本文關(guān)鍵詞：渦軸發(fā)動(dòng)機(jī)模型修正及控制方法研究　出處：《南京航空航天大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： 渦軸發(fā)動(dòng)機(jī) 部件特性修正 H_2/H_∞控制器 微分進(jìn)化算法

【摘要】：高精度的渦軸發(fā)動(dòng)機(jī)模型是渦軸發(fā)動(dòng)機(jī)控制系統(tǒng)設(shè)計(jì)的基礎(chǔ),提高模型精度使其與試車數(shù)據(jù)相匹配是極其重要的研究?jī)?nèi)容。而先進(jìn)的控制規(guī)律可以提升渦軸發(fā)動(dòng)機(jī)的功率響應(yīng)速度以及轉(zhuǎn)速抗干擾能力,是渦軸發(fā)動(dòng)機(jī)控制系統(tǒng)設(shè)計(jì)的重點(diǎn)與難點(diǎn)。為此本文從某型渦軸發(fā)動(dòng)機(jī)模型與實(shí)驗(yàn)數(shù)據(jù)的匹配以及發(fā)動(dòng)機(jī)控制規(guī)律兩個(gè)方面開展研究工作。在模型匹配方面,首先對(duì)部件級(jí)模型的設(shè)計(jì)點(diǎn)精度進(jìn)行修正�；谧冞m應(yīng)度函數(shù)的微分進(jìn)化算法,對(duì)各部件特性修正系數(shù)進(jìn)行優(yōu)化,以達(dá)到減小總體建模誤差,提高模型精度的目的。采用變步長(zhǎng)牛頓-拉夫遜迭代算法,基于平衡方程殘差范數(shù)變化趨勢(shì)來改變牛頓-拉夫遜迭代算法的步長(zhǎng),提高了模型的收斂性和收斂速度。在穩(wěn)態(tài)模型的基礎(chǔ)上,采用微分進(jìn)化算法對(duì)核心部件的引氣系數(shù)、非轉(zhuǎn)動(dòng)部件的總壓恢復(fù)系數(shù)以及各轉(zhuǎn)動(dòng)部件的特性進(jìn)行了修正,使修正后的模型在設(shè)計(jì)點(diǎn)的輸出與試車數(shù)據(jù)匹配精度滿足要求。在模型非設(shè)計(jì)點(diǎn)匹配方面,采用了兩種方法進(jìn)行修正。一種是對(duì)非設(shè)計(jì)點(diǎn)的相鄰兩條轉(zhuǎn)速線進(jìn)行修正達(dá)到多點(diǎn)匹配,另外一種是采用修正因子函數(shù)的方法,以已匹配的非設(shè)計(jì)點(diǎn)換算轉(zhuǎn)速線為基準(zhǔn),對(duì)非設(shè)計(jì)點(diǎn)進(jìn)行修正。在修正完成的發(fā)動(dòng)機(jī)模型基礎(chǔ)上,針對(duì)功率控制以及轉(zhuǎn)速控制系統(tǒng)設(shè)計(jì)控制器�；谛_動(dòng)法建立狀態(tài)變量模型,利用DE(微分進(jìn)化)算法進(jìn)行模型元素的求解,提高了模型的建模精度�；跔顟B(tài)變量模型,針對(duì)功率控制設(shè)計(jì)了基于LMI(線性矩陣不等式)方法的H_2/H_∞控制器,針對(duì)轉(zhuǎn)速控制設(shè)計(jì)了基于多目標(biāo)優(yōu)化算法的H_2/H_∞控制器求解。論文通過仿真驗(yàn)證了算法的有效性。
[Abstract]:High precision turboshaft engine model is the basis of turboshaft engine control system design. Improving the accuracy of the model and matching it with the trial data is a very important research content. The advanced control law can improve the power response speed and speed anti-interference capability of turboshaft engine, and is the key and difficult point of turboshaft engine control system design. In this paper, the research work is carried out from two aspects: the matching of the model of a certain type of vortex shaft engine and the experimental data and the control law of the engine. In the aspect of model matching, the precision of the design point of the component level model is corrected. Based on the differential evolution algorithm of variable fitness function, the correction coefficient of each part is optimized, so as to reduce the overall modeling error and improve the accuracy of the model. The variable step Newton lahson iteration algorithm is used to change the step length of the Newton Ravson iterative algorithm based on the change trend of the residual norm of the balance equation, which improves the convergence and convergence speed of the model. Based on the steady-state model, the total pressure of air entraining coefficient, non rotating parts of the differential evolution algorithm on the core components of the recovery coefficient and the characteristics of the rotating parts is modified, the modified model in the design of output point with test data, the accuracy meets the requirements. In the non design point matching of the model, two methods are used to modify the model. One is to modify the two adjacent speed lines of non design points to achieve multi point matching. The other one is to use modified factor function to modify the non design points based on the matching non design point converted speed line. On the basis of the modified engine model, the controller is designed for the power control and the speed control system. Based on the small perturbation method, the state variable model is built, and the DE (differential evolution) algorithm is used to solve the model element, and the modeling accuracy is improved. Based on the state variable model, a H_2/H_ infinity controller based on LMI (linear matrix inequality) method is designed for power control. A H_2/H_ objective controller based on multi-objective optimization algorithm is designed for speed control. The validity of the algorithm is verified by simulation.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V235.12

