太空飛行器電力次系統硬體迴路測試平台之建立

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姓名

林品安(Pin-An Lin) 查詢紙本館藏

畢業系所

太空科學與工程研究所

論文名稱

太空飛行器電力次系統硬體迴路測試平台之建立
(Implementation of Hardware in-the-loop Test Platform for Spacecraft Electrical Power Subsystem)

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摘要(中)

對於執行太空任務的衛星等飛行器而言，一趟成功的任務將帶來許多可貴的成果，比如科技的進步、解謎未知的深太空科學現象、人才的教育與培養等，然而飛行器必須運行在極度嚴苛的太空環境，承受著相當大的高低溫差以及高能量帶電粒子的不斷打擊，一旦藉由火箭發射升空後若有執行上的異常便只能從地面上傳指令試圖進行修復，因此太空任務能夠被視為是同時具備高價值、高成本、且高風險的計畫。為了確保這樣的計畫能夠順利完成，發射前的各項功能與整合測試勢必是不可缺少，然而在地面進行的測試仍可能會因為與實際之太空環境不同而有潛在的問題難以被診測出，利用硬體迴路測試 (Hardware in the Loop, HIL) 的技術能夠以較低成本的方式使被測系統盡量以貼近真實運作環境的條件下執行功能測試。本文將針對在衛星任務中出現異常機率較高的電力次系統 (Electrical Power Subsystem, EPS) 進行HIL測試，建立電力次系統硬體迴路測試平台 (EPS Hardware in the Loop, EHIL)，並將以已於2021年1月發射的3U立方衛星飛鼠號任務為EHIL平台開發的模擬對象，測試飛鼠號的EPS在長時間運作下的發電、儲電、與配電的能力與穩定度，透過任務期間所下傳的信標封包資料與EHIL平台的模擬結果進行比對以驗證平台的完成度，並期望能夠應用於未來的衛星任務之EPS長期忍受度以及功能驗證。

摘要(英)

For spacecraft such as satellites that execute space missions, a successful mission will bring countless valuable achievements, such as technological improvements, exploration of unknown scientific phenomena in deep space, and education and training of skilled professionals, etc. However, the spacecraft must operate in the extremely harsh space environment, withstanding a considerable temperature difference and the impact of high energy charged particles. Once launched by a rocket, if there is an abnormal event, it can only be addressed remotely by uplinking commands from a ground station. Therefore, space missions can be regarded as high-value, high-cost, and high-risk projects. In order to ensure that the project can be successfully completed, functional and integration tests are essential before launch. However, tests conducted on the ground may still have potential problems that are difficult to diagnose due to differences between the ground and the actual space environment. Hardware in the Loop (HIL) technology enables the system under test to perform functional tests under the conditions close to the real operating environment in a low-cost manner. This thesis will conduct HIL tests on a spacecraft Electrical Power Subsystem (EPS) which is a subsystem with a high probability of abnormality in satellite missions, and build an EPS Hardware in the Loop (EHIL) test platform. The platform uses the EPS from a 3U CubeSat mission, the Ionospheric Dynamics Exploration and Attitude Subsystem Satellite (IDEASSat / INSPIRESat-2), already launched in January 2021 as the simulation object for developing EHIL. Moreover, it also tests the ability and stability of the IDEASSat EPS in power generation, storage, and distribution under long-term operations. The performance of the platform is verified by comparing the simulation results from EHIL with the beacon packet data which downlinked during the commissioning of the spacecraft. It is expected to be applied to the long-term endurance and functional verification of EPS units for future satellite missions.

關鍵字(中)

★ 立方衛星
★ 硬體迴路測試
★ 電力次系統

關鍵字(英)

