Orbit deployment and drag control strategy for formation flight while minimizing collision probability and drift

dc.contributor.authorYoon, Zizung
dc.contributor.authorLim, Yeerang
dc.contributor.authorGrau, Sebastian
dc.contributor.authorFrese, Walter
dc.contributor.authorGarcia, Manuel A.
dc.date.accessioned2021-03-05T08:53:40Z
dc.date.available2021-03-05T08:53:40Z
dc.date.issued2020-03-19
dc.description.abstractThe compact form factor of nanosatellites or even smaller satellites makes them predestined for distributed systems such as formations, constellations or large swarms. However, when it comes to orbit insertion of multiple satellites, these ride share payloads have constrains in the deployment parameters such as sequence, direction, velocity and time interval. Especially for formation flight missions without propulsion, where the satellites should minimize their relative distance drift either passively or by atmospheric drag control, the initial ejection parameters must find a proper trade-off between collision probability and relative drift. Hence, this article covers short-term (first orbit) collision analysis, long-term (30 days) drift analysis and atmospheric drag control strategy for long-term distance control of multiple satellites. The collision analysis considers various orbit deployment parameters such as insertion direction and tolerance, orbital elements of insertion and time span. To cover the parameter space, a Monte Carlo simulation was conducted to identify the impact of these parameters. It showed that for collision probability the major factor is the time span between two ejections and the precision of the deployment vector. For long-term drift analysis, orbit perturbation such as atmosphere and J 2 terms are considered. The result showed that for drift minimizing, minimizing the along-track variation is more substantial than reducing the time span between ejections. Additionally, a drag control strategy to reduce the relative drift of the satellites is described. The results have been applied on the S-NET mission, which consists of four nanosatellites with the task to keep their relative distance within 400 km to perform intersatellite communication experiments. The flight results for orbital drift show equal or better performance (0.1–0.7 km/day) compared to the worst-case simulation scenario, implying that orbit perturbation was chosen correctly and all orbit injection tolerances were within specified range. The drag control maneuver showed good matching to the flight results as well with a deviation for the maneuver time of approximately 10%.en
dc.description.sponsorshipTU Berlin, Open-Access-Mittel – 2020en
dc.identifier.eissn1868-2510
dc.identifier.issn1868-2502
dc.identifier.urihttps://depositonce.tu-berlin.de/handle/11303/12731
dc.identifier.urihttp://dx.doi.org/10.14279/depositonce-11531
dc.language.isoen
dc.rights.urihttps://creativecommons.org/licenses/by/4.0/
dc.subject.ddc620 Ingenieurwissenschaften und zugeordnete Tätigkeitenen
dc.subject.othercollision risken
dc.subject.otherdrag controlen
dc.subject.otherformation flighten
dc.subject.otherorbit deploymenten
dc.subject.otherorbit driften
dc.subject.otherswarmen
dc.titleOrbit deployment and drag control strategy for formation flight while minimizing collision probability and driften
dc.typeArticleen
dc.type.versionpublishedVersionen
dcterms.bibliographicCitation.doi10.1007/s12567-020-00308-6en
dcterms.bibliographicCitation.issue3en
dcterms.bibliographicCitation.journaltitleCEAS Space Journalen
dcterms.bibliographicCitation.originalpublishernameSpringerNatureen
dcterms.bibliographicCitation.originalpublisherplaceLondon [u.a.]en
dcterms.bibliographicCitation.pageend410en
dcterms.bibliographicCitation.pagestart397en
dcterms.bibliographicCitation.volume12en
tub.accessrights.dnbfreeen
tub.affiliationFak. 5 Verkehrs- und Maschinensysteme>Inst. Luft- und Raumfahrt>FG Raumfahrttechnikde
tub.affiliation.facultyFak. 5 Verkehrs- und Maschinensystemede
tub.affiliation.groupFG Raumfahrttechnikde
tub.affiliation.instituteInst. Luft- und Raumfahrtde
tub.publisher.universityorinstitutionTechnische Universität Berlinen
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