【參考文獻(xiàn)】

相關(guān)期刊論文 前10條

1 王軍;隋巖峰;;求解航空發(fā)動(dòng)機(jī)數(shù)學(xué)模型的迭代算法及其改進(jìn)算法的收斂性研究[J];系統(tǒng)仿真學(xué)報(bào);2014年02期

2 許津津;馬進(jìn);唐永紅;賀仁睦;;基于改進(jìn)DE算法的負(fù)荷建模參數(shù)辨識(shí)[J];電力系統(tǒng)保護(hù)與控制;2009年24期

3 邱威;張建華;劉念;;微分進(jìn)化算法在電力系統(tǒng)中的應(yīng)用[J];現(xiàn)代電力;2009年05期

4 白磊;陳思兵;江和甫;;基于模型辨識(shí)的發(fā)動(dòng)機(jī)部件特性修正研究[J];燃?xì)鉁u輪試驗(yàn)與研究;2009年03期

5 楊欣毅;沈偉;劉海峰;董可海;;一種應(yīng)用滑動(dòng)最小二乘求取壓氣機(jī)特性的方法[J];航空動(dòng)力學(xué)報(bào);2009年08期

6 楊欣毅;劉海峰;董可海;;依據(jù)試驗(yàn)數(shù)據(jù)求取航空發(fā)動(dòng)機(jī)部件特性的新方法[J];航空計(jì)算技術(shù);2009年03期

7 吳虎;張亮;馮維林;;一種多級(jí)軸流壓氣機(jī)特性預(yù)測(cè)的工程方法[J];航空動(dòng)力學(xué)報(bào);2009年01期

8 陳玉春;徐思遠(yuǎn);楊云鎧;屠秋野;商旭升;;改善航空發(fā)動(dòng)機(jī)特性計(jì)算收斂性的方法[J];航空動(dòng)力學(xué)報(bào);2008年12期

9 王磊;楊煜普;宮亮;蘇海軍;;基于微分進(jìn)化算法的自適應(yīng)濾波的應(yīng)用[J];自動(dòng)化儀表;2008年05期

10 劉慧;劉永文;;基于通用級(jí)特性圖的壓氣機(jī)特性計(jì)算方法[J];能源技術(shù);2008年02期

相關(guān)博士學(xué)位論文 前2條

1 李秋紅;航空發(fā)動(dòng)機(jī)智能魯棒控制研究[D];南京航空航天大學(xué);2011年

2 周文祥;航空發(fā)動(dòng)機(jī)及控制系統(tǒng)建模與面向?qū)ο蟮姆抡嫜芯縖D];南京航空航天大學(xué);2006年

相關(guān)碩士學(xué)位論文 前4條

1 姜殿文;航空發(fā)動(dòng)機(jī)部件特性修正技術(shù)研究與控制系統(tǒng)設(shè)計(jì)[D];南京航空航天大學(xué);2012年

2 王前宇;基于控制結(jié)構(gòu)優(yōu)化的航空發(fā)動(dòng)機(jī)多變量魯棒控制研究[D];南京航空航天大學(xué);2010年

3 榮立燁;基于神經(jīng)網(wǎng)絡(luò)的航空發(fā)動(dòng)機(jī)控制研究[D];西北工業(yè)大學(xué);2007年

4 袁鴦;發(fā)動(dòng)機(jī)自適應(yīng)建模及神經(jīng)網(wǎng)絡(luò)控制[D];南京航空航天大學(xué);2005年

，

本文編號(hào)：1347542