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| 系統識別號 |
U0002-2707200713392800 |
| 中文論文名稱
|
TUUSAT-1A微衛星姿態控制系統設計與分析 |
| 英文論文名稱
|
The Design and Analysis of Attitude Control System for Microsatellite TUUSAT-1A |
| 校院名稱 |
淡江大學 |
| 系所名稱(中) |
機械與機電工程學系碩士班 |
| 系所名稱(英) |
Department of Mechanical and Electro-Mechanical Engineering |
| 學年度 |
95 |
| 學期 |
2 |
| 出版年 |
96 |
| 研究生中文姓名 |
黃彥臻 |
| 研究生英文姓名 |
Yen-Jen Huang |
| 學號 |
694340497 |
| 學位類別 |
碩士 |
| 語文別 |
中文 |
| 口試日期 |
2007-07-13 |
| 論文頁數 |
82頁 |
| 口試委員 |
指導教授-洪祖昌
委員-謝清志
委員-陳彥升
委員-翁瑞麟
|
| 中文關鍵字 |
TUUSAT-1A微衛星
姿態控制
模擬器
系統驗證計畫
|
| 英文關鍵字 |
TUUSAT-1A Microsatellite
Attitude Control
Simulator
System Verification Plan
|
| 學科別分類 |
學科別＞應用科學＞機械工程
|
| 中文摘要 |
本文根據微衛星TUUSAT-1A任務目標與符合各次系統之需求來設計姿態控制系統與軟體模擬器，簡稱TUUSIM (TUUSAT-1A SIMulator)。本文採用被動式磁控制系統(PMACS)是由兩個永久性磁鐵與四個磁滯棒並纏繞短路線圈所組成。為了驗證TUUSAT-1A姿態控制系統的效能，以MATLAB電腦程式語言來發展模擬器，模擬結果當從初始轉速180 rpm 降至0.3 rpm 所需要時間為2-3天，穩定後與地磁方向的指向誤差在15°以內，振動角為±5°，此設計符合TUUSAT-1A姿態系統需求。
為了驗證TUUSAT-1A次系統設計與效能由系統工程團隊所提出的TUUSAT-1A系統驗證計畫，由TUUSAT-1A機械系統研究團隊自行發展純軟體的分析工具TUUSIM。TUUSIM是一個任務模擬器在軌道與姿態控制系統(AOCS)模擬器的發展上，整合熱控制系統(TCS)、電源電力系統(EPS)、地面站遙測、命令與範圍(TC&R)與任務操作。 |
| 英文摘要 |
This thesis focuses on the design and analysis of the attitude control system (ACS) and the software simulator TUUSIM (TUUSAT-1A SIMulator) for microsatellite TUUSAT-1A. The subsystem requirements of the TUUSAT-1A ACS are allocated and defined according to the mission objectives and requirements. The passive magnetic attitude control system (PMACS) consisted of 2 permanent magnets and 4 hysteresis rods wrapped with shorted coils was adopted. In order to verify the performance of TUUSAT-1A ACS, the software simulator was developed by the MATLAB computer language. The simulation results of TUUSAT-1A ACS show that the deviation from the z-axis to geomagnetic field direction is less than 15 deg in steady-state and it needs about 2-3 days to slowdown the spin rate from 180 rpm to 0.3 rpm.
In order to verify the design and performances of TUUSAT-1A subsystems, the TUUSAT-1A System Verification Plan was proposed by the System Engineering Team. In order to achieve more realistic simulation and performance analysis, the full-software analytical tool TUUSIM was developed by the Mechanical Subsystem Research Team. TUUSIM is a mission simulator developed on the basis of orbital propagator and attitude simulator, and integrated the codes of thermal distribution, communication coverage, power generation, and mode operation together. |
| 論文目次 |
目錄
中文摘要…………………………………………………………………I
英文摘要………………………………………………………...………II
誌謝…………………………………………………………………..…III
目錄…………………………………………………………......………IV
表目錄…………………………………...………………………..……VII
圖目錄………………………………………….………………...…...VIII
名詞解釋………………………………………………………………..XI
第一章 序論
1-1 前言………………………..……………...…..…………….1
1-2 文獻回顧……………………………………………………5
1-3 研究動機與目的…………………………………………....8
1-4 論文架構………………………………………..…………10
第二章 姿態控制系統介紹與任務分析
2-1 姿態子系統介紹……………………………………….….11
2-2 姿態子系統方案……………………………….………….12
2-3 系統方案分析與選擇…………………………….……….15
2-4 TUUSAT-1A 任務分析…………………………..………15
V
第三章 軌道模型與數學模型的建立
3-1 衛星軌道模型…………………………….……..……..….17
3-2 地球磁場模型…………………………………..………....19
3-3 太陽位置模型………………………………..……..……..20
3-4 太陽能板能量產生…………………………..……..……..22
