飛鼠號立方衛星之飛行軟體及韌體設計;Flight Software and Firmware Design of IDEASSat/INSPIRESSat-2

NCU Institutional Repository > 地球科學學院 > 太空科學研究所 > 博碩士論文 > Item 987654321/88120

jsp.display-item.identifier=請使用永久網址來引用或連結此文件: http://ir.lib.ncu.edu.tw/handle/987654321/88120

题名:	飛鼠號立方衛星之飛行軟體及韌體設計;Flight Software and Firmware Design of IDEASSat/INSPIRESSat-2
作者:	戴子雅;Tai, Tzu-Ya
贡献者:	太空科學與工程研究所
关键词:	飛鼠號;立方衛星;飛行軟體;韌體;IDEASSat;INSPIRESSat-2;Flight Software;Firmware
日期:	2021-12-14
上传时间:	2022-07-13 18:11:48 (UTC+8)
出版者:	國立中央大學
摘要:	飛鼠號(IDEASSat/INSPIRESSat-2)是一顆3U大小的立方衛星，其任務目的是對地球電離層進行現地量測，以量化全球尺度的電離層變化和小尺度的電離層不規則體。該衛星目前正在太空中運行，已於2020年12月交付，並於2021年1月24日藉由SpaceX的Falcon 9 Block 5(任務名稱：Transporter-1)發射成功，並順利在軌道上啟動並連續自主運作22天。飛行指令已成功上傳至衛星並下傳存放於衛星電腦的飛行資料，驗證了衛星電腦(On Board Computer，OBC)和飛行軟體(Flight Software，FSW)的技術就緒指數(Technological Readiness Level，TRL)達到了9。飛鼠號(IDEASSat)是由台灣國家太空中心資助，並由國立中央大學(NCU)開發。衛星次系統是由商用(COTS)元件和自行開發元件的組合。本論文主要將介紹和討論IDEASSat飛行軟體的評估和設計。主要挑戰包括科學酬載的高精度指向要求、有限的電源、可下載的資料量、自行開發的飛行軟體的可靠性以及飛行軟體對各次系統的有效整合。我們將介紹軟體架構、軟體邏輯設計、FPGA的設計，以及在IDEASSat飛行軟體開發中所遇到的挑戰和經驗學習。小衛星的自主開發也為將來的任務提供了衛星的設計和運行能力，同時也供後進更好地理解了太空與衛星運行環境之間的關係。 ;The Ionospheric Dynamics Exploration and Attitude Subsystem Satellite (IDEASSat/INSPIRESSat-2) is a 3U CubeSat developed to provide in-situ measurements of the Earth′s ionosphere to quantify both global scale ionospheric variability and small-scale irregularities. The spacecraft is currently on-orbit, with delivery in December 2020, and was successfully launched through SpaceX′s Falcon 9 Block 5 (mission name: Transporter-1) on January 24th, 2021. Commands were uplinked to the spacecraft to replay flight data stored by the on board computer (OBC), which successfully completed this task, verifying that the OBC and flight software (FSW) are Technological Readiness Level (TRL) 9. IDEASSat has been funded in part by the Taiwan National Space Organization and developed by National Central University (NCU), Taiwan. The spacecraft subsystems are a combination of commercial off the shelf (COTS) components, and self-developed components. The thesis will mainly introduce and discuss the assessment and design of the flight software of IDEASSat. Key challenges include high precision pointing requirements of science payload, the limited power and downlinkable data volume, reliability of self-developed flight software, and the efficient integration of each subsystem of flight software. We present the concept of software architecture, software logic design, FPGA design, as well as challenges and lessons learned in the development of IDEASSat flight software. The indigenous development of small satellite design and implementation capacity from the IDEASSat mission is also serving future small satellite missions being developed at National Central University, while also providing people with a better appreciation of the relation between space physics and the spacecraft operational environment.
显示于类别:	[太空科學研究所 ] 博碩士論文

文件中的档案:

档案	描述	大小	格式	浏览次数
index.html		0Kb	HTML	92	检视/开启

在NCUIR中所有的数据项都受到原著作权保护.

社群 sharing

数据加载中.....