                         to the value 100. In order to simplify the expression of the 
                         gravitational potential and, consequently, to reduce the 
                         computational effort required in the simulation, in some cases, 
                         lower values for degree and order are used. Following this aim, it 
                         is made an analysis of the inserted error in the simulations when 
                         using such values of degree and order to propagate the spacecraft 
                         trajectory and control. This analysis was done using the standard 
                         deviation that characterizes the uncertainty for each one of the 
                         values of the degree and order used in LP100K model for the 
                         satellite orbit. With knowledge of the uncertainty of the gravity 
                         model adopted, lunar orbital trajectory simulations may be 
                         accomplished considering these values of uncertainty. Furthermore, 
                         it was also used a Kalman filter, where is considered the sensor's 
                         uncertainty that defines the satellite position at each step of 
                         the simulation and the uncertainty of the model, by means of the 
                         characteristic variance of the truncated gravity model. Thus, this 
                         procedure represents an effort to approximate the results obtained 
                         using lower values for the degree and order of the spherical 
                         harmonics, to the results that would be attained if the maximum 
                         accuracy of the model LP100K were adopted. Also a comparison is 
                         made between the error in the satellite position in the situation 
                         in which the Kalman filter is used and the situation in which the 
                         filter is not used. The data for the comparison were obtained from 
                         the standard deviation in the velocity increment of the space 
                         vehicle.",
                  doi = "10.1088/1742-6596/641/1/012029",
                  url = "http://dx.doi.org/10.1088/1742-6596/641/1/012029",
                 issn = "1742-6588",
                label = "lattes: 0088337156908774 2 
                         Gon{\c{c}}alvesRoccMoraKuga:2015:KaFiAp",
             language = "pt",
           targetfile = "1_goncalves.pdf",
        urlaccessdate = "02 maio 2024"
}