Nanosatellite spin-up using magnetic actuators: ESTCube-1 flight results

Ehrpais, Hendrik; Kütt, Johan; Sünter, Indrek; Kulu, Erik; Slavinskis, Andris; Noorma, Mart

doi:10.1016/j.actaastro.2016.07.032

Cited by 22 publications

(12 citation statements)

References 15 publications

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“…Additionally, energy management concerns can as well impede the attaining of the attitude goal. Thus, the attitude maneuvers can last for over a week time, as is evident from the ESTCube-1 experience [7]. With small improvements in the torque production and energy use efficiency, the maneuver operation times can be substantially reduced.…”

Section: B Magnetorquer Drivermentioning

confidence: 99%

“…Acquiring necessary angular velocity of this magnitude and operating under such circumstances demands reliability, reactiveness and efficiency. There are several nanosatellite missions that were designed with spinstabilized attitude modes, which include CINEMA [4], RACE [5], DICE [6], ESTCube-1 [7] and ELFIN [8]. CINEMA and RACE are both 3U CubeSats with spin rates of 24 • /s and 30 • /s, respectively.…”

Section: Introductionmentioning

confidence: 99%

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Design of Magnetorquer-Based Attitude Control Subsystem for FORESAIL-1 Satellite

Jovanovic

Riwanto

Niemelä

et al. 2021

IEEE J. Miniat. Air Space Syst.

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Magnetorquer based attitude control system capable of attaining high spin rates and precise pointing control is required for a 3U CubeSat satellite FORESAIL-1. The satellite, developed by Finnish Centre of Excellence, needs to maintain a spin rate of 24 • /s and precise pointing of the spin axis toward the Sun for the particle telescope instrument, as well as to reach 130 • /s spin rate for the deployment of the plasma brake. Mission requirements analysis and attitude system requirements derivation are presented, followed by actuator trade-off and selection, with detailed design of the complete attitude control system, including air-cored type of magnetorquer actuators and their drivers, made of H-bridge and filtering components. The design is based on several theoretical and practical considerations with emphasis on high power efficiency, such as effects of parallel and serial magnetorquer connections, modelling the magnetorquers with equivalent circuit models for finding of suitable driving frequency and extrapolation methods for efficient dipole moment usage. In-house manufacturing process of magnetorquers, using a custom 3D-printer setup, is described. Lastly, the testing and verification are performed, by measuring the performance of the manufactured hardware, circuit simulations and attitude control simulations. It is shown that the manufactured attitude control system fulfils all system requirements. Simulations also confirm the capability to satisfy mission requirements.

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Section: B Magnetorquer Drivermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Design of Magnetorquer-Based Attitude Control Subsystem for FORESAIL-1 Satellite

Jovanovic

Riwanto

Niemelä

et al. 2021

IEEE J. Miniat. Air Space Syst.

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“…Besides the protective shield of the "space box" container, and its contained artefacts (payloads), a CubeSat needs to perform other functions to be operative. These operative functions (e.g., navigation, communication) are organized in different subsystems (e.g., attitude determination and control system, communications system) based on specific hardware (e.g., gyroscopic sensors, microstrip antenna; Ehrpais et al, 2016;Slavinskis et al, 2016).…”

Section: Cubesatsmentioning

confidence: 99%

Can Communities Produce Complex Technology? Looking Into Space for Insight

Lemos

Giotitsas

2021

Bulletin of Science, Technology & Society

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This article examines a community producing complex space technology. We attempt to highlight which aspects of the community’s activities can help democratize high-tech development while providing a context for similar cases involved in developing and manufacturing nonhigh-technological artefacts. We discuss how this has been made possible by using a technology-determined organizational approach based on the CubeSat open platform infrastructure, blending formal and hands-on education, open communication, specific recruitment and working practices, and a genuine passion for technology. We identify as critical enablers for community-based collaborative development of space technology the open-source architecture standard called CubeSat Design Specifications, the modularization of work in subsystems and between different organizations, and the open and participatory approach work tasks distribution and decision making. Moreover, we argue that the digital/informational aspect of this technology allows the community to implement organizational practices that resemble how open-source movements over the internet produce complex digital artefacts like Wikipedia or Linux. ESTCube can shed light on community-driven complex technology development, providing lessons on what a democratized version of high technology would resemble and how open and digitalized technology can help develop the capacities of a community.

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“…In orbital transfer, in order to save on the cost, power, weight and complexity of the system, a magnetorquer is normally adopted to provide the control torque. Several control methods have been developed for the attitude acquisition, manoeuvre and stabilisation of magnetic actuated satellites during the last decades (1)(2)(3)(4)(5) . The well-known B-dot control law was proposed early in 1972 (6) .…”

Section: Introductionmentioning

confidence: 99%

Magnetic attitude tracking control of gravity gradient microsatellite in orbital transfer

2019

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The problem of the magnetic attitude tracking control is studied for a gravity gradient microsatellite in orbital transfer. The contributions of the work are mainly shown in two aspects: (1) the design of an expected attitude trajectory; (2) a method of the magnetic attitude tracking control. In orbital transfer, the gravity gradient microsatellite under a constant thrust shows complicated dynamic behaviours. In order to damp out the pendular motion, the gravity gradient microsatellite is subject to the the attitude tracking problem. An expected attitude trajectory is designed based on dynamic characteristics revealed in the paper, which not only ensures the flight safety of the system, but also reduces the energy consumption of the controller. Besides, the control torque produced by a magnetorquer is constrained to lie in a two-dimensional plane orthogonal to the magnetic field, so an auxiliary compensator is proposed to improve the control performance, which is different from existing magnetic control methods. In addition, a sliding mode control based on the compensator is presented, and the Lyapunov stability analysis is performed to show the global convergence of the tracking error. Finally, a numerical case of the gravity gradient microsatellite is studied to demonstrate the effectiveness of the proposed tracking control.

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Nanosatellite spin-up using magnetic actuators: ESTCube-1 flight results

Cited by 22 publications

References 15 publications

Design of Magnetorquer-Based Attitude Control Subsystem for FORESAIL-1 Satellite

Design of Magnetorquer-Based Attitude Control Subsystem for FORESAIL-1 Satellite

Can Communities Produce Complex Technology? Looking Into Space for Insight

Magnetic attitude tracking control of gravity gradient microsatellite in orbital transfer

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