發(fā)布時(shí)間：2019-06-03 09:50

【摘要】：顫振主動(dòng)抑制(以下簡(jiǎn)稱(chēng)為顫振抑制)是近幾十年內(nèi)發(fā)展起來(lái)的氣動(dòng)彈性新技術(shù),主要得益于經(jīng)典控制和現(xiàn)代控制的發(fā)展和成功應(yīng)用。隨著主動(dòng)柔性機(jī)翼概念的提出,人們從以往著力避免氣動(dòng)彈性的負(fù)面效應(yīng)轉(zhuǎn)向充分利用主動(dòng)控制技術(shù)來(lái)獲得所需的氣動(dòng)彈性效應(yīng),使飛行器具有柔性增大、結(jié)構(gòu)重量下降、飛行包線(xiàn)擴(kuò)大、機(jī)動(dòng)性能提高等特點(diǎn),可為下一代飛行器設(shè)計(jì)提供關(guān)鍵技術(shù)。本文以含多操縱面的小展弦比三維機(jī)翼風(fēng)洞模型為研究對(duì)象,開(kāi)展了理論分析、數(shù)值模擬和風(fēng)洞實(shí)驗(yàn)一體化的顫振抑制研究。作者設(shè)計(jì)了顫振抑制控制器,建立了多作動(dòng)機(jī)翼顫振抑制的風(fēng)洞實(shí)驗(yàn)控制系統(tǒng),并在風(fēng)洞實(shí)驗(yàn)中驗(yàn)證了顫振抑制控制器的有效性。本文的主要工作和學(xué)術(shù)貢獻(xiàn)如下:1.提出了一種氣動(dòng)彈性系統(tǒng)中參數(shù)化不確定性建模的新方法。傳統(tǒng)方法直接對(duì)系統(tǒng)狀態(tài)矩陣進(jìn)行不確定性分析,存在重復(fù)建模和不確定性耦合問(wèn)題,使得不確定性模型維數(shù)非常高,給控制器綜合帶來(lái)困難。而新方法從氣動(dòng)彈性建模的根源出發(fā),通過(guò)對(duì)信號(hào)進(jìn)行分析和匯合,避免了不確定性的重復(fù)建模,并能夠?qū)︸詈系牟淮_定項(xiàng)進(jìn)行解耦,從而大幅減少不確定性模型的維數(shù),進(jìn)而可以更有效地設(shè)計(jì)顫振魯棒控制系統(tǒng)。2.針對(duì)含前后緣控制面的二元機(jī)翼/外掛系統(tǒng),使用偶極子網(wǎng)格法,考慮外掛的非定常氣動(dòng)力影響,采用上述建模新方法建立了流速擾動(dòng)下機(jī)翼/外掛氣動(dòng)伺服彈性系統(tǒng)的不確定模型。開(kāi)環(huán)顫振分析驗(yàn)證了新方法的正確性,閉環(huán)仿真結(jié)果表明基于不確定性建模新方法設(shè)計(jì)的控制器能夠大幅提高顫振臨界速度。3.將超聲電機(jī)作動(dòng)器應(yīng)用到三維機(jī)翼顫振抑制中,基于超聲電機(jī)和數(shù)字信號(hào)處理器(DSP)自行設(shè)計(jì)和研制了多作動(dòng)機(jī)翼顫振抑制的風(fēng)洞實(shí)驗(yàn)平臺(tái),通過(guò)DSP的模擬輸出實(shí)現(xiàn)了前后緣超聲電機(jī)的精確角度跟隨。通過(guò)添加額外的輸出方程,成功地將二階微分方程描述的超聲電機(jī)數(shù)學(xué)模型合并到多作動(dòng)機(jī)翼的氣動(dòng)伺服彈性系統(tǒng)方程中,設(shè)計(jì)了多作動(dòng)機(jī)翼顫振抑制的多輸入/多輸出(MIMO)LQG控制器。風(fēng)洞實(shí)驗(yàn)結(jié)果表明,常規(guī)的LQG控制器并不能起到顫振抑制的效果,而對(duì)控制系統(tǒng)中存在的時(shí)滯進(jìn)行補(bǔ)償?shù)腖QG控制器能夠把多作動(dòng)機(jī)翼的顫振臨界速度從34.5 m/s提高到37 m/s。4.自行設(shè)計(jì)并研制了以實(shí)時(shí)仿真器(AD5435)為核心的具有高實(shí)時(shí)性的多作動(dòng)機(jī)翼風(fēng)洞實(shí)驗(yàn)控制系統(tǒng),提出了一種前饋補(bǔ)償?shù)脑隽渴絇ID控制方法,能夠?qū)崿F(xiàn)前后緣直流電機(jī)的精確角度跟蹤。針對(duì)流速和空氣密度不確定性,采用上述建模新方法建立了多作動(dòng)機(jī)翼的氣動(dòng)彈性系統(tǒng)不確定性模型,分別設(shè)計(jì)了顫振抑制的單輸入/單輸出(SISO)和MIMOμ控制器。風(fēng)洞實(shí)驗(yàn)結(jié)果表明,SISO控制器能夠?qū)C(jī)翼顫振臨界速度從36.5 m/s提高到39 m/s,而MIMO控制器能夠?qū)㈩澱衽R界速度從36.5 m/s提高到38 m/s。與LQG控制器相比,μ控制器并沒(méi)有對(duì)時(shí)滯進(jìn)行補(bǔ)償,但是卻能夠有效地抑制顫振,驗(yàn)證了μ控制器的魯棒性。
[Abstract]:Flutter active suppression (hereinafter referred to as flutter suppression) is a new aeroelastic new technology developed in recent decades, which is mainly due to the development and successful application of the classic control and modern control. With the development of the concept of active flexible wing, it is necessary to avoid the negative effect of aeroelasticity from the past to make full use of the active control technology to obtain the required aeroelastic effect, so that the aircraft has the flexibility to increase, the weight of the structure is reduced, the flight envelope is expanded, The mobility can be improved and the key technology can be provided for the design of the next-generation aircraft. In this paper, a three-dimensional wing wind tunnel model with a multi-operating surface is used as the research object, and the theoretical analysis, numerical simulation and the flutter suppression research of wind tunnel experimental integration are carried out. In this paper, the flutter suppression controller is designed, and the wind tunnel experimental control system with multi-action wing flutter suppression is established, and the effectiveness of the flutter suppression controller is verified in the wind tunnel experiment. The main work and academic contribution