本文選題：超聲速　切入點：參數(shù)估計　出處：《南京航空航天大學學報》2016年03期 　論文類型：期刊論文

【摘要】：為解決超聲速狀態(tài)下航空發(fā)動機部件蛻化參數(shù)估計與性能恢復控制的難題,基于改進卡爾曼濾波器,通過一種三維插值方法實現(xiàn)超聲速狀態(tài)包線范圍內的發(fā)動機部件蛻化參數(shù)估計。而航空發(fā)動機性能恢復控制是在常規(guī)內環(huán)控制轉速的基礎上增加了外環(huán)控制回路,該回路主要包括推力估計模型與外環(huán)控制器兩部分�；谧钚《酥С窒蛄炕貧w機設計了一種推力估計模型,其輸入采用特征選擇算法篩選推力估計模型的最優(yōu)輸入,相比于傳統(tǒng)的不經(jīng)選擇的推力估計模型,精度有較大提高。設計了外環(huán)模糊PI(Proportional-integral)控制器自適應調節(jié)內環(huán)轉速指令來實現(xiàn)蛻化發(fā)動機性能恢復的目的。最后通過超聲速狀態(tài)下的數(shù)字仿真,驗證了上述發(fā)動機部件蛻化參數(shù)估計與性能恢復控制方案的有效性。
[Abstract]:In order to solve the problems of parameter estimation and performance recovery control of aero-engine components under supersonic condition, an improved Kalman filter is proposed. A three-dimensional interpolation method is used to estimate the degradation parameters of engine components in the range of supersonic state envelope. The performance recovery control of aeroengine is based on the conventional inner loop to control the speed of the engine, and the outer loop control loop is added to the control loop. The loop consists of two parts: thrust estimation model and outer loop controller. Based on least squares support vector regression machine, a thrust estimation model is designed, and its input adopts feature selection algorithm to filter the optimal input of thrust estimation model. Compared with the traditional unselected thrust estimation model, The precision is greatly improved. An outer loop fuzzy PIPIProportional-integralcontroller is designed to adaptively adjust the internal ring speed instruction to achieve the purpose of performance recovery of the degenerated engine. Finally, the digital simulation under supersonic condition is carried out. The effectiveness of the proposed scheme for estimating the degradation parameters of the engine components and the performance recovery control scheme is verified.
【作者單位】： 中航工業(yè)西安航空計算技術研究所;南京航空航天大學能源與動力學院江蘇省航空動力系統(tǒng)重點實驗室;
【分類號】：V232
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本文編號：1646703