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Deployable tensegrity reflectors for small satellites
KTH, Superseded Departments, Structural Engineering.ORCID iD: 0000-0001-6802-8331
2002 (English)In: Journal of Spacecraft and Rockets, ISSN 0022-4650, E-ISSN 1533-6794, Vol. 39, no 5, 701-709 p.Article in journal (Refereed) Published
Abstract [en]

Future small satellite missions require low-cost, precision reflector structures with large aperture that can be packaged in a small envelope. Existing furlable reflectors form a compact package which, although narrow, is too tall for many applications. An alternative approach is proposed, consisting of a deployable tensegrity prism forming a ring structure that deploys two identical cable nets (front and rear nets) interconnected by tension ties; the reflecting mesh is attached to the front net. The geometric configuration of the structure has been optimized to reduce the compression in the struts of the tensegrity prism. A small-scale physical model has been constructed to demonstrate the proposed concept. A preliminary design of a 3-m-diam, 10-GHz reflector with a focal-length-to-diameter ratio of 0.4 that can be packaged within an envelope of 0.1 x 0.2 x 0.8 m(3) is presented.

Place, publisher, year, edition, pages
2002. Vol. 39, no 5, 701-709 p.
Identifiers
URN: urn:nbn:se:kth:diva-21977ISI: 000178679300010OAI: oai:DiVA.org:kth-21977DiVA: diva2:340675
Note
QC 20100525Available from: 2010-08-10 Created: 2010-08-10 Last updated: 2017-12-12Bibliographically approved

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Tibert, Gunnar

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