Please use this identifier to cite or link to this item: http://dx.doi.org/10.14279/depositonce-15730
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dc.contributor.authorKöthe, Alexander-
dc.contributor.authorLuckner, Robert-
dc.date.accessioned2022-05-17T15:11:36Z-
dc.date.available2022-05-17T15:11:36Z-
dc.date.issued2021-12-21-
dc.identifier.issn1869-5582-
dc.identifier.urihttps://depositonce.tu-berlin.de/handle/11303/16951-
dc.identifier.urihttp://dx.doi.org/10.14279/depositonce-15730-
dc.description.abstractUnmanned aircraft used as high-altitude platform system has been studied in research and industry as alternative technologies to satellites. Regarding actual operation and flight performance of such systems, multibody aircraft seems to be a promising aircraft configuration. In terms of flight dynamics, this aircraft strongly differs from classical rigid-body and flexible aircraft, because a strong interference between flight mechanic and formation modes occurs. For unmanned operation in the stratosphere, flight control laws are required. While control theory generally provides a number of approaches, the specific flight physics characteristics can be only partially considered. This paper addresses a flight control law approach based on a physically exact target model of the multibody aircraft dynamics rather than conventionally considering the system dynamics only. In the target model, hypothetical spring and damping elements at the joints are included into the equations of motion to transfer the configuration of a highly flexible multibody aircraft into one similar to a classical rigid-body aircraft. The differences between both types of aircraft are reflected in the eigenvalues and eigenvectors. Using the eigenstructure assignment, the desired damping and stiffness are established by the inner-loop flight control law. In contrast to other methods, this procedure allows a straightforward control law design for a multibody aircraft based on a physical reference model.en
dc.description.sponsorshipTU Berlin, Open-Access-Mittel – 2021en
dc.language.isoenen
dc.rights.urihttps://creativecommons.org/licenses/by/4.0/en
dc.subject.ddc620 Ingenieurwissenschaften und zugeordnete Tätigkeitende
dc.subject.otherflight control theoryen
dc.subject.othercontrol allocationen
dc.subject.othermultibody aircraften
dc.subject.otherhighly flexible aircraft structuresen
dc.titleApplying eigenstructure assignment to inner-loop flight control laws for a multibody aircraften
dc.typeArticleen
tub.accessrights.dnbfreeen
tub.publisher.universityorinstitutionTechnische Universität Berlinen
dc.identifier.eissn1869-5590-
dc.type.versionpublishedVersionen
dcterms.bibliographicCitation.doi10.1007/s13272-021-00549-zen
dcterms.bibliographicCitation.journaltitleCEAS Aeronautical Journalen
dcterms.bibliographicCitation.originalpublisherplaceHeidelbergen
dcterms.bibliographicCitation.volume13en
dcterms.bibliographicCitation.pageend43en
dcterms.bibliographicCitation.pagestart33en
dcterms.bibliographicCitation.originalpublishernameSpringer Natureen
tub.affiliationFak. 5 Verkehrs- und Maschinensysteme » Inst. Luft- und Raumfahrt » FG Flugmechanik, Flugregelung und Aeroelastizitätde
Appears in Collections:Technische Universität Berlin » Publications

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