@Article{SantosRoccCarr:2014:TrCoDu,
               author = "Santos, Willer Gomes dos and Rocco, Evandro Marconi and Carrara, 
                         Valdemir",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)} and {Instituto Nacional de 
                         Pesquisas Espaciais (INPE)}",
                title = "Trajectory control during an aeroassisted maneuver between 
                         coplanar circular orbits",
              journal = "Journal of Aerospace Technology and Management",
                 year = "2014",
               volume = "6",
               number = "2",
                pages = "159--168",
                month = "Apr.-Jun.",
             keywords = "Altitude control, Proportional control systems, Aeroassisted 
                         maneuvers, External disturbances, Orbital dynamics, Proportional 
                         integral derivative controllers, Rate of heat transfer, Reference 
                         trajectories, Sensors and actuators, Trajectory control, Orbits.",
             abstract = "This paper presents the simulation results of an aeroassisted 
                         maneuver around the Earth, between coplanar circular orbits, from 
                         a geostationary orbit to a low orbit. The simulator developed 
                         considers a reference trajectory and a trajectory perturbed by 
                         external disturbances combined with non-idealities of sensors and 
                         actuators. It is able to operate in closed loop, controlling the 
                         trajectory (drag-free control) at each instant of time using a 
                         Proportional-Integral-Derivative (PID) controller and propulsive 
                         jets. We adopted a spacecraft with a cubic body composed of two 
                         rectangular plates arranged perpendicular to the velocity vector 
                         of the vehicle. Propulsive jets are applied at the apogee of the 
                         transfer orbit in order to keep the perigee altitude and control 
                         the rate of heat transfer suffered by the vehicle during 
                         atmospheric passage. A PID controller is used to correct the 
                         deviation in the state vector and in the keplerian elements. The 
                         U.S. Standard Atmosphere is adopted as the atmospheric model. The 
                         results have shown that the aeroassisted transfer presents a 
                         smaller fuel consumption when compared to a Hohmann transfer or a 
                         bi-elliptic transfer.",
                  doi = "10.5018/jatm.v6i2.351",
                  url = "http://dx.doi.org/10.5018/jatm.v6i2.351",
                 issn = "1984-9648",
                label = "scopus 2014-07 GomesdosSantosRoccCarr:2014:TrCoDu",
             language = "en",
           targetfile = "351-1856-1-PB.pdf",
        urlaccessdate = "27 abr. 2024"
}