提高模型精度以及保證方程求解收斂是目前發(fā)動機(jī)建模亟待解決的問題。該文以雙轉(zhuǎn)子加力渦噴發(fā)動機(jī)的數(shù)學(xué)模型為例，介紹了線性狀態(tài)空間模型的建立，提出了一種根據(jù)發(fā)動機(jī)進(jìn)口參數(shù)進(jìn)行飛行包線區(qū)域劃分的方法，在應(yīng)用該方法得到的飛行區(qū)域內(nèi)，發(fā)動機(jī)模型的結(jié)構(gòu)參數(shù)攝動最小。
關(guān) 鍵 詞 航空發(fā)動機(jī); 數(shù)學(xué)模型; 線性狀態(tài)空間; 飛行包線

Abstract Improving models’ precision and ensuring equation’s resolution constringency are two unresolved problems in engine modeling. The mathematical model of twin-rotor accelerating turbo-jet engine is taken as an example to illustrate the modeling of linear state-space model. A method is proposed for dividing the flight envelope into a number of sub-regions in witch the perturbations of aeroengine model are relatively small.
Key words aeroengine; mathematical model; linear state-space; flight envelope