@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 = "27 abr. 2024"
}