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Design of debris removal missions performed by robotic graspers
Sapienza Università di Roma, Dipartimento di Ingegneria Astronautica Elettrica Ed Energetica (DIAEE).
University of Rome la Sapienza.
University of Rome la Sapienza, Dipartimento di Ingegneria Meccanica e Aeronautica (DIMA), University of Rome la Sapienza.
Dipartimento di Ingegneria Meccanica e Aeronautica (DIMA), University of Rome la Sapienza.
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2012 (English)In: 63rd International Astronautical Congress 2012: Naples, Italy, 1-5 October 2012 : (IAC 2012)., Paris: International Astronautical Federation, 2012, Vol. 8, p. 6356-6366Conference paper, Published paper (Refereed)
Abstract [en]

The well known increase of the orbiting debris, leading to a critical condition in which additional launches could be precluded, calls for mitigation and removal practices. First, and maybe easier to accomplish with respect to other concepts under study, some missions should be probably carried out in a close fiiture to grasp large unused orbiting objects, like upper stages or idle spacecraft that already ended their operational lifetime. The focus on large objects, even if they are a limited subset of orbiting spent bodies, helps in two ways: The reduction of the cross section for possible impacts, and, more remarkably, the reduction of the number and size of additional debris to be generated in a possible collision. As a result, these targets can justify the cost and the complexity of removal missions which, even if almost traditional in the approach and not-too-far from current operational capabilities, still pose significant technical problems. The paper aims to present the operational sequence of a removal mission to be performed by a robotic spacecraft. The issues relevant for the different phases are discussed, with a special focus on the grasping operations, when the robotic arms of the servicing spacecraft, after the determination of the relative kinematic state of the target, should carcfully embraces and precisely catch, in a safe area, the orbiting body. Such an approach should bypass obstacles like solar panels and avoid the break-up of the target, possibly degraded due to its long exposure to space environment. The results of simulations under reasonable, engineering hypothesis for the mission's scenario are presented, with the estimate of torques and forces to be exerted by the robotic arms. The attitude issues for the servicing spacecraft, as well as the vibration behaviour for an accurate end-effector positioning during robotic arms manoeuvres are considered. The confidence in the findings of these numerical studies is strengthened by the know-how gained with the related experimental activities performed during recent years in the labs at Sapienza Universita' di Roma by means of dedicated, small test-beds

Place, publisher, year, edition, pages
Paris: International Astronautical Federation, 2012. Vol. 8, p. 6356-6366
National Category
Other Electrical Engineering, Electronic Engineering, Information Engineering
Research subject
Onboard space systems
Identifiers
URN: urn:nbn:se:ltu:diva-29725Local ID: 34a3fa71-8efd-42c5-9a5a-5a9dbcae0c72ISBN: 978-162276979-7 (print)OAI: oai:DiVA.org:ltu-29725DiVA, id: diva2:1002950
Conference
International Astronautical Congress : 01/10/2012 - 05/10/2012
Note
Upprättat; 2012; 20160512 (andbra)Available from: 2016-09-30 Created: 2016-09-30 Last updated: 2017-11-25Bibliographically approved

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Felicetti, Leonard

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