★ CubeSat
★ Hardware in-the-loop
★ Electrical Power Subsystem

論文目次

摘要 i
Abstract ii
誌謝 iv
目錄 v
圖目錄 viii
表目錄 xii
符號說明 xiii
一、緒論 1
1-1 前言 1
1-2 立方衛星與系統架構 2
1-3 論文概要 4
二、迴路測試介紹 5
2-1 系統開發與模擬 5
2-1-1 系統測試過程與標準 5
2-1-2 迴路測試類型 7
2-2 硬體迴路測試應用於衛星任務 9
三、飛鼠號任務 12
3-1 飛鼠號任務介紹 12
3-1-1 任務目標 12
3-1-2 次系統架構 13
3-1-3 任務操作模式 16
3-2 飛鼠號發射成果 17
四、飛鼠號電力次系統 26
4-1 電力需求 26
4-2 飛鼠號EPS架構 28
4-2-1 電力源 28
4-2-2 EPS運作架構 31
五、電力次系統硬體迴路測試平台之設計 33
5-1 平台設計架構與執行流程 33
5-1-1 EHIL配置架構 33
5-1-2 迴路測試流程 34
5-2 運行環境之邏輯判定 38
5-2-1 地蝕判斷 38
5-2-2 地面站通聯判斷 44
5-3 Arduino控制介面 48
5-3-1 次系統電源開關之GPIO控制 49
5-3-2 EPS健康資料讀取之I2C介面 50
5-4 任務操作模式切換流程 54
5-5 電子負載控制 57
5-5-1 操作模式 58
5-5-2 控制介面 61
5-6 太陽能陣列模擬器控制 63
六、迴路平台功能驗證 67
6-1 EHIL測試平台之開發成果 67
6-1-1 EHIL平台整合 67
6-1-2 EHIL平台功能測試 69
6-2 平台模擬準確度 74
6-2-1 邏輯判定演算 74
6-2-2 EPS資料讀取 76
6-2-3 Timer計時器 78
6-3 EHIL平台於飛鼠號任務之應用 80
6-3-1 信標封包比較 81
6-3-2 任務執行推估 85
七、討論與總結 87
7-1 EHIL成果討論 87
7-1-1 INA3221電壓電流感測計量測敏感度 87
7-1-2 EHIL平台價值 91
7-2 總結 92
參考文獻 94
附錄一 100

