This study mainly covers the finite element analysis of a micro satellite structure by considering the vibration effects at the time interval from the launching to the Earth&rsquo / s orbit landing.
Micro-satellites have a great importance in the satellite industry and several developing countries deal with micro-satellite design and production. Turkey is one of these countries by conducting new satellite projects. RASAT project is one the continuing micro-satellite project, which has being developed by TÜ / BiTAK Space Technologies Research Institute. In this thesis, the RASAT satellite is taken as the model for the study. On this model, many mechanical design studies which are performed according to the specified requirements and constraints are verified by finite element analyses. These analyses cover all the essential vibration loads during launching. In the study, firstly, a finite element model of RASAT is prepared. Then, the essential analyses are performed according to the specifications required by the launchers. In the analyses, commercially available finite element software is used.
Finally all the results obtained from the finite element analyses are compared with the predefined requirements and constraints. The results show that the structural design verification regarding the reliability of the structure for the desired mission has been successfully completed.
| Identifer | oai:union.ndltd.org:METU/oai:etd.lib.metu.edu.tr:http://etd.lib.metu.edu.tr/upload/3/12609502/index.pdf |
| Date | 01 May 2008 |
| Creators | Ontac, Suat |
| Contributors | Dag, Serkan |
| Publisher | METU |
| Source Sets | Middle East Technical Univ. |
| Language | English |
| Detected Language | English |
| Type | M.S. Thesis |
| Format | text/pdf |
| Rights | To liberate the content for public access |
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