關鍵字查詢 | 類別:研究報告 | | 關鍵字:微機電飛行資訊量測元件用於姿態計算之實現

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序號 學年期 教師動態
1 101/1 航太系 蕭照焜 教授 研究報告 發佈 微機電飛行資訊量測元件用於姿態計算之實現 , [101-1] :微機電飛行資訊量測元件用於姿態計算之實現研究報告微機電飛行資訊量測元件用於姿態計算之實現Realization of Attitude Determination Using Mems-Based Flight Information Measurement Unit馬德明; 蕭照焜淡江大學航空太空工程學系計畫編號:NSC101-2221-E032-010
 研究期間:201208~201307
 研究經費:481,000行政院國家科學委員會The purpose of research is to transfer the results of the quaternion-based nonlinear filter to integrate the traditional quaternion and gravitational force decomposition methods attitude determination using an in-house designed low-cost MEMS-based flight information measurement unit to on-board flight computer. The nonlinear filter utilizes the evolution of the four elements in the quaternion method for attitude determination as the dynamic model, with the four elements as the states of the filter. The attitude angles obtained from the gravity computations and from the electronic magnetic sensors are regarded as the measurement of the filter. The immeasurable gravity accelerations are deduced from the outputs of the three axes accelerometers, the relative a
2 101/1 航太系 馬德明 教授 研究報告 發佈 微機電飛行資訊量測元件用於姿態計算之實現 , [101-1] :微機電飛行資訊量測元件用於姿態計算之實現研究報告微機電飛行資訊量測元件用於姿態計算之實現Realization of Attitude Determination Using Mems-Based Flight Information Measurement Unit馬德明; 蕭照焜淡江大學航空太空工程學系計畫編號:NSC101-2221-E032-010
 研究期間:201208~201307
 研究經費:481,000行政院國家科學委員會The purpose of research is to transfer the results of the quaternion-based nonlinear filter to integrate the traditional quaternion and gravitational force decomposition methods attitude determination using an in-house designed low-cost MEMS-based flight information measurement unit to on-board flight computer. The nonlinear filter utilizes the evolution of the four elements in the quaternion method for attitude determination as the dynamic model, with the four elements as the states of the filter. The attitude angles obtained from the gravity computations and from the electronic magnetic sensors are regarded as the measurement of the filter. The immeasurable gravity accelerations are deduced from the outputs of the three axes accelerometers, the relative a
[第一頁][上頁]1[次頁][最末頁]目前在第 1 頁 / 共有 02 筆查詢結果