中文摘要
在各個領域研究者的努力之下，全球定位系統(Global Positioning System, GPS)技術日趨純熟，於是利用衛星取代地基無線電設施，來提供航機導航資訊的新一代航管技術是今日研究的方向。本論文則著重於將此概念應用至無人飛行載具導航系統的開發研究；而於先趨階段運用超輕航機(MXL II 503)來作系統穩定性及初步精度的測試。該測試系統係以驗證GPS姿態判定方法的精確程度以及開發一即時差分修正導航系統為目的，希冀對日後RMRL實驗室實現無人飛機自動降落技術開發有所助益。經過實驗驗證，本系統之地面UHF差分訊號於高約2500英呎空中可被正確接收，其差分過後的平面精度亦可提昇約2公尺，而利用GPS訊號求解的虛擬姿態判定(Pseudo-attitude)方法亦有一定程度之準確性，若能伴以更嚴謹之濾波等數值方法，其所提供之尤拉角度可克服因使用慣性導航系統所產生的積分誤差，進而達成單一GPS系統提供導航及姿態資訊的目標。

Abstract
Owing to the maturity of Satellite technology and Global Positioning System, the new generation of Air Traffic Management technique is designated to utilize the navigation information provided by the Global Navigation Satellite System (GNSS). For precision landing and take-off of an aircraft, the Local Area Augmentation System (LAAS) is needed to enhance the navigation accuracy, integrity, reliability and availability. Present study simulates the concept of LAAS and has established a ground-based Real-Time DGPS (RT-DGPS) reference station. This base station provides 0.5-meter RMS error and 0.2-meter correction for static horizontal navigation and 1.1-meter RMS error and 2-meter correction for dynamic horizontal navigation. The verification of pseudo-attitude in flight is also accomplished in an ultralight vehicle. The flight test combined with the RT-DGPS technique has qualitatively demonstrated that the GPS-determined attitude is feasible and quantitatively proved the pseudo-roll and pseudo-heading angles are reliable especially.

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