@TechReport{AntunesRiccRamo:2016:EsSoDi,
               author = "Antunes, Leonardo de Faria and Ricci, M{\'a}rio C{\'e}sar and 
                         Ramos, Marco Antonio Ram{\'{\i}}rez",
                title = "Estudos sobre a din{\^a}mica e controle de espa{\c{c}}onaves 
                         propulsadas por velas solares, aplicado ao problema de desvio de 
                         rota de colis{\~a}o de aster{\'o}ides com a terra",
          institution = "Instituto Nacional de Pesquisas Espaciais",
                 year = "2016",
                 type = "RPQ",
              address = "S{\~a}o Jos{\'e} dos Campos",
                 note = "{Bolsa PIBIC/INPE/CNPq}",
             keywords = "Collision. Asteroid. Comet. Control. Dynamics.",
             abstract = "The ultimate goal of this work - which has a term for completion 
                         in July 2017 - is to apply the classical control theory in the 
                         design of a satellite attitude control system propelled by solar 
                         sails. The aim of this work present the design procedures for a 
                         control system necessary to change the orbits of objects on a 
                         collision course with Earth. The use of solar sails for space 
                         travel is an interesting option because they do not require a 
                         large amount of propellant to move around in space. This happens 
                         because the solar sail does not use the propellant traditional way 
                         power source as its main propellant is sunlight provided from the 
                         sun. This radiation force while being reflected on the surface of 
                         the sail generates a time, making snow accelerate and gain speed 
                         over time. Although this force is smaller compared to a 
                         conventional rocket using chemical propellants to gain 
                         acceleration, this force is constant and is provided by the sun 
                         itself, unlike the rocket that depends entirely on the fuel that 
                         lasts a short time losing speed faster than see her. To accomplish 
                         this mission to divert orbit collision course objects to the 
                         Earth, we use the concept of gravity tractor, which uses the 
                         mutual gravitational force between a spacecraft propelled by solar 
                         sail hovering at a target asteroid as a towline using a 
                         non-Keplerian orbits instead of a static orbit to save fuel. This 
                         will probe go intercept the orbit of the target asteroid and will 
                         {"}anchor{"} in this object. When entering a nearby orbit, the 
                         object that ship will slightly attract the object over time will 
                         have their orbits modified by such action. This ship should be in 
                         inclination of approximately 55° to the object to produce a force 
                         required to tow the asteroid. It is intended for future work to 
                         describe the non-nuclear deflections options using kinetic 
                         impactors, gravity tractos and solar sails of a greater depth, 
                         emphasizing the aspects of dynamic modeling and control.",
          affiliation = "FATESF and {Instituto Nacional de Pesquisas Espaciais (INPE)} and 
                         {Instituto Nacional de Pesquisas Espaciais (INPE)}",
             language = "pt",
                pages = "40",
                  ibi = "8JMKD3MGP3W34R/42PMPNH",
                  url = "http://urlib.net/rep/8JMKD3MGP3W34R/42PMPNH",
           targetfile = "Antunes_Estudos.pdf",
        urlaccessdate = "25 jan. 2021"
}