IDEASSat任務的經驗教訓：大學立方衛星 的設計、測試、在軌運行和異常分析

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姓名

邱奕中(Yi-Chung Chiu) 查詢紙本館藏

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太空科學研究所

論文名稱

IDEASSat任務的經驗教訓：大學立方衛星的設計、測試、在軌運行和異常分析
(Lessons Learned from IDEASSat: Design, Testing, On Orbit Operations, and Anomaly Analysis of a University CubeSat)

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摘要(中)

IDEASSat(Ionospheric Dynamics and Attitude Subsystem Satellite) / INSPIRESat-2，中文命名為飛鼠號，是由國立中央大學所開發的立方衛星，用於進行電離層電漿參數的量測。該計畫任務科學目標為觀測電離層不規則體，工程項目目標為驗證自製衛星結構是否能承受太空環境的考驗。此太空計畫主要由學生負責設計及運行，為此計畫賦予了教育意義。
IDEASSat計劃於2017年4月14日正式啟動，並於2021年1月24日成功發射到近地軌道(Low Earth Orbit, LEO)，並且在執行任務的過程中成功展現出姿態上的穩定控制、衛星的遙測通訊，以及自主操作的飛行軟件和地面系統。軌道運行22天後，衛星發生了1.5個月的通信中斷。與衛星通信恢復兩天后，地面站再次與衛星失去聯繫。通過對兩天恢復期間的下行飛行數據的分析，可以高度確定停電異常的原因和機制。本論文涵蓋了IDEASSat在軌性能的集成、測試和分析，並且記錄整個任務生命週期所得到的經驗及教訓，以提供後續相關任務參考。

摘要(英)

IDEASSat (Ionospheric Dynamics and Attitude Subsystem Satellite) / INSPIRESat-2 is a 3U CubeSat developed by National Central University (NCU) for the measurement of ionospheric plasma parameters, and is also the first spacecraft to be developed by NCU. The primary science mission objective was plasma irregularity observation and the engineering objective was to verify the ability of the self-made satellite system to survive and function in the space environment. This project is mainly designed and operated by students, which also provided this project with educational significance.
IDEASSat program started in April 14, 2017 and was successfully launched into Low Earth Orbit (LEO) on January 24, 2021, and successfully demonstrated attitude determination and control, satellite telemetry communications, and autonomously operating flight software and ground systems during the mission. After 22 days of on orbit operations, the satellite experienced a communication interruption for 1.5 months. After two days of communication recovery with the satellite, the ground station lost contact with the satellite again. The cause and mechanism of the blackout anomaly was determined to a high level of confidence from analysis of the downlinked flight data during the two day recovery period. This dissertation covers the integration, testing, and analysis of on-orbit performance of IDEASSat, and will record the lessons learned during the mission life cycle to provide reference for subsequent related missions.

關鍵字(中)

★ 立方衛星
★ 飛鼠號

關鍵字(英)

★ CubeSat
★ IDEASSat
★ Lessons learned

論文目次

Table of Contents
摘要i
Abstract ii
致謝iii
Table of Contents iv
Figure List vi
Table List viii
1 Introduction 1
1-1 Space Mission System Architecture 1
1-2 CubeSat 2
1-3 Satellite Subsystems 7
1-3-1 Orbital Mechanics (ORB) 7
1-3-2 Propulsion ( 8
1-3-3 Attitude Determination and Control System (ADCS) 8
1-3-4 Electrical Power System (EPS) 9
1-3-5 Thermal Control System (TCS) 9
1-3-6 Command and Data Handling (CDH) 10
1-3-7 Telecommunication (COMM) 10
1-3-8 Structure and Mechanisms (STR) 12
2 IDEASSat Mission 13
3 IDEASSat: Design and Architecture 15
3-1 Spacecraft 15
3-2 Payload: Compact Ionospheric Probe (CIP) 21
3-3 Operating Modes 23
3-4 NCU Ground Station 27
3-4-1 S-band Station 28
3-4-2 UHF / VHF Ground Station 29
3-5 Power budget 32
3-6 Link budget 33
3-7 Mass budget 37
3-8 Radiation environment 38
4 Integration and Test 39
4-1 Flatsat 39
4-2 End to End Test 40
4-3 Vibration Test 42
4-4 Thermal Vacuum Cycling Test (TVCT) 47
4-5 Delivery and Launch Integration 50
5 Flight Data and Anomaly Analysis 53
5-1 Single Event Upset (SEU) 55
5-2 UHF: Reboot Count Anomaly 57
5-3 OBC: Command Reject Anomaly (random noise interference) 58
5-4 STR: Incompletely Deployed Solar Panels 60
5-5 TCS: Temperature Performance 64
5-6 ADCS: Reboot and State Recovery 67
5-7 EPS: Single Event Latch-up (SEL) 69
6 Conclusions and Lessons Learned 74
References 79
Appendix A Vibration test spectrum 83

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指導教授

張起維(Loren C. Chang)

審核日期

2023-6-29

推文