碩士 / 國立成功大學 / 航空太空工程學系碩博士班 / 100 / The main goal of this thesis develops a deployer which can accommodate the CubeSat. The deployer connects with the rocket, and protects the CubeSat and main satellite. When the rocket arrive the orbit, the deployer can deploy the CubeSat into orbit. This thesis present a process that design and manufacture the deployer. With the commercial software of the finite element method, ANSYS, the launch environment of the PSLV rocket was simulated. In the simulation, the deployer with the CubeSat is simulated in acceleration test, sine vibration, random vibration and shock test. The first three kinds of test can be simulated with the solver in ANSYS. In the shock test, this thesis use the shock response spectrum (SRS) to transform the time domain of shock test, in order to simulate the shock test in the response spectrum, which can increase the simulation efficiency.The second goal researches the vibration isolating effect of deployer. This thesis uses the concept of whole-spacecraft vibration isolation (WSVI), which designs the isolation in the deployer, not in the satellite. This thesis also uses the structure dynamic modification (SDM) to increase the simulation efficiency.
| Identifer | oai:union.ndltd.org:TW/100NCKU5295103 |
| Date | January 2012 |
| Creators | Yuan-ShengHuang, 黃源聖 |
| Contributors | Syh-Tsang Jeng, 鄭泗滄 |
| Source Sets | National Digital Library of Theses and Dissertations in Taiwan |
| Language | zh-TW |
| Detected Language | English |
| Type | 學位論文 ; thesis |
| Format | 51 |
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