| 姓名 |
許源顯(Yuan-Hsien Hsu)
查詢紙本館藏 |
畢業系所 |
太空科學與工程研究所 |
| 論文名稱 |
海事天線軌道推算器演算法開發
(Orbital propagator algorithm development of Maritime antenna)
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| 相關論文 | |
| 檔案 |
 [Endnote RIS 格式]
[Bibtex 格式]
 [相關文章]  [文章引用]  [完整記錄]  [館藏目錄]  至系統瀏覽論文 (2025-7-10以後開放)
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| 摘要(中) |
海事天線比起地面天線站，在追蹤衛星上還需要面臨海面晃動造成的誤差，因此對於計算衛星位置的精確度會有更高的要求。本研究主要開發海事天線的天線控制單元(Antenna Control Unit, ACU)中衛星軌道推算器，採用C語言撰寫，確保可順利在微控制器(Micro Control Unit, MCU)平台運行，以利後續開發者進行維護。研究的重點目標為將自行計算的衛星位置與業界慣用的Ansys Systems Tool Kit計算的衛星位置的向量夾角，能縮減至0.1度以內。在衛星位置座標轉換的流程上參考(林彥夫，2021)，衛星位置計算使用簡化擾動模型(Simplified General Perturbations Models)中的SGP4衛星軌道推算器，此模型適用於衛星軌道週期小於225分鐘的近地軌道衛星。本研究同時開發適合的應用程式介面(Application Programming Interface, API)，允許使用者將位置向量轉換並輸出至地心地固座標系(Earth Center Earth Fixed, ECEF)、以天線站為中心的東北高座標系(East North Up, ENU)、以及以天線站為中心的衛星所在之方位角與俯仰角，可使後續的應用更加靈活。 |
| 摘要(英) |
Compared with ground antenna stations, maritime antennas also need to face perturbation caused by waves when tracking satellites, so there will be higher requirements for the accuracy of satellite position calculation. This research mainly develops the satellite orbit propagator in the Antenna Control Unit (ACU) of the maritime antenna, which is written in C language to ensure that it can run on the Micro Control Unit (MCU) platform to facilitate subsequent developers’ maintenance. The main goal of the research is to reduce the vector angle between the satellite position calculated by self-developed program and by the Ansys Systems Tool Kit within 0.1 degrees. Refer to the process of satellite position coordinate conversion (Lin, 2021). The satellite position calculation uses the SGP4 orbit propagator in the Simplified General Perturbations Models. This model is suitable for low-Earth orbits with satellite orbit periods less than 225 minutes satellite. This research also develops a suitable Application Programming Interface (API), which allows users to convert and output the position vector to the Earth Center Earth Fixed (ECEF) coordinate system, the north east elevation coordinate (East North Up, ENU) centered on the antenna station, as well as the azimuth and elevation angles of the satellites centered on the antenna station, can make subsequent applications more flexible. |
| 關鍵字(中) |
★ 低軌衛星追蹤
★ 演算法
★ 軌道推算器 |
關鍵字(英) |
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| 論文目次 |
摘 要 i
ABSTACT ii
誌 謝 iii
目 錄 iv
圖 目 錄 vi
表 目 錄 ix
一、 緒論 1
1.1軌道推算 1
二、研究方法 4
2.1 執行流程 4
2.2 時間處理函式 7
2.2.1 isLeap 7
2.2.2 DoY2Date 8
2.2.3 DateTime2JD 9
2.2.4 JD2JDCentury 11
2.2.5 JD2GMST 12
2.2.6 GetTsince 15
2.3 資料處理函式 16
2.3.1 OPCompare 16
2.3.2 TLEhandle, GPShandle, EOPhandle 18
2.3.3 OPCheck 19
2.3.4 angleConversion, arctan 20
2.4 座標轉換函式 21
2.4.1 ECI2ECEF 21
2.4.2 ECEF2ENU 24
2.4.3 LLA2ECEF 26
2.4.4 ENU2AER 28
三、實驗結果 29
3.1 SGP4 輸出結果比較 29
3.1.1 時間經過(Tsince)運算 31
3.1.2 SGP4計算準確度 33
3.2 ECEF輸出結果比較 35
3.3 AER輸出結果比較 38
四、結論與討論 42
4.1 誤差來源 42
4.2 週期性誤差 43
4.3 未來展望 43
五、參考文獻 44
附錄A 軌道推算器次函式 使用文件 45
次函式目錄 45
附錄B 座標系定義說明 72 |
| 參考文獻 |
[1] 林彥夫(2021)。海事天線追蹤低軌道衛星與控制單元開發。國立中央大學，桃園市。
[2] 廖啟珽(2020)。福衛五號軌道推算軟體敏感度及飛行資料分析。國立中央大學，桃園市。
[3] Curtis, Howard D. (2014). Orbital mechanics for engineering students. 3rd ed. Oxford, UK:Elsevier.
[4] Explanation of Julian Day Number Calculation. Retrieved June 11, 2022, from http://www.cs.utsa.edu/~cs1063/projects/Spring2011/Project1/jdn-explanation.html
[5] Hoots, Felix R., and Roehrich, Ronald L. (1980). SpaceTrack Report No. 3: Models for Propagation of NORAD Element Sets, U.S. Air Force Aerospace Defense Command.
[6] IERS Bulletins. Retrieved April 6, 2022, from https://www.iers.org/IERS/EN/Publications/Bulletins/bulletins.html
[7] Vallado, David A., Seago, John H., Seidelmann, P. Kenneth (2006). Implementation Issues Surrounding the New IAU Reference Systems for Astrodynamics, 16th AAS/AIAA Space Flight Mechanics Conference.
[8] Vallado, David A., and Wayne D. McClain (2013). Fundamentals of Astrodynamics and Applications. 4th ed. Hawthorne, CA: Microcosm Press.
[9] Xu, Guochang (2008). Orbits. 1st ed. Berlin, Heidelberg: Springer Berlin Heidelberg. |
| 指導教授 |
趙吉光
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審核日期 |
2022-7-20 |
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