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Study and Design of an Adaptive Control Law for Spacecraft Attitude Control
2014 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

In this thesis the problem of spacecraft attitude control is investigated. The spacecraft dynamics are modeled as a rigid body system controlled by 4 thrusters, and the kinematics are represented by direction cosine matrix. In this thesis, the effectiveness of retrospective cost adaptive control for spacecraft attitude control is evaluated. The prominent feature of this adaptive controller is that it requires little knowledge of the system to be controlled. This makes this controller attractive since for most spacecraft knowledge of the spacecraft’s inertia tensor is limited and will sometimes change over the spacecraft lifetime.

Place, publisher, year, edition, pages
2014. , p. 60
Keyword [en]
Technology, Adaptive Control, RCAC, Attitude Control, ADCS, AOCS, Spacecraft
Keyword [sv]
Teknik
Identifiers
URN: urn:nbn:se:ltu:diva-50766Local ID: 7fe41f8d-9900-4350-82b9-4ffc006c6064OAI: oai:DiVA.org:ltu-50766DiVA, id: diva2:1024128
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Supervisors
Examiners
Note
Validerat; 20140728 (global_studentproject_submitter)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
Permanent link

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Cite
Citation style
  • apa
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf