| 研究生: |
梅培安 Cifuentes, Angel Bernal Menendez |
|---|---|
| 論文名稱: |
微衛星重返地球任務之熱分析 Thermal Analysis for a Re-entry CubeSat Mission |
| 指導教授: |
苗君易
Miau, Jiun-Jih 莊智清 Juang, Jyh-Ching |
| 學位類別: |
碩士 Master |
| 系所名稱: |
工學院 - 航空太空工程學系 Department of Aeronautics & Astronautics |
| 論文出版年: | 2017 |
| 畢業學年度: | 105 |
| 語文別: | 英文 |
| 論文頁數: | 66 |
| 外文關鍵詞: | CubeSat, Re-entry, Finite Element Method, Thermal Analysis, Floating Langmuir Probe |
| 相關次數: | 點閱:102 下載:3 |
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A re-entry CubeSat mission is being investigated to measure data in-situ for a better understanding of the lower thermosphere. The mission aims to develop a 3U CubeSat to place in orbit the scientific payloads as well as some new subsystems for testing. By successfully using these new subsystems in outer space, it will be demonstrated that they are capable of performing their tasks under the harsh conditions of the space environment.
In order to ensure the survivability of the CubeSat throughout its expected life spam, it is of outermost interest to determine the range of temperatures at which it will oscillate during the orbital phase, so that either a more robust thermal control can be applied or to use subsystems that can withstand these variations. The present study uses the FEA method to simulate the temperature variations and compares the results with the minimum and maximum operational and survivability temperatures of each individual component expected to be in the CubeSat. The results showed that the current configuration of its thermal protection subsystem and placement of the inner components lie within the safe margins to ensure the mission success.
Since one of the scientific missions of this CubeSat is to measure the electron density and electron temperature within the plasma generated on its re-entry through Earth’s ionosphere, a Floating Langmuir Probe was developed to fit the specific conditions of traveling in a nanosatellite. Variations in flush-mounted and needle-built, double probes and triple probes were evaluated in order to find the most suitable configuration for the mission. Design issues revolved around the harness being connected in one extreme to the probe being placed directly in contact with the plasma and on the other extreme to the highly insulated OBC, carrying through it not only the data signal but also the harsh temperatures from the outside. Due to the small size of the CubeSat, it was not possible to use active cooling systems, and so the design played a very important role. In the end, the triple probe, needle-built, made out of Tungsten was selected for this mission.
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