Coulomb drag propulsion experiments of ESTCube-2 and FORESAIL-1

Iakubivskyi, Iaroslav; Janhunen, P.; Praks, Jaan; Allik, Viljo; Bussov, Kadri; Clayhills, Bruce; Dalbins, Janis; Eenmäe, T.; Ehrpais, Hendrik; Envall, Jouni; Haslam, Sean; Ilbis, Erik; Jovanovic, Nemanja; Kilpua, Emilia; Kivastik, Joosep; Laks, Jürgen; Laufer, Philipp; Merisalu, Maido; Meskanen, Matias; Märk, Robert; Nath, Anjan Jyoti; Niemelä, Petri; Noorma, Mart; Mughal, M. Rizwan; Nyman, Samuli; Pajusalu, Mihkel; Palmroth, Minna; Paul, Aditya Savio; Peltola, Timo; Plans, Mathias; Polkko, J.; Islam, Quazi Saimoon; Reinart, Anu; Riwanto, Bagus; Sammelselg, Väinö; Sate, Janis; Sünter, Indrek; Tajmar, Martin; Tanskanen, Eija; Teras, Hans; Toivanen, Petri; Vainio, Rami; Väänänen, Mika; Slavinskis, Andris

doi:10.1016/j.actaastro.2019.11.030

Cited by 32 publications

(37 citation statements)

References 45 publications

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“…Beside the scientific values for Earth space environment of these measurements, the gained knowledge can help improve reliability and longevity of future satellites. The plasma brake payload will demonstrate an affordable and efficient deorbiting technology, a viable solution for reducing space debris [23]. This experiment will provide valuable insights for improvements of propellantless propulsion systems.…”

Section: The Foresail-1 Missionmentioning

confidence: 99%

“…However, the plasma brake requires to attain a significant angular momentum, as deployment of plasma brake's 300 metres long tether is only possible if sufficient centrifugal force is available throughout the deployment process. For the deployment of first 10 m the initial spin rate of 130 • /s should be provided by the ACS [23], [24].…”

Section: The Foresail-1 Missionmentioning

confidence: 99%

“…Force is provided through the rotational motion of the satellite obtained with the attitude control system. Angular velocity needed to accomplish this goal is calculated to be 130 • /s [23], which would exert the maximal allowed force without damaging the tether. The angular momentum for deployment of the remaining length of the 300 m long tether can then be generated by actuating plasma brake.…”

Section: A the Mission Attitude Requirementsmentioning

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: The Foresail-1 Missionmentioning

confidence: 99%

Section: The Foresail-1 Missionmentioning

confidence: 99%

Section: A the Mission Attitude Requirementsmentioning

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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“…FORESAIL-1 is the first in FORESAIL mission series developed by the Finnish Centre of Excellence for Sustainable Space. In addition to the PATE payload, it carries a plasma brake for lowering of the orbit (Iakubivskyi et al, 2019), which is crucial to achieve the requirements of acquiring particle measurements with a drifting MLT. The initial PATE demonstration will take place in the original orbit for about four months with the satellite's spin plane aligned with the meridional plane to achieve scanning of the different pitch angles by spacecraft spin.…”

Section: Missionmentioning

confidence: 99%

Particle telescope aboard FORESAIL-1: Simulated performance

Oleynik

Vainio

Hedman

et al. 2020

Advances in Space Research

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The Particle Telescope (PATE) of FORESAIL-1 mission is described. FORESAIL-1 is a CubeSat mission to polar Low Earth Orbit. Its scientific objectives are to characterize electron precipitation from the radiation belts and to observe energetic neutral atoms (ENAs) originating from the Sun during the strongest solar flares. For that purpose, the 3-unit CubeSat carries a particle Email addresses: philipp.oleynik@utu.fi (Philipp Oleynik), rami.vainio@utu.fi (Rami Vainio), hannu-pekka.hedman@utu.fi (Hannu-Pekka Hedman), arjupu@utu.fi (Arttu Punkkinen), rpunk@utu.fi (Risto Punkkinen), laolsal@utu.fi (Lassi Salomaa), teansa@utu.fi (Tero Säntti), Jarno.Tuominen@turkuamk.fi (Jarno Tuominen), pakavir@utu.fi (Pasi Virtanen), alexandre.bosser@aalto.fi (Alexandre Bosser), Pekka.Janhunen@fmi.fi (Pekka Janhunen), emilia.kilpua@helsinki.fi (Emilia Kilpua), minna.palmroth@helsinki.fi (Minna Palmroth), jaan.praks@aalto.fi (Jaan Praks), andris.slavinskis@aalto.fi (Andris Slavinskis), srukak@utu.fi (Syed R. U.telescope that measures energetic electrons in the nominal energy range of 80-800 keV in seven energy channels and energetic protons at 0.3-10 MeV in ten channels. In addition, particles penetrating the whole telescope at higher energies will be measured in three channels: one >800 keV electron channel, two integral proton channels at >10 MeV energies. The instrument contains two telescopes at right angles to each other, one measuring along the spin axis of the spacecraft and one perpendicular to it. During a spin period (nominally 15 s), the rotating telescope will, thus, deliver angular distributions of protons and electrons, at 11.25-degree clock-angle resolution, which enables one to accurately determine the pitch-angle distribution and separate the trapped and precipitating particles. During the last part of the mission, the rotation axis will be accurately pointed toward the Sun, enabling the measurement of the energetic hydrogen from that direction. Using the geomagnetic field as a filter and comparing the rates observed by the two telescopes, the instrument can observe the solar ENA flux for events similar to the only one so far observed in December 2006. We present the Geant4-simulated energy and angular response functions of the telescope and assess its sensitivity showing that they are adequate to address the scientific objectives of the mission.

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“…The use of CubeSats is one plausible option to realize innovative technology demonstration of tether systems in space since they are developed and launched at a much lower cost than conventional satellites. The authors of this paper currently develop 3U CubeSat FORESAIL-1 to realize the world's first space demonstration of Coulomb drag propulsion [6], [7]. FORESAIL-1 will demonstrate the plasma brake for deorbiting in the Low Earth Orbit (LEO).…”

Section: Introductionmentioning

confidence: 99%

Verification of Tether Deployment System aboard CubeSat through Dynamics Simulations and Tests

Sakamoto

Mughal

Slavinskis

et al. 2021

2021 IEEE Aerospace Conference (50100)

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This paper proposes a proper model selection strategies for the dynamic simulations of the tether deployment mission aboard a CubeSat. Space tether technology will enable innovative space missions in the near future. The Coulomb Drag Propulsion (CDP), including electric solar wind sailing, is one of the plausible future technologies. The authors currently develop a CubeSat, FORESAIL-1, for space demonstration of CDP. However, the analytical simulations for the verification and validation of the mission design typically require a high computational cost. This is because a minimum model order is not selected properly. In this study, through observing a preliminary analytical model for tether deployment analysis, the simplest model is chosen to avoid the mission failure modes in each deployment phase.

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Coulomb drag propulsion experiments of ESTCube-2 and FORESAIL-1

Cited by 32 publications

References 45 publications

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

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

Particle telescope aboard FORESAIL-1: Simulated performance

Verification of Tether Deployment System aboard CubeSat through Dynamics Simulations and Tests

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