of this paper are as follows:1. A new method for parametric uncertainty modeling in aeroelastic systems is presented. In the traditional method, the uncertainty analysis of the system state matrix is directly carried out, and the problem of repeated modeling and uncertainty coupling is present, so that the dimension of the uncertainty model is very high, and the difficulty is brought to the synthesis of the controller. The new method, based on the origin of aeroelastic modeling, avoids the repeated modeling of the uncertainty by analyzing and merging the signals, and can decouple the undecided term of the coupling, thus greatly reducing the dimension of the uncertainty model, And the flutter robust control system can be designed more effectively. In view of the two-element wing/ store system with the control surface of the front and rear edge, the unsteady aerodynamic effect of the external store is considered by using the dipole grid method, and the uncertain model of the wing/ external pneumatic servo elastic system under the flow velocity disturbance is established by the new method. The open-loop flutter analysis verifies the correctness of the new method, and the closed-loop simulation results show that the controller designed based on the new method of uncertainty modeling can greatly improve the flutter critical speed. The ultrasonic motor actuator is applied to the flutter suppression of the three-dimensional wing, and a wind tunnel experimental platform is designed and developed based on the ultrasonic motor and the digital signal processor (DSP), and the accurate angle of the front and rear edge ultrasonic motor is realized by the analog output of the DSP. The multi-input/ multiple-output (MIMO) LQG controller for multi-action wing flutter suppression is designed by adding additional output equation, and successfully combining the mathematical model of the ultrasonic motor described by the second order differential equation into the equation of the pneumatic servo elastic system of the multi-action wing. The results of wind tunnel experiment show that the conventional LQG controller can not play the effect of flutter suppression, and the LQG controller that can compensate the time-delay in the control system can increase the flutter critical speed of the multi-acting wing from 34.5 m/ s to 37 m/ s. A multi-action wing wind tunnel experiment control system with high real-time performance based on the real-time simulator (AD5435) is designed and developed. An incremental PID control method for feedforward compensation is proposed, which can realize the accurate angle tracking of the front and rear edge DC motor. In view of the uncertainty of flow velocity and air density, the model of aeroelastic system uncertainty of multi-acting wing is established by using the new method, and the single input/ single output (SISO) and MIMO. mu. controller for flutter suppression are respectively designed. The wind tunnel test results show that the SISO controller can increase the flutter critical speed of the wing from 36.5 m/ s to 39 m/ s, while the MIMO controller can increase the flutter critical speed from 36.5 m/ s to 38 m/ s. In contrast to the LQG controller, the controller does not compensate for the time-delay, but can effectively suppress the flutter and verify the robustness of the.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：博士
【學(xué)位授予年份】：2014
【分類(lèi)號(hào)】：V215.34;TB535

