Abstract The increasing number of man-made objects in near-earth space is becoming a serious problem for future space missions around the Earth. Among the proposed strategies to face this issue, and due to the passive and propellant-less character, electrodynamic tethers appear to be a promising option for spacecraft in low Earth orbits thanks to the limited storage mass and the minimum interface requirements to the host spacecraft. This work presents the roadmap that the Electrodynamic Tether Technology for Passive Consumable-less Deorbit Kit (E.T.PACK) is following to develop a prototype of a deorbit device based on electrodynamic tether technology with Technology Readiness Level 4 by the end of 2022. The paper illustrates the roadmap of the activities carried out at the University of Padova, where software and hardware have been prepared to validate some of the critical elements of the deorbit device. Specifically, the software tools include: (a) the software called “DEPLOY” that allows the computation of a reference trajectory for the deployment of the tether and the completion of sensitivity analysis of the deployment trajectory to key error sources; (b) the software called “FLEXSIM” that predicts the performances of electrodynamic tethers as a function of the system configuration employed; and (c) the software called “FLEX” that includes the dynamical effects of tether flexibility and provides important information on the dynamic stability of the system during deployment and deorbiting phase. The paper describes in detail the three software tools and provides results of a simulation showing how it is possible to deorbit a 24-kg satellite from an initial orbital altitude of 600 km in less than 100 days using a 500-m long tape-like bare tether. The team has also developed laboratory mock-ups and performed experimental activities to: (a) determine the tether mechanical properties; (b) test the functionality of mechanisms used to deploy the tether; (c) test the functionality of the attitude control assembly used during the deployment phase; and (d) validate a passive damper designed for dissipating the longitudinal oscillations of the tether and thus guarantee the stability of the system during both deployment and deorbiting phase. The paper provides a description of both the laboratory setup and the experimental activities performed to validate EDT technologies, including the damping capability of a compact passive-damping mechanism, showing how it can reduce consistently the peak forces up to about 80%.

    Highlights Optimization of full-length deployment trajectory. High fidelity simulations of deorbiting with electrodynamic tethers. Experimental validation of technologies for tape electrodynamic tethers. Close-proximity deployment testing with frictionless table and trajectory control. Development and testing of passive in-line damper.


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    Titel :

    Validation of enabling technologies for deorbiting devices based on electrodynamic tethers


    Beteiligte:
    Valmorbida, A. (Autor:in) / Olivieri, L. (Autor:in) / Brunello, A. (Autor:in) / Sarego, G. (Autor:in) / Sánchez-Arriaga, G. (Autor:in) / Lorenzini, E.C. (Autor:in)

    Erschienen in:

    Acta Astronautica ; 198 ; 707-719


    Erscheinungsdatum :

    2022-06-10


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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    Analysis of electrodynamic tethers as deorbiting systems

    Ahedo, E. / Sanmartin, J. | AIAA | 2000


    Deorbiting of LEO Satellites with Electrodynamic Tethers

    Vannaroni, G. / Dobrowolny, M. / De Venuto, F. et al. | British Library Conference Proceedings | 2000


    Deorbiting of LEO satellites with electrodynamic tethers

    Vannaroni, G. / Dobrowolny, M. / De Venuto, F. | AIAA | 2000


    Electrodynamic Tethers for Deorbiting Applications (IAA 99-6.6.08)

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