國家實驗研究院國家太空中心委託國家中山科學研究院研製的探空火箭，在2014年10月7日完成探空十號的飛試任務後已告一段落。從過去探空五號與七號搭載的磁力計量測結果顯示，火箭的可能姿態與飛試的模擬結果並非一致。因此自探空八號開始，國家中山科學研究院同意搭載由國立中央大學所製作的姿態量測模組（類比式微機電系統加速計、磁力計、陀螺儀組合而成），可對科學資料的校正提供可靠的憑據。然而在探空九號光纖陀螺儀的比較之下，察覺先前採用的陀螺儀在振動環境下無法正確顯示角速度的讀值。並且火箭團隊希望在推進的過程中，能將火箭轉速提升至每秒4.5轉以求飛行穩定。科學團隊則希望在鼻錐罩開啟前，讓轉速降為每秒1轉以求量測穩定。在各種條件改變下，我們在探空十號上採用全數位三軸感測器，重新設計新一代的數位姿態量測模組。本論文將使用探空十號數位姿態模組的飛行量測資料重建火箭姿態，並且與探空八號與九號的姿態量測結果相比較。其證明數位姿態量測模組可符合高低轉速的需求、改善振動環境下的雜訊干擾、可監控減滾裝置運作前後的火箭姿態變異等。;Sounding Rocket X (SR-X), funded by National Space Organization (NSPO) has been successfully launched by National Chung-Shan Institute of Science and Technology (NCSIST) on October 17, 2014. According to data of a three-axes fluxgate magnetometer on board SR-V and SR-VII, the rocket’s attitude is not consistent with the simulation results. Since SR-VIII, an aspectmeter (MEMS analog accelerometers, magnetometers, and gyroscopes) designed and fabricated by NCU is installed on the rockets to provide reliable attitude information for science data calibrations. However, the analog gyroscope of the aspectmeter cannot show correct angular rates under a vibrating condition compared to the fiber optic gyroscope data from the SR-IX. Meanwhile, for stability the SR-X intends to raise the spin rate to 1,620°/s instead of 1,500°/s for the others. A Yo-Yo de-spin is required by scientific team to reduce the spin rate down to 360°/s after the nose cone separation. Under the all new requirements, we re-design a new full digital aspectmeter to incorporate all new digital 3-axis sensors for the SR-X. In this thesis, flight test results of the aspectmeter are used to reconstruct the SR-X’s attitude, and compared with the data of the SR-VIII and the SR-IX. The data indicate that the digital aspectmeter can satisfy the requirements of high--low rotation rates, resistance from the vibration, and monitoring of attitude variation during the Yo-Yo de-spin.
