@InProceedings{SumidaCamLuzCruGoé:2015:FlDyPa,
               author = "Sumida, Ivana Yoshie and Campos Velho, Haroldo Fraga de and Luz, 
                         Eduardo F. P. and Cruz, Ronaldo V. and Go{\'e}s, Luiz Carlos S.",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {} and {Instituto 
                         Tecnol{\'o}gico de Aeron{\'a}utica (ITA)} and {Instituto 
                         Tecnol{\'o}gico de Aeron{\'a}utica (ITA)}",
                title = "Flight dynamics parameter estimation of a rotary wing aircraft 
                         using theoutput error minimization with natural and meta heuristic 
                         methods",
                 year = "2015",
         organization = "Pan-American Congress on Computational Mechanics, 1. (PANACM)",
             keywords = "Flight Simulation, Parameter Identification, Multiple Particle 
                         Collision Algorithm (MPCA).",
             abstract = "Flight simulators are employed by civil and military pilots, as 
                         well by engineers, in order to increase the security in training 
                         of crew, and to find out the behavior of the aircraft under 
                         different operational conditions. However, it is necessary to 
                         calibrate the simulator software to have good adherence to real 
                         flight. In this process, parameters of the mathematical model of 
                         the flight simulation need to be identified, such that the 
                         simulation is as close as possible to the real flight dynamic. 
                         With appropriated values of these parameters, the simulator will 
                         be ready for training or assessing the aircraft dynamics. This can 
                         be described as an inverse problem or parameter identification, 
                         formulated as an optimization problem. The simulator is designed 
                         to represent the dynamics of the helicopter AS355-F2, for testing 
                         two types of maneuvers were employed: a sinusoidal input and 
                         3-2-1-1 pulse input. The aerodynamics derivatives estimation 
                         methodology is also known as quad-M scheme, since it involves four 
                         different processes: Measurement, Maneuver, Model, and Methods of 
                         error minimization. The tested helicopter was equipped with the 
                         Aydin Vector Data Acquisition System (AVDAS) PCU-816-I, ATD-800 
                         digital recorder The system measures a total of thirty-five 
                         different parameters. The calibration of a dynamic flight 
                         simulator is achieved by two meta-heuristics: a Genetic Algorithm 
                         and a new approach named Multiple Particle Collision Algorithm 
                         (MPCA). Preliminary results show a good performance of the 
                         employed optimization methods.",
  conference-location = "Buenos Aires, Argentina",
      conference-year = "29-29 Apr.",
             language = "en",
        urlaccessdate = "27 abr. 2024"
}