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Linear covariance techniques for attitude dynamics determination on a small satellite
2009 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

A spin-stabilized spacecraft is designed to rotate around one of its principal axes. However, geometric factors such as products of inertia, and environmental factors such as external disturbance torques can cause the spacecraft to precess. In this thesis, Linear Covariance Analysis is implemented to quantify how the coelevation angle of a spacecraft relates to normally distributed variations in a set of a geometric and enviromental input parameters. Further, a Matlab software tool for implementing Linear Covariance Analysis on Simulink computer models is presented.

Place, publisher, year, edition, pages
2009.
Keyword [en]
Technology, Linear Covariance Analysis, Spin-Stabilized Satellite
Keyword [sv]
Teknik
Identifiers
URN: urn:nbn:se:ltu:diva-49799ISRN: LTU-PB-EX--09/024--SELocal ID: 71c796b8-8343-4920-9781-7814be041b78OAI: oai:DiVA.org:ltu-49799DiVA: diva2:1023147
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Examiners
Note
Validerat; 20101217 (root)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

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Type fulltextMimetype application/pdf

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CiteExportLink to record
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Citation style
  • apa
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  • nn-NB
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Output format
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