Deorbiting small satellites from the ISS using a tether system
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ORIGINAL PAPER
Deorbiting small satellites from the ISS using a tether system Alice Brunello1 · Andrea Valmorbida1,2 · Enrico C. Lorenzini1,2 · Stefania Cantoni3 · Mario De Stefano Fumo3 · Alberto Fedele3 · Roberto Gardi3 · Raffaele Votta3 Received: 21 June 2020 / Revised: 12 September 2020 / Accepted: 28 September 2020 © CEAS 2020
Abstract This paper presents results of a study conducted for the project IPERDRONE that aims at the design and development of a small re-entry system, able to perform in-orbit operations near the International Space Station (ISS), to reenter the atmosphere, and to land safely on Earth bringing back scientific payloads/experiments intact from the ISS. The results presented focus on the dynamics of the tethered space drone using the Swing and Release technique in close proximity of the ISS to exchange momentum between the departing IPERDRONE and the ISS, and the active propulsion system needed for the re-entry trajectory. This study could lead to a new technological solution for deorbiting a space vehicle from the ISS that is low cost, safe and free of contamination. Keywords Deorbiting · Tether system · ISS environment · Swing and release · Dynamics and control Abbreviations θ Libration angle α Critical flux V0 Initial launching speed * Andrea Valmorbida [email protected] Alice Brunello [email protected] Enrico C. Lorenzini [email protected] Stefania Cantoni [email protected] Mario De Stefano Fumo [email protected] Alberto Fedele [email protected] Roberto Gardi [email protected] Raffaele Votta [email protected] 1
Center of Studies and Activities for Space (CISAS) “Giuseppe Colombo”, University of Padova, Via Venezia 15, 35131 Padova, Italy
2
Department of Industrial Engineering (DII), University of Padova, Via Venezia 1, 35131 Padova, Italy
3
Italian Aerospace Research Centre (CIRA),, Via Maiorise, 81043 Capua, Italy
ΔV at tether cut when crossing LV ΔVd ASI Italian Space Agency Acs Longitudinal cross section area Aw ‘Wet’ area CF Cost function CoM Center of mass EVA Extra vehicular activity F Impacting flux Fmet Micrometeoroid flux Fod Orbital debris flux IOL Input output linearization ISS International space station JEM Japan experiment module J-SSOD JEM small satellite orbital KOS Keep out sphere LV Local vertical M/ODs Micrometeorites/orbital debris NRKDS Nanoracks Kaber deployment system NRSS Nanoracks separation system Pcad Survival probability SPDM Special purpose dexterous manipulator
1 Introduction The project IPERDRONE, funded by the Italian Space Agency, will consist of a series of missions characterized by incremental objectives, aiming at qualifying this new type
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of missions and related technologies [1, 2]. The program includes, as first steps, the development of inspection services for spacecraft and manned vehicles to reduce the EVA missions of astronauts and the retrieval of payloads through their reentry on ground. In particular, the requirement on the mass of the vehicle, of abo
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