本文選題：變形機(jī)翼　切入點(diǎn)：柔性蒙皮　出處：《南京航空航天大學(xué)》2014年博士論文　論文類型：學(xué)位論文

【摘要】：多任務(wù)變體飛機(jī)相比傳統(tǒng)飛機(jī)具有更高的飛行效率和更優(yōu)異的飛行性能,在軍用和民用飛行器領(lǐng)域都有著廣泛的應(yīng)用前景。變形機(jī)翼作為變體飛機(jī)的重要組成部分,近年來日益受到重視,得到了快速的發(fā)展,已經(jīng)從理論研究和實(shí)驗(yàn)室研究階段逐步向?qū)嶋H應(yīng)用階段邁進(jìn)。目前,美國(guó)科學(xué)家們提出并研究了多種不同的變形機(jī)翼構(gòu)型,對(duì)其關(guān)鍵技術(shù)進(jìn)行了廣泛而深入的研究,并且在某些型號(hào)的飛機(jī)上進(jìn)行了初步應(yīng)用,得到了顯著效果。我國(guó)的變形機(jī)翼研究工作剛剛起步,目前處于理論或樣機(jī)測(cè)試階段,技術(shù)尚未成熟,也未出現(xiàn)能夠進(jìn)行實(shí)際飛行應(yīng)用的變形機(jī)翼。由于航空航天技術(shù)的敏感性,國(guó)外技術(shù)僅見于文獻(xiàn)報(bào)道,其產(chǎn)品和關(guān)鍵技術(shù)也限制對(duì)我國(guó)出口。為此,加大變形機(jī)翼關(guān)鍵技術(shù)的研究和開發(fā)力度,加速柔性蒙皮、新型智能作動(dòng)器以及變形機(jī)構(gòu)等變形機(jī)翼關(guān)鍵技術(shù)的發(fā)展,將會(huì)有力地促進(jìn)我國(guó)航空航天事業(yè)的發(fā)展。本文對(duì)國(guó)內(nèi)外變體飛機(jī)與變形機(jī)翼的發(fā)展歷史及研究現(xiàn)狀進(jìn)行了總結(jié),對(duì)變體飛機(jī)構(gòu)型進(jìn)行了分類并對(duì)其研究?jī)?nèi)容進(jìn)行了分析。在國(guó)內(nèi)外對(duì)變形機(jī)翼幾項(xiàng)關(guān)鍵技術(shù)研究的基礎(chǔ)上,以研究和開發(fā)擁有自主知識(shí)產(chǎn)權(quán)的變形機(jī)翼為目標(biāo),開展了變形機(jī)翼柔性蒙皮的結(jié)構(gòu)設(shè)計(jì)與優(yōu)化、基于超聲電機(jī)的變形機(jī)翼設(shè)計(jì)等方面的研究工作,并對(duì)兩種變形機(jī)翼進(jìn)行了實(shí)驗(yàn)測(cè)試,驗(yàn)證了變形機(jī)翼的性能。本論文的主要研究?jī)?nèi)容和成果如下:1、提出了一種具有優(yōu)秀面內(nèi)性能的褶皺型余弦蜂窩柔性伸縮蒙皮支撐結(jié)構(gòu)。對(duì)其面內(nèi)特性進(jìn)行了理論與實(shí)驗(yàn)研究并通過比較研究對(duì)其面內(nèi)伸縮特性進(jìn)行了驗(yàn)證。研究了該結(jié)構(gòu)面法向特性與結(jié)構(gòu)參數(shù)的關(guān)系,并利用Optimus軟件對(duì)其結(jié)構(gòu)參數(shù)進(jìn)行了優(yōu)化。2、提出了折線形和U形蜂窩面內(nèi)褶皺型伸縮蒙皮支撐結(jié)構(gòu)�；诮y(tǒng)一的結(jié)構(gòu)參數(shù),對(duì)余弦形、V形、折線形以及U形蜂窩四種結(jié)構(gòu)的面內(nèi)橫向等效彈性模量進(jìn)行了研究。建立了這四種結(jié)構(gòu)的參數(shù)化有限元模型并對(duì)其面法向承載能力進(jìn)行了研究。通過綜合比較,對(duì)這四種面內(nèi)褶皺型伸縮蒙皮支撐結(jié)構(gòu)性能進(jìn)行了探討。3、提出了一種位矩陣基因表示的具有多重約束處理能力的NSGA-II算法,對(duì)柔性伸縮和剪切蒙皮支撐結(jié)構(gòu)分別進(jìn)行拓?fù)鋬?yōu)化并得到了一系列優(yōu)化結(jié)果;提出了一種局部?jī)?yōu)化算法并將之與NSGA-II算法結(jié)合,得到了一種混合多目標(biāo)優(yōu)化算法,利用該算法對(duì)兩種柔性蒙皮支撐結(jié)構(gòu)重新進(jìn)行了優(yōu)化計(jì)算,獲得了更加理想的結(jié)果,驗(yàn)證了算法的有效性。4、提出了兩種基于超聲電機(jī)作動(dòng)的變形機(jī)翼:柔性后緣機(jī)翼和變后掠機(jī)翼,并對(duì)其進(jìn)行了設(shè)計(jì)與制造。通過面元法對(duì)這兩種機(jī)翼的氣動(dòng)特性進(jìn)行了研究;詳細(xì)設(shè)計(jì)并研究了柔性后緣機(jī)翼的柔性伸縮蒙皮與變形機(jī)構(gòu),通過風(fēng)洞試驗(yàn)驗(yàn)證了柔性后緣機(jī)翼的氣動(dòng)特性;設(shè)計(jì)了變后掠機(jī)翼的柔性剪切蒙皮與變形機(jī)構(gòu)并對(duì)其機(jī)械性能進(jìn)行了實(shí)驗(yàn)驗(yàn)證。
[Abstract]:Multi task variant aircraft compared to conventional aircraft has higher flight flight efficiency and excellent performance and have broad application prospects in military and civil aircraft. The wing deformation is an important part of the morphing aircraft, has attracted much attention in recent years, has been rapid development, from theoretical research and laboratory research stage step by step to the practical application stage. At present, American scientists proposed and different deformation of wing configuration is