3-5 通訊系統建立…………………………………….……….23
3-6 系統數學模型…………………………………..…………24
3-7 環境作用力矩……………………………………….....….28
第四章 姿態系統設計與分析
4-1 姿態系統發展介面……………………..………...……….31
4-2 系統動態描述……………………………………...……...31
4-3 被動式磁控制硬體設計與分析…………………...……...33
4-3.1 硬體配置分析……………………………………...36
4-3.2 指向誤差分析……………………………….……..37
4-4 參數分析與選擇…………………………………………..38
4-5 模擬結果討論…………….……………….………………40
4-6 Worst Case 計算………………………………………….42
第五章 任務模擬器設計與分析
5-1 任務模擬器介紹…………………………………………..44
VI
5-2 TUUSIM 設計與發展……………………………………46
5-3 發展成果結果與結論…………………...…….…..………49
第六章 結論與未來展望
6-1 結論………………………………………………….…….51
6-2 未來展望…………………………………….…………….52
參考文獻………………………………………………….…………….53
表目錄
表1.1 世界微衛星姿態控制與穩定方式…………………56
表2.1 姿態系統設計流程…………………………………58
表2.2 姿態子系統控制方式………………………………58
表2.3 一般操作模式介紹…………………………………59
表2.4 方案特性比較………………………………………59
表2.5 方案成本比較………………………………………59
表2.6 衛星與地面站通訊估算……………………………60
表3.1 2000年到2005年地球磁場模型的高斯係數…….60
表4.1 AlNiCo-5材料特性表…………………………….61
表4.2 HyMu-80材料特性表………………………………61
表5.1 Excel Spreadsheets表單範例………………….62
圖目錄
圖2.1 被動式磁控制硬體配置圖…………………………62
圖2.2 被動式磁控制姿態運行圖…………………………62
圖2.3 YamSat三軸磁力控制硬體配置圖……………….63
圖2.4 三軸磁力控制姿態運行圖…………………………63
圖2.5 重力梯度穩定系統示意圖…………………………64
圖2.6 重力梯度桿配置圖…………………………………64
圖2.7 重力梯度穩定控制姿態運行圖……………………65
圖2.8 模擬可通訊範圍……………………………………65
圖3.1 軌道六元素示意圖…………………………………66
圖3.2 衛星軌道模擬與地面站……………………………66
圖3.3 磁偶示意圖…………………………………………67
圖3.4 L-Shell Model……………………………………67
圖3.5 模擬L-Shell Model下地磁變化量……………….68
圖3.6 模擬地球磁場在ECI座標下的變化量…………….68
圖3.7 地球與太陽旋轉角…………………………………68
圖3.8 本影區示意圖………………………………………69
圖3.9 太陽能板接收陽光之有效面積……………………69
圖3.10 地球、衛星與太陽位置關係圖………………….70
圖3.11 各面之陽光入射角……………………………….70
圖3.12 地面站與衛星間之仰角與方位角……………….71
圖3.13 天線追蹤範圍…………………………………….71
圖4.1 系統數學模式架構圖………………………………71
圖4.2 控制平面……………………………………………72
圖4.3 磁鐵與地磁作用圖…………………………………72
圖4.4 磁滯現象B-H曲線圖……………………………….72
圖4.5 磁滯棒重量與despin時間關係圖…………………73
圖4.6 被動式磁控制系統架構圖…………………………73
圖4.7 地磁緯度與水平面夾角之關係圖…………………74
圖4.8 硬體配置圖…………………………………………74
圖4.9 硬體配置與地磁指向之關係圖……………………75
圖4.10 HyMu-80材料B-H特性曲線圖……………………75
圖4.11 重量與despin時間關係圖……………………….76
圖4.12 模擬結果圖形…………………………………….76
圖4.13 衛星自旋角速度圖形…………………………….76
圖4.14 角速度向量輸出圖形…………………………….77
圖4.15 Worst case計算結果……………………………77
圖4.16 模擬Worst Case角速度輸出…………………….77
圖5.1系統驗證架構圖…………………………………….78
圖5.2 驗證概念圖…………………………………………78
圖5.3 軟體平台驗證概念圖………………………………79
圖5.4 衛星任務操作模式圖………………………………79
圖5.5 向光與背光區域功率輸出…………………………80
圖5.6 太陽能單元電流值輸出……………………………80
圖5.7 衛星與地面站通訊聯結……………………………80
圖5.8 衛星表面所照射到的輻射線面積…………………81
圖5.9 表面與內部平均溫度的變化………………………81
圖5.10 模擬器操作介面………………………………….81
圖5.11 系統測試平台架構……………………………….82
圖5.12 TUUSIM方塊圖….……………………………….82 |
| 參考文獻 |
[1] Fischell, R.E., ”Magnetic Damping of the Angular Motion of Earth Satellite”, America Rocket Society Journal, Vol.31 ,No.9 ,Sept.1961 ,pp.1210-1217
[2] Fischell, R.E., ”Passive Magnetic Attitude Control for Earth Satellite”, Advances in Astronautical Sciences, Vol.11 ,Jan.1962 ,pp. 147-177
[3] Chen, Yu ,”The Damped Angular Motion of a Magnetically Oriented Satellite.” Journal of The Franklin Institute, Vol.280, No.4, 1965, pp.291-306
[4] Ovchinnikov, Michael, “Attitude control system for the first Swedish nanosatellite 'MUNIN'” Acta Astronautica, v 46, n 2, 2000, p 319-326
[5] M. Yu. Ovchinnikov, “Passive Magnetic Attitude Control System of the first Russian Nanosatellite TNS-0.” Preprint of the Keldysh Institute of Applied Mathematics RAS, 2005, N 46, 23p.
