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  本文關(guān)鍵詞：航空發(fā)動機(jī)多變量變增益控制器設(shè)計及仿真　出處：《北京航空航天大學(xué)學(xué)報》2016年09期 　論文類型：期刊論文

  更多相關(guān)文章： 渦扇發(fā)動機(jī) 多變量控制 KQ控制算法 變增益調(diào)度 控制器

【摘要】：針對航空發(fā)動機(jī)全包線工作下的多變量變增益控制器設(shè)計問題,給出了一種改進(jìn)的埃德蒙德算法(以下簡稱KQ算法)并進(jìn)行了仿真應(yīng)用。首先,闡明了多變量KQ算法的控制原理與優(yōu)化算法,進(jìn)而通過閉環(huán)期望函數(shù)選擇、控制器結(jié)構(gòu)選擇以及控制器參數(shù)優(yōu)化進(jìn)行了KQ控制器設(shè)計,并針對所設(shè)計的KQ控制器,給出了穩(wěn)定性證明和系統(tǒng)奇異值分析。分析表明所設(shè)計KQ控制器能夠使系統(tǒng)閉環(huán)穩(wěn)定,且具有滿意的低頻指令跟蹤、干擾抑制能力、傳感器噪聲的抑制、高頻未建模動態(tài)的魯棒穩(wěn)定性和低頻發(fā)動機(jī)建模誤差不敏感等性能,滿足發(fā)動機(jī)控制要求。其次,通過調(diào)度變量選擇、設(shè)計點KQ控制器設(shè)計以及采用插值方法的非設(shè)計點KQ控制器設(shè)計等過程實現(xiàn)某型渦扇發(fā)動機(jī)的多變量KQ變增益控制器設(shè)計研究,并進(jìn)行仿真驗證。仿真結(jié)果表明,設(shè)計點條件下,當(dāng)渦輪后溫度和增壓比參考輸入均為階躍信號時,其被控參數(shù)響應(yīng)速度很快,且上升時間均小于1 s,耦合影響小于6%,設(shè)計點KQ控制器滿足控制要求;非設(shè)計點條件下,利用插值方法建立的KQ變增益控制器具有較好的性能,能夠?qū)崿F(xiàn)該型渦扇發(fā)動機(jī)全包線控制性能要求。
[Abstract]:An improved Ednunde algorithm (hereinafter referred to as KQ algorithm) is proposed for the design of variable variable gain controller (VGC) under the full envelope operation of aero-engine. The control principle and optimization algorithm of multivariable KQ algorithm are expounded, and then the design of KQ controller is carried out through the selection of closed-loop expected function, the selection of controller structure and the optimization of controller parameters. For the designed KQ controller, the stability proof and singular value analysis of the system are given. The analysis shows that the designed KQ controller can make the system closed-loop stable and has satisfactory low frequency command tracking. Interference suppression capability, sensor noise suppression, high frequency unmodeled dynamic robust stability and low frequency engine modeling error are insensitive to meet the requirements of engine control. Secondly, through scheduling variables selection. The design of a multi-variable KQ variable gain controller for a turbofan engine is realized by the design of the KQ controller and the non-design point KQ controller using interpolation method. The simulation results show that the response speed of the controlled parameters is fast and the rise time is less than 1 s when the temperature and the booster ratio reference input are step signals at the design point. The coupling effect is less than 6 and the design point KQ controller meets the control requirements. Under the condition of non-design point, the KQ variable gain controller established by interpolation method has better performance and can meet the requirements of the full envelope control performance of the turbofan engine.
【作者單位】： 西北工業(yè)大學(xué)動力與能源學(xué)院;中航工業(yè)西安航空動力控制科技有限公司;
【分類號】：V233.7
【正文快照】： 網(wǎng)絡(luò)出版地址:www.cnki.net/kcms/detail/11.2625.V.20151022.1940.003.html引用格式:李嘉,李華聰,徐軒,等.航空發(fā)動機(jī)多變量變增益控制器設(shè)計及仿真[J].北京航空航天大學(xué)學(xué)報,2016,42(9):1958-1968.LI J,LI H C,XU X,et al.Multi-variable variable gain controller design a

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