【摘要】：航空發(fā)動(dòng)機(jī)是強(qiáng)非線性復(fù)雜動(dòng)力系統(tǒng),在實(shí)際工作中往往會(huì)受到外界干擾信號(hào)或測(cè)量噪聲的影響,使得轉(zhuǎn)速很難跟蹤到目標(biāo)轉(zhuǎn)速。同時(shí),由于在飛行過程中,發(fā)動(dòng)機(jī)各項(xiàng)參數(shù)的變化范圍較大,采用傳統(tǒng)方法設(shè)計(jì)單一的線性變參數(shù)控制器,很難保證在全飛行包線內(nèi)系統(tǒng)的穩(wěn)定性。然而,以航空發(fā)動(dòng)機(jī)為研究對(duì)象,針對(duì)以上兩點(diǎn)的相關(guān)研究鮮有報(bào)道。在本文中,采用切換控制理論及魯棒控制中的H∞控制理論設(shè)計(jì)控制器來實(shí)現(xiàn)高壓轉(zhuǎn)軸轉(zhuǎn)子轉(zhuǎn)速的跟蹤控制。首先,依據(jù)渦扇發(fā)動(dòng)機(jī)的氣體動(dòng)力學(xué)原理和能量守恒定理,建立部件級(jí)模型,并通過構(gòu)建共同工作方程,使得各個(gè)部件相互約束,發(fā)生聯(lián)動(dòng)效應(yīng)。其次,利用牛頓-拉夫遜方法,求解非線性方程組,并在非線性模型的基礎(chǔ)上,利用“抽功法”建立小偏離線性化模型。最后,為了便于仿真實(shí)現(xiàn),對(duì)平衡流形展開模型進(jìn)行離散化處理,建立離散的線性變參數(shù)系統(tǒng),再選擇合理的映射方式,使得模型更為準(zhǔn)確地貼近原系統(tǒng),保證模型精度。應(yīng)用切換控制的思想,將原系統(tǒng)按高壓轉(zhuǎn)子轉(zhuǎn)速的大小劃分為若干個(gè)子系統(tǒng),降低保守性,并采用滯后切換律,有效地提高了切換系統(tǒng)的性能,避免發(fā)生震顫。應(yīng)用線性矩陣不等式求解出共同Lyapunov函數(shù),并給出相應(yīng)的定理和理論證明,保證切換系統(tǒng)的穩(wěn)定性。應(yīng)用H∞控制理論求解出帶有參數(shù)依賴的輸出反饋控制器,并在數(shù)值仿真實(shí)例中進(jìn)行驗(yàn)證,同時(shí)將設(shè)計(jì)的控制器應(yīng)用到某型號(hào)渦扇發(fā)動(dòng)機(jī)模型中,結(jié)果表明在擾動(dòng)信號(hào)存在的條件下,高壓轉(zhuǎn)子轉(zhuǎn)速能夠無差跟蹤到目標(biāo)轉(zhuǎn)速,實(shí)現(xiàn)控制目標(biāo)。
[Abstract]:Aeroengine is a strong nonlinear complex power system. In practice, it is often affected by external disturbance signal or measurement noise, which makes it difficult to track the target speed. At the same time, because of the large range of engine parameters in flight, it is difficult to ensure the stability of the system in the whole flight envelope by using the traditional method to design a single linear variable parameter controller. However, the aero-engine as the research object, the above two related studies are rarely reported. In this paper, the switching control theory and the H 鈭，

本文編號(hào)：2205805