太空氣象科學儀器酬載II

Space Weather Science Instrument Payload II

陳立悟(Li-wu Chen)

指導教授 ： 江士標 ； 葉則亮

國立中央大學/工學院/光機電工程研究所/碩士(2012年)

摘要

本論文以開發太空氣象科學儀器酬載(Space Weather Science Instrument Payload)包含本體系統之工程體(Engineering Model)與飛行體(Flying Model)及開發系統之程式體(Programming Model)為目標，希望能完成系統穩定且高可靠度的氣象科學量測應用。
本太空氣象科學儀器酬載本體系統整合了主控數位訊號處理次系統(Digital Processing Unit)、電源供應處理次系統(DC/DC Power Supply)及以下五組科學儀器次系統：三軸地球磁場感測次系統(Magneto-Resistive Magnetometer)、分離式三軸地球磁場感測次系統(Separate Magneto-Resistive Magnetometer)、電漿電子溫度及濃度感測系統(Electron Temperature Probe & Electron Density Probe)、雙波長氣暉光剖面儀次系統(Airglow Photo-Tomograph Instrument)及酬載三軸加速度與旋轉速度感測次系統(Gravity & Gyro)。期望能藉由科學儀器酬載量測到的太空氣象數據，分析而得到太空氣象變化的相關線索。
為了確保資料的正確性及整個科學儀器酬載的穩定性，本論文並整合多個開發測試平台，建構出科學儀器酬載開發系統，可以針對科學儀器酬載的任務需求做功能及性能上的驗證。希望本論文所開發之太空氣象科學儀器酬載不論是硬體或韌體的設計上都能確實且穩定地執行所設定的任務目標及功能。

關鍵字

加速度 ； 旋轉速度 ； 重力 ； 暉光剖面儀 ； 太空氣象 ； 科學儀器 ； 酬載 ； 衛星 ； 地球磁場 ； 電漿電子溫度 ； 電漿電子濃度

並列摘要

This thesis aims to develop space weather science instrument payload including ontology system(engineering model and flying model) and development system(program model), hoping to complete the system stability and high reliability of weather science measurement applications.
Ontology system of the space weather science instrument payload integrates digital signal processing unit, DC/DC power supply system and the following five scientific instruments system: magneto-resistive magnetometer sub-system, separate Magneto-Resistive magnetometer sub-system, plasma electron temperature and density probe sub-system, airglow photo-tomograph instrument sub-system, gravity and gyro sensing sub-system. Using the space weather data measured by the instrument, we expect to analyze the clues relating to space weather changes.
In order to ensure the accuracy of the information and the stability of the scientific instruments payload, this thesis construct a scientific instrument payload development system that integrates multiple development platform and testing platform. The development system can help the scientific instrument payload on the mission requirements for functionality and performance verification. I hope the space weather science instrument payload, whether the objectives and functions of the design of hardware or firmware can be really stable implementation of the tasks set.

並列關鍵字

gravity ； gyro ； airglow ； electron density ； space weather ； science instrument ； payload ； satellite ； magnetometer ； electron temperature

參考文獻

[1] S. B. Jiang, T. L. Yeh, H. C. Yeh, J. Y. Liu, Y. H. Hsu, and L.Y. Liu, “System Architecture of the BCU Payload on Tatiana-2”, Terrestrial, Atmospheric and Oceanic Sciences, 2011.

[2] Koh-Ichiro Oyama, Yoshihiro Kakinami, Jann-Yenq Liu, Masashi Kamogawa, and Tetsuya Kodama,“Reduction of electron temperature in low-latitude ionosphere at 600 km before and after large earthquakes”, Journal of Geophysical Research, 2008.

[3] Mei-Lan Hsu, Panthalingal Krishnanunni Rajesh, Jann-Yenq Liu, Lung-Chih Tsai, Ho-Fang Tsai, Chien-Hung Lin, Ken neth F. Dymond, Clay ton Coker, Damien H. Chua, Scott A. Budzien, and Chio-Zong Cheng,“Ionospheric Electron Density Concurrently Derived by TIP and GOX of FORMOSAT-3/COSMIC”, Terrestrial, Atmospheric and Oceanic Sciences, 2008.

[4] Yoshihiro Kakinami, Shigeto Watanabe, Jann-Yenq Liu, and Nanan Balan, “Correlation between electron density and temperature in the topside ionosphere”, Journal of Geophysical Research, 2011.

[5] Huixin Liu, Hermann Luhr, and Shigeto Watanabe,“A solar terminator wave in thermospheric wind and density simultaneously observed by CHAMP”, Geophysical Research Letters, 2009.