The ITASAT CubeSat Development and Design

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, an...

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Bibliographic Details
Published in:	Journal of aerospace technology and management Vol. 9; no. 2; pp. 147 - 156
Main Authors:	Carrara, Valdemir, Januzi, Rafael Barbosa, Makita, Daniel Hideaki, Santos, Luis Felipe de Paula, Sato, Lidia Shibuya
Format:	Journal Article
Language:	English
Published:	Departamento de Ciência e Tecnologia Aeroespacial 01-04-2017 Instituto de Aeronáutica e Espaço (IAE)
Subjects:	Attitude determination CubeSat ENGINEERING, AEROSPACE Kalman filter Satellite attitude control Attitude determination CubeSat Satellite attitude control Kalman filter
Online Access:	Get full text
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Summary:	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 Tecnológico de Aeronáutica, in São José 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 Tecnológico de Aeronáutica. 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 desaturation 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.
ISSN:	2175-9146 2175-9146
DOI:	10.5028/jatm.v9i2.614