【參考文獻(xiàn)】

相關(guān)期刊論文 前10條

1 唐長(zhǎng)紅,鄒叢青;利用雙目標(biāo)優(yōu)化尋求顫振抑制控制律[J];北京航空航天大學(xué)學(xué)報(bào);1990年02期

2 曹奇凱,陳桂彬;機(jī)翼/外掛系統(tǒng)的顫振主動(dòng)抑制研究[J];航空學(xué)報(bào);1991年10期

3 楊超,鄒叢青;多輸入氣動(dòng)伺服彈性系統(tǒng)抗陣風(fēng)不靈敏性研究[J];航空學(xué)報(bào);2000年06期

4 楊超;宋晨;吳志剛;張?chǎng)妮x;;多控制面飛機(jī)的全機(jī)顫振主動(dòng)抑制設(shè)計(jì)[J];航空學(xué)報(bào);2010年08期

5 鄒叢青，陳桂彬;數(shù)字式顫振主動(dòng)抑制系統(tǒng)的研究[J];航空學(xué)報(bào);1994年06期

6 鄒叢青,陳桂彬;機(jī)翼/外掛顫振主動(dòng)抑制的控制律研究[J];力學(xué)學(xué)報(bào);1991年03期

7 王衛(wèi)平 ,顧仲權(quán) ,李鳴 ,周蒂蓮;顫振主動(dòng)抑制系統(tǒng)的試驗(yàn)研究[J];南京航空航天大學(xué)學(xué)報(bào);1988年02期

8 劉紅軍,楊智春,惠曉明;電流變液在飛機(jī)操縱面顫振半主動(dòng)控制中的應(yīng)用研究[J];西北工業(yè)大學(xué)學(xué)報(bào);2000年01期

9 孫偉,胡海巖;基于多級(jí)磁流變阻尼器的操縱面振動(dòng)半主動(dòng)抑制——阻尼器設(shè)計(jì)與試驗(yàn)建模[J];振動(dòng)工程學(xué)報(bào);2005年01期

10 于明禮;胡海巖;;基于超聲電機(jī)作動(dòng)器的翼段顫振主動(dòng)抑制[J];振動(dòng)工程學(xué)報(bào);2005年04期

相關(guān)博士學(xué)位論文 前1條

1 孫偉;基于多級(jí)磁流變阻尼器的顫振半主動(dòng)抑制[D];南京航空航天大學(xué);2005年

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