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高可靠度3U立方衛星之電源系統研製 = = Design and Imp...

蕭崇恩

高可靠度3U立方衛星之電源系統研製 = = Design and Implementation of High Reliability Electrical Power System for 3U Cubesat /

Record Type:	Language materials, printed : Monograph/item
Title/Author:	高可靠度3U立方衛星之電源系統研製 =/ 蕭崇恩.
Reminder of title:	Design and Implementation of High Reliability Electrical Power System for 3U Cubesat /
remainder title:	Design and Implementation of High Reliability Electrical Power System for 3U Cubesat.
Author:	蕭崇恩
Published:	雲林縣 :國立虎尾科技大學 , : 民113.07.,
Description:	[10], 96面 :圖, 表 ; : 30公分.;
Notes:	指導教授: 陳裕愷.
Subject:	Reliability Analysis. -
Online resource:	電子資源

高可靠度3U立方衛星之電源系統研製 = = Design and Implementation of High Reliability Electrical Power System for 3U Cubesat /
蕭崇恩

高可靠度3U立方衛星之電源系統研製 =Design and Implementation of High Reliability Electrical Power System for 3U Cubesat /Design and Implementation of High Reliability Electrical Power System for 3U Cubesat.蕭崇恩. - 初版. - 雲林縣 :國立虎尾科技大學 ,民113.07. - [10], 96面 :圖, 表 ;30公分.

指導教授: 陳裕愷.

碩士論文--國立虎尾科技大學飛機工程系航空與電子科技碩士班.

含參考書目.

本論文所提出的高可靠度3U立方衛星電源系統由生成、儲能、轉換與控制四個部份組成。生成部份由太陽能板透過SEPIC轉換器生成能量，使用三段式擾動觀察法進行最大功率追蹤，使追蹤時間縮短至1秒，轉換效率可高達84.63%。SEPIC轉換器具有昇/降壓轉換、輸入與輸出電壓同相、輸入電流連續性及短路保護等優點，適用於模組化電力系統開發。此外，電路中加入旁路繼電器，當電池電壓過低或轉換器故障時，開啟繼電器使太陽能板能直接對電池充電，以保障衛星系統的任務運行。儲能部份使用2串4並的鋰電池組，其電池組具有保護電路，可提供過充、過放、過流與短路保護的功能。電力系統中還新增衛星電源硬體重啟繼電器，允許透過地面通訊的方式對衛星電力系統進行硬體重啟，使其在控制器當機時恢復初始狀態。轉換部份包含18組獨立的Buck轉換器電路，其中15組可獨立開關，轉換器電路分為小功率與大功率兩種電源，矽開關小功率電源效率最高可達91.11%，氮化鎵高功率電源效率最高可達96.11%。經過系統架構的可靠度分析，本文所提出的衛星電源系統可靠度高達0.9801。控制部份，系統可通過不同的工作模式來開啟不同的次系統，當電壓低於設定值時，會強制關閉全部次系統電源，並在電池電壓回升高於設定值時重新開啟。由於衛星在外太空環境需要面對真空、極端溫度變化與高輻射等挑戰，因此必須先在地面進行真空熱循環、輻射以及運送所需的振動等測試，以確保衛星從運送到發射後能正常運作，通過實作與環境測試驗證了電力系統的可行性與可靠性。.

(平裝)Subjects--Topical Terms:

1450795
Reliability Analysis.

高可靠度3U立方衛星之電源系統研製 = = Design and Implementation of High Reliability Electrical Power System for 3U Cubesat /
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246 1 1 $a Design and Implementation of High Reliability Electrical Power System for 3U Cubesat.
250 $a 初版.
260 # $a 雲林縣 : $b 國立虎尾科技大學 , $c 民113.07.
300 $a [10], 96面 : $b 圖, 表 ; $c 30公分.
500 $a 指導教授: 陳裕愷.
500 $a 學年度: 112.
502 $a 碩士論文--國立虎尾科技大學飛機工程系航空與電子科技碩士班.
504 $a 含參考書目.
520 3 $a 本論文所提出的高可靠度3U立方衛星電源系統由生成、儲能、轉換與控制四個部份組成。生成部份由太陽能板透過SEPIC轉換器生成能量，使用三段式擾動觀察法進行最大功率追蹤，使追蹤時間縮短至1秒，轉換效率可高達84.63%。SEPIC轉換器具有昇/降壓轉換、輸入與輸出電壓同相、輸入電流連續性及短路保護等優點，適用於模組化電力系統開發。此外，電路中加入旁路繼電器，當電池電壓過低或轉換器故障時，開啟繼電器使太陽能板能直接對電池充電，以保障衛星系統的任務運行。儲能部份使用2串4並的鋰電池組，其電池組具有保護電路，可提供過充、過放、過流與短路保護的功能。電力系統中還新增衛星電源硬體重啟繼電器，允許透過地面通訊的方式對衛星電力系統進行硬體重啟，使其在控制器當機時恢復初始狀態。轉換部份包含18組獨立的Buck轉換器電路，其中15組可獨立開關，轉換器電路分為小功率與大功率兩種電源，矽開關小功率電源效率最高可達91.11%，氮化鎵高功率電源效率最高可達96.11%。經過系統架構的可靠度分析，本文所提出的衛星電源系統可靠度高達0.9801。控制部份，系統可通過不同的工作模式來開啟不同的次系統，當電壓低於設定值時，會強制關閉全部次系統電源，並在電池電壓回升高於設定值時重新開啟。由於衛星在外太空環境需要面對真空、極端溫度變化與高輻射等挑戰，因此必須先在地面進行真空熱循環、輻射以及運送所需的振動等測試，以確保衛星從運送到發射後能正常運作，通過實作與環境測試驗證了電力系統的可行性與可靠性。.
520 3 $a The high-reliability 3U CubeSat power system proposed in this thesis consists of four parts: generation, storage, conversion, and control. The generation part uses solar panels to generate energy through a SEPIC converter. By employing a three-stage perturb-and-observe method for maximum power point tracking (MPPT), the tracking time is reduced to 1 second, and the conversion efficiency can reach up to 84.63%. The SEPIC converter offers advantages such as boost/buck conversion, in-phase input and output voltage, continuous input current, and short-circuit protection, making it suitable for modular power system development. Additionally, a bypass relay is incorporated into the circuit. When the battery voltage is too low or the converter fails, the relay opens to allow the solar panels to charge the battery directly, ensuring the satellite system's mission operation. The storage part uses a 2-series, 4-parallel lithium battery pack with a protection circuit that provides overcharge, over-discharge, overcurrent, and short-circuit protection. The power system also includes a satellite power hardware reset relay, which allows for hardware reset of the satellite power system via ground communication, restoring it to its initial state in case of a controller crash. The conversion part comprises 18 independent Buck converter circuits, 15 of which can be switched on and off independently. The converter circuits are divided into low-power and high-power supplies, with the highest efficiency of the silicon low-power supply reaching 91.11%, and the gallium nitride high-power supply reaching a maximum efficiency of 96.11%. This not only saves energy, but improves reliability. The control part of the system can activate different subsystems through various operating modes. When the voltage falls below a set value, all subsystem power supplies are forcibly shut down, and they are reactivated when the battery voltage rises above the set value. Since satellites need to withstand the challenges of vacuum, extreme temperature changes, and high radiation in outer space, vacuum thermal cycling tests, radiation tests, and vibration tests required for satellite transportation are conducted on the ground to ensure the satellite operates normally from transportation to post-launch. Finally, the feasibility and reliability of the power system were validated through implementation and environmental testing. Reliability analysis shows that the proposed satellite power system achieves a high reliability of 0.9801..
563 $a (平裝)
650 # 4 $a Reliability Analysis. $3 1450795
650 # 4 $a Perturb and Observe. $3 1450794
650 # 4 $a Gallium Nitride. $3 1225522
650 # 4 $a Cubesat. $3 1150883
650 # 4 $a 可靠度分析. $3 1026589
650 # 4 $a 擾動觀察法. $3 995441
650 # 4 $a 氮化鎵. $3 996074
650 # 4 $a 立方衛星. $3 1150880
856 7 # $u https://handle.ncl.edu.tw/11296/6k69kr $z 電子資源 $2 http