參考文獻

［1］Celestrack Orbit Visualization. Access on 18 February, 2022. From https://celestrak.com/
［2］Alicia Johnstone. “CubeSat Design Specification Rev. 14.” San Luis Obispo, CA, July, 2020.
［3］Doug Sinclair, Jonathan Dyer. “Radiation effects and COTS parts in SmallSats.” Small Satellite Conference, Utah State University, USA, August 13, 2013.
［4］Charles D. Brown. Elements of Spacecraft Design. Reston, VA, USA: American Institute of Aeronautics and Astronautics, Inc. 2002.
［5］Fowler, Kim R. and Silver, Craig L. Developing and Managing Embedded Systems and Products: Methods, Techniques, Tools, Processes, and Teamwork. Oxford: Newnes, January 1, 2015.
［6］John Adam. “What is the V-model approach to software development and testing?” September 24, 2021. From https://kruschecompany.com/v-model-software-development-methodology/
［7］Jens Eickhoff. Simulating Spacecraft Systems. 1st Edition. New York: Springer, 2009.
［8］ISO. “19683: 2017: Space Systems—Design Qualification and Acceptance Tests of Small Spacecraft and Units.” Vol 1, ISO, July, 2017.
［9］S. Corpino, and F. Stesina. “Verification of a CubeSat via hardware-in-the-loop simulation.” IEEE Transactions on Aerospace and Electronic Systems. Vol 50, 2014, pp. 2807-2818, DOI: 10.1109/TAES.2014.1303700.
［10］Ledin, Jim A. “Hardware-in-the-loop simulation.” Embedded Systems Programming. Vol 12, 1999, pp. 42-62.
［11］Chen Xiang, et al. “Real Time Software-in-the-Loop Simulation for Control Performance Validation.” Simulation, Vol 84, August, 2008, pp. 457-471, DOI: 10.1177/0037549708097420.
［12］Wittawat Tapsawat, et al. “Development of a hardware-in-loop attitude control simulator for a CubeSat satellite.” IOP Conference Series: Materials Science and Engineering, Vol 297, 2018.
［13］H. Hu, et al. “Hardware-In-the-Loop Simulation of Electric Vehicle Powertrain System.” 2009 Asia-Pacific Power and Energy Engineering Conference, March, 2009, pp. 1-5, DOI: 10.1109/APPEEC.2009.4918397.
［14］Aki Kuusisto, “Hardware-In-The-Loop Test Setup for Battery Management Systems.” Master’s Thesis, Tampere University of Technology, November, 2017, DOI: 10.13140/R G.2.2.11480.80644.
［15］Hu Min, et al. “Thruster Control for Micro-satellite Attitude and Hardware-in-the-loop Demonstration.” 2012 International Conference on Industrial Control and Electronics Engineering, August, 2012, pp. 588-591, DOI: 10.1109/ICICEE.2012.160.
［16］Park, Jae-Ik, et al. “Hardware-in-the-loop simulations of GPS-based navigation and control for satellite formation flying.” Advances in Space Research, Vol 46, 2010, pp. 1451-1465, DOI: 10.1016/j.asr.2010.08.012.
［17］Jonis Kiesbye, et al. “Hardware-In-The-Loop and Software-In-The-Loop Testing of the MOVE-II CubeSat.” Aerospace, Vol 6, Num 12, Multidisciplinary Digital Publishing Institute, 2019, pp. 130.
［18］K. S. Badaruddin, et al. “The Importance of Hardware-In-The-Loop Testing to the Cassini Mission to Saturn.” 2007 IEEE Aerospace Conference, 2007, pp. 1-9, DOI: 10.1109/AERO.2007.352985.
［19］Thyrso Villela, et al. “Towards the Thousandth CubeSat: A Statistical Overview.” International Journal of Aerospace Engineering, Vol 2019, 2019.
［20］Frost, and Sullivan. “Commercial Communications Satellite Bus Reliability Analysis.” August, 2004.
［21］Geoffrey A. Landis, et al. “Causes of Power-Related Satellite Failures.” 2006 IEEE 4th World Conference on Photovoltaic Energy Conference, May, 2006, pp. 1943-1945, DOI: 10.1109/WCPEC.2006.279878.
［22］RS Dabas. “Ionosphere and its influence on radio communications.” Resonance. Vol 5, July, 2000, pp. 28-43, DOI: 10.1007/BF02867245.
［23］Geeta Rana, and Mayank Yadav. “The ionosphere and radio propagation.” Journal Impact Factor. Vol 5, 2014, pp. 9-16.
［24］Habila Mormi John. “Ionospheric Irregularities and their Impact on Global Navigation Satellite Systems (GNSS).” Doctoral Thesis, University of Bath, September 8, 2021.
［25］Yi Duann, et al. “IDEASSat: A 3U CubeSat mission for ionospheric science.” Advances in Space Research, Vol 66, July 1, 2020, pp. 116-134, DOI: 10.1016/j.asr.2020.01.012.
［26］Zai-Wun Lin, et al. “Advanced Ionospheric Probe scientific mission onboard FORMOSAT-5 satellite.” Terrestrial, Atmospheric and Oceanic Sciences, Vol 28, April 1, 2017, DOI: 10.3319/TAO.2016.09.14.01.
［27］Chang, Loren C., et al. “Integration, Launch, and First Results from IDEASSat / INSPIRESat-2–A 3U CubeSat for Ionospheric Physics and Multi-National Capacity Building.” Small Satellite Conference, Utah State University, USA, 2021.
［28］Yi-Chung Chiu, et al. “Lessons Learned from IDEASSat: Design, Testing, On Orbit Operations, and Anomaly.” International Conference on Astronautics and Space Exploration, Hsinchu, Taiwan, November 16-18, 2021.
