| DC 欄位 |
值 |
語言 |
| DC.contributor | 太空科學與工程研究所 | zh_TW |
| DC.creator | 黃偉豪 | zh_TW |
| DC.creator | Wei-Hao Huang | en_US |
| dc.date.accessioned | 2023-7-24T07:39:07Z | |
| dc.date.available | 2023-7-24T07:39:07Z | |
| dc.date.issued | 2023 | |
| dc.identifier.uri | http://ir.lib.ncu.edu.tw:444/thesis/view_etd.asp?URN=110623007 | |
| dc.contributor.department | 太空科學與工程研究所 | zh_TW |
| DC.description | 國立中央大學 | zh_TW |
| DC.description | National Central University | en_US |
| dc.description.abstract | 本文目的為對珍珠號(Propagation Experiment using Kurz-Above-band Radio in Low earth orbit, PEARL)系列立方衛星進行結構分析，主要對搭載鐳洋科技研發的K/Ka-band通訊實驗酬載（K/Ka-band Communication Payload, KCP）與國立中央大學太空酬載實驗室研製的CIP（Compact Ionosphere Probe）科學酬載，以及對搭載創未來科技的通訊酬載（Communication Payload, CPL）與鴻海科技集團的相機模組的PEARL-1C及PEARL-1H這兩枚立方衛星進行分析。珍珠號立方衛星預計使用SpaceX的獵鷹9號火箭部署至距地表550公里的低地球軌道（Low Earth Orbit, LEO）執行任務，其軌道形式為太陽同步軌道（Sun Synchronous Orbit, SSO），因此本文將著重於分析發射環境對珍珠號所施加的各式外力，以及其在任務軌道上的軌道熱模擬，以評估珍珠號的結構設計是否能通過發射環境及太空環境的考驗。 | zh_TW |
| dc.description.abstract | The purpose of this paper is to analyze the structure of the Pearl (Propagation Experiment using Kurz-Above-band Radio in Low earth orbit, PEARL) series cube satellites, It is mainly equipped with the K/Ka-band communication experimental payload (K/Ka-band Communication Payload, KCP) developed by RAPIDTEK TECHNOLOGIES INC. and the CIP (Compact Ionosphere Probe) scientific payload developed by the Space Payload Laboratory of National Central University, and Analyze these two CubeSats, PEARL-1C and PEARL-1H, equipped with the Communication Payload (CPL) of Tron Future Technology and the camera module of Foxconn Technology Group. The PEARL CubeSat is expected to use SpaceX′s Falcon 9 rocket to deploy to a low earth orbit (Low Earth Orbit, LEO) mission 550 kilometers above the Earth’s surface, and its orbit is in the form of a sun synchronous orbit (Sun Synchronous Orbit, SSO). Therefore, this paper will focus on analyzing the various external forces exerted by the launch environment on the PEARL, as well as its orbital thermal simulation on the mission orbit, to assess whether the structural design of the Pearl can pass the test of the launch environment and the space environment. | en_US |
| DC.subject | 珍珠號 | zh_TW |
| DC.subject | 立方衛星 | zh_TW |
| DC.subject | 結構 | zh_TW |
| DC.subject | 結構分析 | zh_TW |
| DC.subject | PEARL | en_US |
| DC.subject | Cubesat | en_US |
| DC.subject | Structure | en_US |
| DC.subject | Structure analyze | en_US |
| DC.title | 珍珠號立方衛星之結構分析 | zh_TW |
| dc.language.iso | zh-TW | zh-TW |
| DC.title | PEARL CubeSat Structure Analyze | en_US |
| DC.type | 博碩士論文 | zh_TW |
| DC.type | thesis | en_US |
| DC.publisher | National Central University | en_US |