探空八號火箭／姿態量測（制式）模組
國科會國防科技學術合作研究計畫主持人：趙吉光副教授
(Launched at 15:00, 6/5/2013)
Taiwan’s sounding rocket programs are funded by National Space Organization. The rockets are fabricated by Chung-Shan Institute of Science and Technology (CSIST) programs to provide vehicle services for domestic scientific missions. However, no complete attitude information of the rockets was available at the beginning of the programs. It is due to high spin rate of the rockets and mechanical gyroscopes fail in this condition. Based on previous flight tests from the SR-III and SR-VII, scientific results could be greatly improved if attitude information were available. A new aspectmeter to measure the attitude of the sounding rockets is required for future missions. In this proposal, an aspectmeter (ASM) consisted of a 3-axis MEMS-based gyroscope, magnetometer, and accelerator with a digital processing system is designed to meet the specifications of the Taiwan’s sounding rockets. The ASM will be evaluated by CSIST’s navigation test platform and National Central University’s environmental test facility and then can be installed on the SR-VIII, SR-IX, and SR-X for flight tests. The attitude information will be provided for flight analysis and scientific missions.
目前國家太空中心委託中山科學研究院製作的探空火箭，僅由全球定位系統接收機獲取軌跡資訊與加速計得到火箭轉速，並無完整的火箭姿態量測。由探空三號與探空七號之飛試資料研判，中科院有必要提供完整的飛行姿態量測制式裝備，以釐清相關科學任務的分析結果。過去所採用的姿態模組多屬於機械式陀螺儀與加速度計。但此類型的陀螺儀僅適合低轉速飛行。而加速度計在自由落體的過程中，無法確知重力方向。因此原先的姿態量測模組必須重新規劃與設計，以研發可適合我國探空火箭高轉速的特性。在本計畫中，使用三軸式（或以單軸與雙軸式來組合）微機電系統陀螺儀、磁力計、與加速計製作探空火箭用姿態量測模組。配合類比數位轉換與數位資料處理，可即時將量測資訊傳送給探空火箭輸出入處理單元。並使用中科院的導航測試裝備與中大太空酬載實驗室的環境測試設施，完成姿態量測模組的校正與測試等工作，並符合探空火箭制式裝備的規範。所研製的姿態量測模組，將安置在我國探空八號火箭上進行驗證與改良。其量測的飛行姿態，可供飛行研判與科學酬載團隊使用。