Articulated permanent magnets can function as low-power cubesat magnetotorquers
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The retrieved literature demonstrates the general use of permanent magnets for passive attitude control systems and stabilization in CubeSats, but does not specifically settle whether articulated permanent magnets can function as low-power magnetotorquers.
AstroBio CubeSat is a mission funded by the Italian Space Agency aimed at validating novel lab-on-chip technology, that would enable the use of micro- and nanosatellites as autonomous orbiting laboratories for research in astrobiology. This 3U CubeSat is equipped with a passive magnetic attitude control system (PMACS), including permanent magnets and hysteresis strips, which allows for stabilizing the spacecraft with the longitudinal axis in the direction of the geomagnetic field vector. This work presents the process followed for the experimental characterization of the system, performed on the engineering unit of the satellite by using a Helmholtz cage facility and a spherical air-bearing to recreate environmental conditions similar to the ones experienced during the orbital motion. The hysteresis strips are characterized starting from the determination of the hysteresis loop, from which the energy dissipation per cycle and the apparent magnetic permeability are extracted. Tests performed by using the Helmholtz cage and the air-bearing facility allows for further investigating the damping torque produced by the PMACS and validating the abovementioned parameters. Numerical analysis is then used to select the number of permanent magnets which allows for achieving a pointing accuracy within an error of 10∘ within 24 h from the deployment. The analysis of the flight data supports the results obtained from the experimental test campaigns, confirming the effectiveness of the proposed methods and of the PMACS design.
Robotics plays a pivotal role in contemporary space missions, particularly in the development of robotic manipulators for operations in environments that are inaccessible to humans. In accordance with the trend of integrating multiple functionalities into a single system, this study evaluates the feasibility of using a robotic manipulator, termed a C-arm, for passive attitude control of a 1U CubeSat. A simplified multibody model of the CubeSat system was employed to assess the robotic arm’s functionality as a gravity gradient boom and subsequently as a passive magnetic control mechanism by utilising a permanent magnet at its extremity. The effectiveness of the C-arm as a gravitational boom is constrained by size and weight, as evidenced by the simulations; the pitch angle oscillated around ±40°, while roll and yaw angles varied up to 30° and 35°, respectively. Subsequent evaluations sought to enhance pointing accuracy through the utilisation of permanent magnets. However, the absence of dissipative forces resulted in attitude instabilities. In conclusion, the integration of a robotic arm into a 1U CubeSat for passive attitude control shows potential, especially for missions where pointing accuracy can tolerate a certain range, as is typical of CubeSat nanosatellite missions.
This paper delves into the pivotal domain of CubeSat Attitude Determination and Control Systems (ADCS) with a focus on passive control strategies. CubeSats have revolutionized space exploration but face challenges in attaining and maintaining stable orientations. The paper begins by elucidating the significance of ADCS in satellite stability and its evolution from simple systems to sophisticated technology. It outlines a prevalent issue in CubeSat ADCS, prompting the need for enhanced passive control strategies. While discussing common strategies, it acknowledges their inherent limitations. The study involves both theoretical analysis and MATLAB-based simulations to explore design parameters, such as mass and magnetic system applications, particularly permanent magnets and hysteresis dampers. The simulation results became stable in 110 minutes, and this stability was achieved faster than the results from UiTMSAT-1, which required 120 minutes. In this comparison, it's worth noting that the simulation used 6 permanent magnets and 6 hysteresis dampers, while UiTMSAT-1 utilized 16 permanent magnets and 2 hysteresis dampers. The paper concludes with suggestions for future research, including the incorporation of hysteresis dampers and optimizing permanent magnet configurations, thus contributing to more efficient and reliable CubeSat missions. This research advances our understanding of CubeSat ADCS passive systems and their potential for significant improvements in space exploration.
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