標題: 用子空間判別飛機氣動力係數(橫向系統)Using Subspace Identification for Aircraft Aerodynamic Parameter(Lateral System) 作者: 陳大彬Chen, Ta-Bin吳永春Yung-Chun Wu電控工程研究所 關鍵字: 氣動力係數;判別;飛機;Aerodynamic;Identification;Aircraft 公開日期: 1997 摘要: 本論文探討在模擬飛機作側飛飛行(轉彎)時,如何即時的將參數判別出來, 首先,建立飛機側飛時系統的模型及完整的線性化方程式,在平衡點(高 度30000呎、速度0.5馬赫)為模擬的起始點,氣動力係數、高度、速度等外 在環境,作為模擬時變動的依據。而本論文的重點是在即時判別的結果與 原本參數的變動是否追蹤的到,亦或是只有極小比例的差異。為了模擬實 際飛行的情形,我們曾經到訪新竹空軍基地,請飛官將實際飛行情形及狀態 詳細敘述,然後參觀了模擬機的操作與試飛。參觀後,使得我們的輸入輸出 資料建立,能夠更符合實際飛行情形,而不再是憑空猜想。我們判別的方法 是子空間(subspace)判別法,它的特點就是可以即時的將A、B、C、D矩陣 判別出來。我們可以很快的比較出判別前與判別後(離散)的差異。總之, 用此種方法於此種模型上,所得到的判別結果,可提供未來發展的參考。 In this thesis, how identify real time parameters when airplane is simulated lateral (turn) flying is very important. First, building system model when airplane lateral flying and completely linear equation. The proportional point (height is 30000ft and velocity is 0.5 Mach) is simulate start point. The environment is including aerodynamic parameter、height and velocity etc, is varying reliance by simulating. Therefore, the important of this thesis are real time result and how small is primal parameter's vaFrom simulating practical flying condition, we ever visit Hsinchu airbase, and request an aviator to explicate practical flying condition and situation. Then, we visit simulator operation and test flight. After visitation, which makes us simulating input and output data building is more coincidental like practical flying condition, and is not cloud castle.Subspace identification method is our using method. Its characteristic is capable to identify matrices A、B、C and D on real time. We can compare the difference between before identifying and after identifying soon. Altogether, Using this method on this model, which the identification result is got can be reference for future upgrowth. URI: http://140.113.39.130/cdrfb3/record/nctu/#NT860591051http://hdl.handle.net/11536/63231 Appears in Collections: Thesis