[6] Ergin E.I, Wheeler P.C. “Magnetic Attitude Control of a spinning Satellite”, Journal of Spacecraft and Rockets ,1965, Vol. 2, No. 6, pp.846-850
[7] Ping Wang, Yu. B. “Satellite Attitude Control Using only Magnetorquers” AIAA paper 98-4430
[8] Michele Grassi, “Attitude Determination and Control for A Small Remote Sensing Satellite” , Acta Astronautica Vol. 40, No. 9, 1997 ,pp. 675-681
[9] Wisniewski, Rafal, “Fully magnetic attitude control for spacecraft subject to gravity gradient”, Automatica, v 35, n 7, Jul, 1999, p 1201-1214
[10] Bak, T.; Wisniewski, R.; Blanke, M. “Autonomous attitude determination and control system for the Ørsted satellite” Aerospace Applications Conference, 1996. Proceedings., 1996 IEEE Vol. 2, 3-10 Feb. 1996 Page:173 - 186
[11] 林煥榮,洪祖昌,李大本,陳正興等, ”小(微)衛星姿態控制分析與設計” ,中國航空太空學刊, Vol.29, No.2, 1997, pp.109-144
[12] C.H. Lin ,Z.C. Hong, C.H. Shih ,and C.K. Chuang, “The Passive Magnetic Stabilization used Magnetic Rods for a Microsatellite TUUSAT-1 ” , presented at 50th International Astronautical Congress , Amsterdam, The Netherlands, 4-8 OCT 1999./IAF-ST-99-W.1.06.
[13] C. H. Lin, Z. C. Hong , H. J. Lin, “The Imagery Payload Design for Passive Magnetically Stabilized Micro-satellite” , AIAA Journal of Spacecraft and Rocket,Vol.40,,No.3,May-June,2003, p396-404
[14] Chung-Hsien Lin ,Zuu-Chang Hong , “Mission and Constellation Design for Low-Cost Weather Observation Satellites”, Journal of Spacecraft and Rockets ,Vol. 41, No. 3, May–June 2004
[15] C.H. Lin ,Z.C. Hong , C.J. Shieh “The Constellation Design of Weather Observation Mission for Gravity-Gradient Stabilized Microsatellites”, Journal of Mechanics, Vol. 20, No. 3, September 2004
[16] Z. C. Hong, Y. H. Chen, C. H. Lin and J. S. Chern, “Aerodynamics and Gravity Gradient Stabilization for Microsatellites”, Acta Astronautica, Vol. 46, No.7 ,2000, pp. 491-499
[17] J.F. Levesque, “Passive Magnetic Attitude Stabilization using Hysteresis Materials” Intelligent Systems,Mechatronics and Aerospace. http://www.geocities.com/jflev/cubesim.htm
[18] Santoni, F., Bolotti, F.,”Attitude determination of small spinning spacecraft using three axis magnetometer and solar panels data” Aerospace Conference Proceedings, 2000 IEEE Vol. 7, 18-25 March 2000 ,pp.127-133
[19] Lovera, Marco. ,Astolfi.Alessandro,”Global magnetic attitude control of spacecraft in the presence of gravity gradient.” IEEE Transactions on Aerospace and Electronic Systems, v 42, n 3, 2006, p 796-804
[20] Ashenberg, Joshua, Lorenzini, Enrico C. “Active gravity-gradient stabilization of a satellite in elliptic orbits”, Acta Astronautica, v 45, n 10, Nov, 1999, pp. 619-627
[21] Lovera, M. , Astolfi, A. “Spacecraft attitude control using magnetic actuators.” Automatica, v 40, n 8, August, 2004, pp.1405-1414
[22] Ovchinnikov, Michael; Pen'kov, Vladimir. “Attitude control system for the first Swedish nanosatellite 'MUNIN'.” , Acta Astronautica, v 46, n 2, 2000, pp. 319-326
[23] Menges,B.M., Guadiamos, C.A. and Lewis, E.K., “Dynamic Modeling of Mirco-Satellite Spartnik’s Attitude.” ,Region VI AIAA Student Conference, Seattle, Washington, April 1997.
[24] Wertz, J.R. ,Larson, W.J. “Space Mission Analysis and Design”, Kluwer Academic Publishers,Dordrecht,The Netherlands, 1991.
[25] Wertz, J.R. “Spacecraft Attitude Dynamics and Control”, Krieger Publishing Company,Florida, 1991, pp.77-111.
[26] Arthur E., Bryson,JR. “Control of Spacecraft and Aircraft”, Princeton university press, pp.50-163
[27] http://ssdl.stanford.edu/ssdl/index.php
[28] Sanguk Lee, Sungki Cho, “Design, Implementation, and Validation of KOMPSAT-2 Software Simulator”, ETRI Journal, Volume 27, Number 2, April 2005
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