author = "Carrara, Valdemir and Januzi, Rafael Barbosa and Makita, Daniel 
                         Hideaki and Santos, Luis Felipe de Paula and Sato, Lidia Shibuya",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and 
                         {Universidade Federal de S{\~a}o Paulo (UNIFESP)} and 
                         {Universidade Federal de S{\~a}o Paulo (UNIFESP)} and {Instituto 
                         Tecnol{\'o}gico de Aeron{\'a}utica (ITA)} and {Instituto 
                         Tecnol{\'o}gico de Aeron{\'a}utica (ITA)}",
                title = "The ITASAT cubesat development and design",
              journal = "Journal of Aerospace Technology and Management",
                 year = "2017",
               volume = "9",
               number = "2",
                pages = "138--147",
             keywords = "Attitude determination, CubeSat, Kalman filter, Satellite attitude 
             abstract = "Because they are inexpensive platforms for satellites, CubeSats 
                         have become a low-cost way for universities and even developing 
                         countries to have access to space technology. This paper presents 
                         the ITASAT design, particularly the Attitude Determination and 
                         Control Subsystem, the Onboard Software, and the Assembly, 
                         Integration and Testing program. The ITASAT is a 6U CubeSat 
                         nano-satellite in development at the Instituto Tecnol{\'o}gico de 
                         Aeron{\'a}utica, in S{\~a}o Jos{\'e} dos Campos, Brazil. The 
                         platform and its subsystems will be provided by industry while the 
                         payloads are being designed and developed by the principal 
                         investigators. The ITASAT Attitude Determination and Control 
                         Subsystem will rely on a 3-axis magnetometer, 6 analog cosine sun 
                         sensors, 3-axis MEMS gyroscopes, 3 magnetic torque coils, and 3 
                         reaction wheels. The Attitude Determination and Control Subsystem 
                         operating modes, control laws, and embedded software are under the 
                         responsibility of the Instituto Tecnol{\'o}gico de 
                         Aeron{\'a}utica. A Kalman filter shall be employed to estimate 
                         the quaternion attitude and gyroscope biases from sensor 
                         measurements. The Attitude Determination and Control Subsystem 
                         operating modes are the nominal mode, with geocentric pointing 
                         attitude control and the stabilization mode, in which only the 
                         satellite angular velocity is controlled. The nominal mode will be 
                         split into 2 sub-modes: reaction wheel control plus magnetic wheel 
                         de-saturation and 3-axis magnetic attitude control. Simulation 
                         results have shown that the attitude can be controlled with 
                         1-degree accuracy in nominal mode with the reaction wheels, but 
                         these errors grow as much as 20 degrees or higher with the 3-axis 
                         magnetic control.",
                  doi = "10.5028/jatm.v9i2.614",
                  url = "http://dx.doi.org/10.5028/jatm.v9i2.614",
                 issn = "1984-9648",
             language = "en",
           targetfile = "carrara_itasat.pdf",
        urlaccessdate = "23 abr. 2021"