Galaczi, D.S. (2026) Designing a deployment mechanism for a space debris de-orbiting satellite. Master's Thesis / Essay, Mechanical Engineering.
|
Text
mME2026GalacziD.pdf Download (23MB) | Preview |
Abstract
This thesis presents a dynamic vibrational analysis of a satellite de-orbiting system designed to clear space debris using a drag-chute deployed using inflatable structures. While a previous prototype functioned in static conditions, its survivability during a launch environment remained unverified. Using SpaceX Falcon 9 qualification levels, the system response was evaluated for the modal, quasi-static, harmonic, shock, and random vibration loads. Identifying critical failure points led to structural refinements, including the redistribution of mass and the stiffening of the support frame’s sidewalls and base plate, including the addition of internal stiffening ribs. The final design successfully meets all SpaceX qualification standards. Additionally, this research explores the orbital tumbling induced by the deployment of the inflatable mechanism. This was undertaken as a tumbling rate equal to the orbital period would negate the dragbased de-orbiting system and understanding the tumbling dynamics is crucial to eliminate this potential. By mapping the energy flow from deployment to satellite rotation, an analytical approach was developed with a MATLAB-based tool to predict 1D tumbling rates, providing a foundational framework for future de-orbiter induced tumbling analysis.
| Item Type: | Thesis (Master's Thesis / Essay) |
|---|---|
| Supervisor name: | GhandchiTehrani, M. and Szirbik, N.B. |
| Degree programme: | Mechanical Engineering |
| Thesis type: | Master's Thesis / Essay |
| Language: | English |
| Date Deposited: | 26 May 2026 13:37 |
| Last Modified: | 26 May 2026 13:37 |
| URI: | https://fse.studenttheses.ub.rug.nl/id/eprint/37311 |
Actions (login required)
 |
View Item |