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dc.contributor.authorClark, Christopher P.
dc.contributor.authorTan, Dun Y.
dc.contributor.authorArnal Luna, Patricia
dc.contributor.authorHastings, Daniel E.
dc.contributor.authorMasterson, Rebecca A.
dc.contributor.authorRicard, Michael J.
dc.date.accessioned2021-05-12T16:05:25Z
dc.date.available2021-05-12T16:05:25Z
dc.date.issued2020-11
dc.identifier.isbn9781624106088
dc.identifier.urihttps://hdl.handle.net/1721.1/130575
dc.description.abstractRecent events such as the 2009 Iridium-Cosmos collision and multiple anti-satellite weapon (ASAT) tests have propelled the increasingly urgent topic of space debris management to the forefront of current engineering inquiry. Simultaneously, the so-called “CubeSat Revolution” has significantly reduced barriers to entry for commercial and scientific space missions. Cube-Sats have demonstrated an ever-increasing potential to offer useful capabilities for a fraction of the size, mass, and power of their larger counterparts. This paper explores the relevance and effectiveness of CubeSat architectures in active space debris removal by propulsive methods. The chosen target of interest is the Zenit-2 second-stage rocket body, representative of a particularly large and prevalent family of debris objects. The debris removal mission design problem is approached from a fundamental level. First, the CubeSat architecture design tradespace is defined and outlined, including the proposed design vector, constraints, and objective function. Next, a system model and optimization methods are presented and implemented in MATLAB. Given a set of mission requirements, the algorithm arrives at an optimal or near-optimal architecture design by iterating through combinations of commercially available CubeSat components stored in a database. Results are examined for various deorbiter CubeSat designs, and key tradeoffs between architecture options are identified and explored. Finally, considering the optimized results, a discussion of the most effective propulsive solutions for Zenit-2 rocket body removal using CubeSat clusters is presented.en_US
dc.language.isoen
dc.publisherAmerican Institute of Aeronautics and Astronauticsen_US
dc.relation.isversionofhttp://dx.doi.org/10.2514/6.2020-4241en_US
dc.rightsCreative Commons Attribution-Noncommercial-Share Alikeen_US
dc.rights.urihttp://creativecommons.org/licenses/by-nc-sa/4.0/en_US
dc.sourceProf. Hastings via Barbara Williamsen_US
dc.titleEffectiveness of CubeSat-Based Architectures for Active Removal of On-Orbit Rocket Bodiesen_US
dc.typeArticleen_US
dc.identifier.citationClark, Christopher P. et al. "Effectiveness of CubeSat-Based Architectures for Active Removal of On-Orbit Rocket Bodies." Accelerating Space Commerce, Exploration, and New Discovery Conference, November 2020, virtual event, American Institute of Aeronautics and Astronautics, November 2020. © 2020 The Charles Stark Draper Laboratory, Incen_US
dc.contributor.departmentCharles Stark Draper Laboratoryen_US
dc.contributor.departmentMassachusetts Institute of Technology. Department of Aeronautics and Astronauticsen_US
dc.relation.journalAccelerating Space Commerce, Exploration, and New Discovery Conferenceen_US
dc.eprint.versionAuthor's final manuscripten_US
dc.type.urihttp://purl.org/eprint/type/ConferencePaperen_US
eprint.statushttp://purl.org/eprint/status/NonPeerRevieweden_US
dc.date.updated2021-05-11T18:16:18Z
dspace.orderedauthorsClark, CP; Tan, DY; Luna, PA; Hastings, DE; Masterson, RA; Ricard, MJen_US
dspace.date.submission2021-05-11T18:16:20Z
mit.licenseOPEN_ACCESS_POLICY
mit.metadata.statusComplete


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