［29］Yi-Chung Chiu, et al. “Lessons Learned from IDEASSat: Design, Testing, On Orbit Operations, and Anomaly Analysis of a First University CubeSat for Ionospheric Science.” Aerospace, Vol 9, February 18, 2022, DOI: 10.3390/aerospace9020110.
［30］SPACEX - TRANSPORTER-1 MISSION. January 24, 2021. From https://www.space x.com/launches/transporter-1-mission/
［31］SatNOGS network - Observation. Access on March 11, 2022. From https://net work.satnogs.org/observations/?future=0&bad=0&failed=0&norad=47458&observer=&station=&start=&end=
［32］Matthew Joplin. “A Method for Characterization of Single-Event Latchup in CMOS Technologies as A Function of Geometric Variation.” Master’s Thesis, the Faculty of the University of Tennessee, August, 2018.
［33］Kyechong Kim, and Agis A. Iliadis. “Latch-up effects in CMOS inverters due to high power pulsed electromagnetic interference.” Solid-State Electronics. Vol 52, October 1, 2008, pp. 1589-1593, DOI: 10.1016/j.sse.2008.06.041.
［34］蔡林融：＜飛鼠號立方衛星電力次系統設計＞。碩士論文，國立中央大學，民國108年6月。
［35］T. Dittrich. “Basic Characteristics and Characterization of Solar Cells.” Materials Concepts for Solar Cells. Vol 3, 2018, DOI: 10.1142/9781786344496_0001.
［36］C. B. Honsberg and S. G. Bowden. “Absorption Coefficient.” Access on January 19, 2022. From www.pveducation.org
［37］AZUR SPACE Solar Power GmbH - SPACE Assemblies, “Triple Junction Solar Cell Assembly 3G30A Data Sheet (HNR 0003401-01-01).” Access on January 19, 2022. From http://www.azurspace.com/index.php/en/products/products-space/space-assemblies
［38］Rong Tsai-Lin, “IDEASSat Electrical Power subsystem ICD rev4.” August 31, 2020.
［39］Mathworks, “Matlab Programming Fundamentals.” September, 2021.
［40］Analytical Graphics, Inc. Systems Tool Kit (STK). Access on March 11, 2022. From https://www.agi.com/products/stk
［41］David A. Vallado. Fundamentals of Astrodynamics and Applications. 4th Edition. Hawthorne, California: Microcosm Press, 2013.
［42］Jeremy Tatum. Ecliptic Coordinates. University of Victoria, December 31, 2020.
［43］Arduino, “Arduino MEGA 2560 & Genuino MEGA 2560.” Access on January 30, 2022. From https://www.arduino.cc/en/Main/arduinoBoardMega2560
［44］TEXAS INSTRUMENTS, “UCC2752x Dual 5-A High-Speed, Low-Side Gate Driver datasheet (Rev. G).” Access on January 30, 2022. From https://www.ti.com/product/UCC27523
［45］VISHAY, “SQ4917EY, Automotive Dual P-Channel 60 V (D-S) 175°C MOSFET.” Access on January 30, 2022. From https://www.vishay.com/mosfets/list/product-62785/
［46］Maxim Integrated, Inc. “MAX17048/MAX17049 3μA 1-Cell/2-Cell Fuel Gauge with ModelGauge.” December 15, 2016.
［47］Analog Devices. “AD7997/AD7998 8-Channel, 10- and 12-Bit ADCs with I2C Compatible Interface in 20-Lead TSSOP.” 2004.
［48］TEXAS INSTRUMENTS, “INA3221 Triple-Channel, High-Side Measurement, Shunt and Bus Voltage Monitor with I2C- and SMBUS-Compatible Interface.” March, 2016.
［49］TEXAS INSTRUMENTS, “TCA9548A Low-Voltage 8-Channel I2C Switch with Reset datasheet (Rev. G).” Access on January 31, 2022. From https://www.ti.com/product/TCA9548A
［50］KEYSIGHT, “Keysight Series N6700C Low-Profile Modular Power System.” Access on February 3, 2022. From https://www.keysight.com/tw/zh/support/key-34741/n6700-series-modular-system-power-supplies-400w-1200w.html
［51］KEYSIGHT, “Keysight N6700 Modular Power System Family.” Access on February 3, 2022. From https://www.keysight.com/tw/zh/support/N6791A/dc-electronic-load-module-1u-height-60-v-20-a-100w.html
［52］KEYSIGHT, Electronic Load Fundamentals. USA, May 11, 2019.
［53］Mathworks - Instrument Control Toolbox. “Control test and measurement instruments and communicate with computer peripherals.” Access on March 14, 2022. From https://www. mathworks.com/products/instrument.html
［54］KEYSIGHT, “Keysight E4360 Modular Solar Array Simulator.” Edition 4, December, 2018. From https://www.keysight.com/tw/zh/support/E4360A/modular-solar-array-simulator-mainframe-1200w.html
［55］KEYSIGHT, “Keysight Technologies Series E4360 Modular Solar Array Simulator.” Edition 8, December, 2018. From https://www.keysight.com/tw/zh/support/E4361A/solar-array-simulator-dc-module-65v-8-5a-510w.html
［56］National Instruments, “GPIB-USB-HS+ Device Specifications.” July 14, 2014. From https://www.ni.com/zh-tw/support/model.gpib-usb-hs-.html
［57］Celestrack. Access on March 14, 2022. From http://celestrak.com/
［58］SatNOGS network - Observation #3537160. Access on January 24, 2022. From https://network.satnogs.org/observations/3537160/
［59］Kathrin Huber, ”Analog sampling: what do accuracy, sensitivity, precision, and noise mean?” July 5, 2018. From https://www.embedded.com/analog-sampling-what-do-accuracy-sensitivity-precision-and-noise-mean/

指導教授

張起維(Loren Chang)

審核日期

2022-5-30

推文