Passive magnetic attitude stabilization of the UNISAT-4 microsatellite

Santoni, Fábio; Zelli, Mauro

doi:10.1016/j.actaastro.2009.03.012

Cited by 38 publications

(34 citation statements)

References 11 publications

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“…Another disadvantage of the B-dot strategy is the lack of control regarding the final attitude of the satellite (once stabilized), which depends on its initial condition. Consequently, the magnetic attitude control systems that are exclusively based on this strategy normally include a permanent magnet, making one of the satellite axes remain permanently aligned with the geomagnetic field [17].…”

mentioning

confidence: 99%

Magnetic Attitude Control for Satellites in Polar or Sun-Synchronous Orbits

Cubas

Farrahi

Pindado

2015

Journal of Guidance, Control, and Dynamics

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In this work, a new law for magnetic control of satellites in near-polar orbits is presented. This law has been developed for the UMPSat-2 microsatellite, which has been designed and manufactured by Universidad Politecnica de Madrid, Madrid. The control law is a modification of the B-dot strategy that enables the satellite to control the rotation rate. Besides, the satellite's equilibrium state is characterized by having the rotation axis perpendicular to the orbit's plane. The control law described in the present work only needs magnetometers and magnetorquers, as sensors and actuators, respectively, to carry out a successful attitude control on the spacecraft A description of the analysis is included. Performance and applicability of the proposed method have been demonstrated by control dynamics together with Monte Carlo techniques and by implementing the control law in the UPMSat-2 mission simulator. Results show good performance in terms of acquisition and stability of the satellite rotation rate and orientation with respect to its orbit's plane.

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mentioning

confidence: 99%

Magnetic Attitude Control for Satellites in Polar or Sun-Synchronous Orbits

Cubas

Farrahi

Pindado

2015

Journal of Guidance, Control, and Dynamics

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“…Attitude control systems (ACSs), e.g., are hindered in their ability to achieve precise pointing or fast slewing maneuvers due to size and power constraints. Many ACS approaches have been examined for picoscale satellites such as spin and passive stabilization, gravity gradient approaches, magnetic torque coils, miniaturized control momentum gyros, and thrusters [2][3][4][5]. The most common methods of those listed for active control are the magnetic torque rods and/or coils [5].…”

Section: Introductionmentioning

confidence: 99%

L<sub>1</sub> adaptive attitude control for a picoscale satellite test bed

Sease

Yang

et al. 2015

IEEE Trans. Aerosp. Electron. Syst.

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Smaller and more agile space assets, such as picoscale satellites, have become one of the promising focuses for space missions because of the benefits in cost reduction, enhanced flexibility, survivability, and reliability. A simple magnetic torque coil-based attitude control system is proposed here for a one unit picoscale satellite test bed using an L 1 adaptive controller. A pointing accuracy of 2 deg is achieved in both a one-axis ground test bed and three-axis control simulation.

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“…The mathematical modeling of such systems is quite a difficult task, since the majority of existent hysteresis models result in differential equations with discontinuous right-hand side. The analysis of dynamics for attitude control systems with magnetic hysteresis dampers and optimization of their parameters have been done in Sarychev et al (1988) and Guerman et al (1989), and the results of these studies have been implemented in real missions (Ovchinnikov et al, 2000;Santoni and Zelli, 2009). However, these studies lacked an accurate theoretical basis for application of doi: 10.5028/jatm.v6i4.…”

Section: Mathematics Of Nanosatellitesmentioning

confidence: 99%