@Article{CarraraJanMakSanSat:2017:ITCuDe,
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
control.",
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 = "29 mar. 2024"
}