ESTCube-1 in-orbit experience and lessons learned

Slavinskis, Andris; Pajusalu, Mihkel; Kuuste, Henri; Ilbis, Erik; Eenmäe, T.; Sünter, Indrek; Laizans, Kaspars; Ehrpais, Hendrik; Liias, Paul; Kulu, Erik; Viru, Jaan; Kalde, Jaanus; Kvell, Urmas; Kütt, Johan; Zalite, Karlis; Kahn, Karoli; Lätt, S.; Envall, Jouni; Toivanen, Petri; Polkko, J.; Janhunen, P.; Rosta, Roland; Kalvas, Taneli; Vendt, Riho; Allik, Viljo; Noorma, Mart

doi:10.1109/maes.2015.150034

Cited by 44 publications

(11 citation statements)

References 19 publications

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Section: Introductionmentioning

confidence: 99%

“…The latter is a deorbiting system, consisting of a single charged tether that interacts with ions in the ionosphere to generate a drag. The first test was tried by the Estonian satellite EstCube [7], but a failure to the tether unreel mechanism occurred [8]. Currently, the Finnish Aalto-1 [9] satellite is equipped with a plasma brake tether that should enable an end-of-life deorbiting [10].The major advantage of an E-sail-based spacecraft over more conventional systems is in its capability of providing thrust without consuming any propellant mass [11], [12],[13], [14], in a similar way to a solar sail [15].…”

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Artificial Collinear Lagrangian Point Maintenance With Electric Solar Wind Sail

Niccolai

Caruso

Quarta

et al. 2020

IEEE Trans. Aerosp. Electron. Syst.

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This paper discusses the maintenance of an L1type artificial equilibrium point in the Sun-[Earth+Moon] circular restricted three-body problem by means of an Electric Solar Wind Sail. The reference configuration instability is compensated for with a feedback control law that adjusts the grid voltage as a function of the distance from the natural L1 point. Two different control strategies are analyzed assuming the solar wind fluctuations to be modelled through a statistical approach.Index Terms-Electric Solar Wind Sail, artificial Lagrangian equilibrium point, solar wind fluctuations, circular restricted three-body problem I. IntroductionA N Electric Solar Wind Sail (E-sail) is an innovative propulsion system, invented in 2004 by Pekka Janhunen [1], which generates a propulsive acceleration by exploiting the solar wind dynamic pressure through the electrostatic interaction between a grid of charged tethers and the solar wind ions. After an on-ground experimental campaign [2], [3], the first in-flight testing of E-sail technology is being attempted in a geocentric environment by flying a variant of the E-sail working principle, the plasma brake [4], [5], [6]. The latter is a deorbiting system, consisting of a single charged tether that interacts with ions in the ionosphere to generate a drag. The first test was tried by the Estonian satellite EstCube [7], but a failure to the tether unreel mechanism occurred [8]. Currently, the Finnish Aalto-1 [9] satellite is equipped with a plasma brake tether that should enable an end-of-life deorbiting [10].The major advantage of an E-sail-based spacecraft over more conventional systems is in its capability of providing thrust without consuming any propellant mass [11], [12],[13], [14], in a similar way to a solar sail [15]. The latter however uses the interaction of the solar radiation pressure with a large and highly reflective surface. The peculiarity of propellantless propulsive systems allows exotic mission scenarios to be envisaged, such as the creation and maintenance of an artificial equilibrium point (AEP) in which the relative position of the spacecraft is constant with respect to the Sun and the [Earth+Moon]. Indeed, because an

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Section: Introductionmentioning

confidence: 99%

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confidence: 99%

Artificial Collinear Lagrangian Point Maintenance With Electric Solar Wind Sail

Niccolai

Caruso

Quarta

et al. 2020

IEEE Trans. Aerosp. Electron. Syst.

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“…ESTCube-1 was in many respects an unusual science project. The building of a satellite was initiated as part of the space technologies course in the University of Tartu without any prior in-house expertise (Slavinskis, Pajusalu, et al, 2015). The aim of the satellite project was as much educational as scientific (Slavinskis, Reinkubjas, et al, 2015): Problem-based learning allows a more practical and engaging learning process than classical lectures or seminars.…”

Section: Introductionmentioning

confidence: 99%

Mediatization of a Research Group: The Estonian Student Satellite ESTCube-1

Olesk

2019

Science Communication

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Increased interactions between researchers and the media can change the individual and collective practices in science due to the considerations about media logic. This article uses the example of the team behind the Estonian satellite ESTCube-1 to describe the process of mediatization and its impacts on the research project. The quick and extensive adaption to media logic by the team can be attributed to the interplay of three elements: the role of the group leader, participation in media trainings, and regular interactions with the media. This article provides a model of how micro-level mediatization is likely to take place in science.

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“…The ESTCube-1 Attitude Determination and Control System (ADCS) was able to perform the required satellite spin up for the tether deployment experiment. However, the tether was not deployed due to payload malfunction [3]. ESTCube-1 used three magnetorquers as actuators which produced the magnetic moment of up to 0.1 A•m 2 ; therefore, relying only on magnetic attitude control.…”

Section: Introductionmentioning

confidence: 99%

Stabilised LQR Control and Optimised Spin Rate Control for Nanosatellites

Ofodile

Ehrpais

Slavinskis

et al. 2019

2019 9th International Conference on Recent Advances in Space Technologies (RAST)

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This paper presents the design and study of cross product control, Linear-Quadratic Regulator (LQR) optimal control and high spin rate control algorithms for ESTCube-2/3 missions. The three-unit CubeSat is required to spin up in order to centrifugally deploy a 300-m long tether for a plasma brake deorbiting experiment. The algorithm is designed to spin up the satellite to one rotation per second which is achieved in 40 orbits. The LQR optimal controller is designed based on closed-loop step response with controllability and stability analysis to meet the pointing requirements of less than 0.1 • for the Earth observation camera and the high-speed communication system. The LQR is based on linearised satellite dynamics with an actuator model. The preliminary simulation results show that the controllers fulfil the requirements set by payloads. While ESTCube-1 used only electromagnetic coils for high spin rate control, ESTCube-2 will make the use of electromagnetic coils, reaction wheels and cold gas thrusters to demonstrate technologies for a deep-space mission ESTCube-3. The attitude control algorithms will be demonstrated in low Earth orbit on ESTCube-2 as a stepping stone for ESTCube-3 which is planned to be launched to lunar orbit where magnetic control is not available.

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ESTCube-1 in-orbit experience and lessons learned

Cited by 44 publications

References 19 publications

Artificial Collinear Lagrangian Point Maintenance With Electric Solar Wind Sail

Artificial Collinear Lagrangian Point Maintenance With Electric Solar Wind Sail

Mediatization of a Research Group: The Estonian Student Satellite ESTCube-1

Stabilised LQR Control and Optimised Spin Rate Control for Nanosatellites

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