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@InProceedings{BatistaMartMatt:2018:UsFaEm,
               author = "Batista, Carlos Leandro Gomes and Martins, Eliane and 
                         Mattiello-Francisco, Maria de F{\'a}tima",
          affiliation = "{Instituto Nacional de Pesquisas Espaciais (INPE)} and 
                         {Universidade Estadual de Campinas (UNICAMP)} and {Instituto 
                         Nacional de Pesquisas Espaciais (INPE)}",
                title = "On the use of a failure emulator mechanism at nanosatellite 
                         subsystem integration tests",
            booktitle = "Proceedings...",
                 year = "2018",
         organization = "IEEE Latin-American Test Symposium, 19. (LATS)",
             keywords = "injetor de falhas, nanosatelites, robustez, canal de 
                         comunica{\c{c}}{\~a}o.",
             abstract = "The increase number of CubeSat based space missions in the last 
                         decade shows the new possibilities for cheaper, faster but not so 
                         better projects. This lack of quality in a mission completeness 
                         point of view is associated to lack of good practices at 
                         developing, assembly and testing phases. Addressing such problem, 
                         this work presents a fault injection tool for nanosatellite 
                         robustness testing, named Failure Emulator Mechanism (FEM). The 
                         goal of the FEM is to emulate at the subsystems interface level 
                         faults that could be presented during the mission operation of the 
                         spacecraft. Working at the communication bus, the FEM is capable 
                         to intercept the exchanged messages between two subsystems under 
                         test and inject different faults: (i) time related faults, i.e. 
                         delay; (ii) value related faults, i.e. bitflip and; (iii) specific 
                         communication bus faults, i.e. a verbose subsystem. The FEM was 
                         developed to support the integration tests of the 
                         software-intensive NanoSatC-BR2 On Board Data Handling Software 
                         (OBSw) and its Payloads. The NanoSatC-BR2 is the second scientific 
                         nanosatellite developed jointly by the Brazilian National 
                         Institute for Space Researches (INPE) and Santa Maria Federal 
                         University (UFSM). As this spacecraft works with a full shared I2C 
                         communication bus, the FEM was implemented to support and work at 
                         this communication protocol and electric interface. The use of FEM 
                         has proved to be helpful along all phases of nanosatellite 
                         development. In the early phase, FEM supports robustness 
                         requirement validation by means models in the loop (MIL). In the 
                         nanosatellite integration phase, FEM supports robustness testing 
                         of the communicating subsystems under integration, configuring 
                         hardware in the loop (HIL). In this paper, we present the design, 
                         implementation and results of FEM as MIL tool for robustness 
                         requirement validation of OBSw and Langmuir Probe, a particular 
                         NanoSatC-BR2 Payload.",
  conference-location = "S{\~a}o Paulo, SP",
      conference-year = "12-14 mar.",
                label = "lattes: 8666823357523918 3 BatistaMartMatt:2018:UsFaEm",
             language = "en",
           targetfile = "batista_on.pdf",
                  url = "http://ieee-ceda.org/event/19th-ieee-latin-american-test-symposium-2018",
        urlaccessdate = "28 nov. 2020"
}


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