本論文針對探空八號與九號的姿態量測模組加以改良，採用全新的三軸數位式感測器（陀螺儀、磁力計、與加速計）製作可安置在探空十號的全數位式姿態量測模組。其優點為可簡化外部電路、減少元件使用等。其缺點為數位邏輯裝置需要使用較多的邏輯閘，並直接控制所有的感測器。該模組現今已通過中山科學院的制式模組測試，目前正進行整合測試中。預計探空十號將可於2014年10月進行飛試，但在本論文完成前無法獲得飛試資料。為明瞭實際飛試可能遭遇的困難，本論文使用探空八號與九號的飛試資料，來探討過去製作的姿態量測模組與光纖陀螺儀的量測結果作比較。其資料顯示，在火箭推進的過程中，姿態量測模組的陀螺儀部分呈現較多的擾動。在自由落體的過程中，姿態量測模組的陀螺儀與光纖陀螺儀的量測結果相近。

This thesis is about to introduce the new designed ASpectMeter (ASM) onboard Sounding Rocket X (SR-X) with advanced 3-axis digital sensors includes gyroscopes, magnetometers and accelerometers respected to the analog type sensors installed on ASM of SR-IX and SR-VIII. The advantage is the simplification of electric circuits and the reduction on the amount of sensor usage. The disadvantage is the increases in the number of logic gates requirement in CPLD, moreover, needs to control sensor directly. The individual ASM has passed the functional test by CSIST, is currently performing the integration test with payload vehicle. The SR-X is anticipated to launch in October this year, causing the absence of the flight data. In order to study the capability of ASM, flight result from SR-IX and SR-VIII is present to show the comparison between previous version of ASM and FOG. It shows that a perturbation from gyroscope records came up while rocket propelling. However, the result of gyroscope is very similar to each other from ASM and FOG while rocket freefall.

1、 探空八號測試品環境接收試驗規範,2011
2、 ASM IDD 探空火箭十號,2011
3、 探空十號PDR審查報告,2012
4、 倪健航,探空火箭姿態計,2013
5、 行政院國家科學委員會應用科技學術合作研究計畫,2014
6、 Analog Devices Inc., ADXL345 data sheet, 2009
7、 STMicroelectronics Inc., L3G4200D data sheet, 2010
8、 Honeywell, Inc., HMC5883L data sheet, 2010
9、 XILINX, Inc., XC2C512 data sheet, 2007
10、 I2C BUS 簡介
11、 John A. Geen, IEEE A&E System Magazine, November 2004
12、 TA0343, Technical Article: Everything about STMicroelectronics’ 3-axis digital MEMS gyroscope, December 2010