studied, the key technologies are studied deeply and widely, and has carried on the preliminary application in some types of aircraft, has a significant effect. The morphing wing research work in China has just started, at present the theory or prototype testing phase, the technology is not yet mature, does not appear to be deformed wing actual flight applications. Because of the sensitivity of the aerospace technology, Only to see foreign technical literature, its products and key technology also limits on China's exports. Therefore, increase research and development efforts to accelerate the key technology of the wing deformation, deformation of flexible skin, the development of key technology of wing actuator and the deformation mechanism of the new intelligent work, will effectively promote the development of China's aerospace industry the development history and research status of the domestic and foreign aircraft wing variants and deformation are summarized, the variant aircraft configuration are classified and the research contents are analyzed. Based on the domestic and foreign research on several key technology on the wing deformation, deformation of wing with independent intellectual property rights in research and development. As the goal, to carry out the deformation of flexible skin wing structure design and Optimization Research of ultrasonic motor based on the deformation of wing design, and two kinds of deformed wing is carried out Test and verify the performance of the wing deformation. The main research contents and results are as follows: 1, an excellent performance in plane fold type cellular cosine flexible telescopic support structure. The skin surface characteristics are studied experimentally and theoretically and through a comparative study to verify the expansion characteristics the plane was studied. The relation of structural plane to the properties and the structure parameters, and the structure parameters were optimized by using.2 Optimus software, the line shaped and U shaped honeycomb inner fold type telescopic covering support structure. The structure parameters based on the unified, the cosine shaped, V shaped, polygonal shape and U honeycomb structure of the four kinds of in-plane transverse equivalent elastic modulus were studied. To establish the parameters of the four kinds of finite element model and the vertical bearing capacity is studied. By comparison, the four plane fold Wrinkled skin type telescopic support structure performance of.3 is discussed, put forward with multiple constraint processing ability of the NSGA-II algorithm is a matrix of gene expression, the flexible extension and shear diaphragm braced structure were topology optimization and obtain a series of optimization results; this paper proposes a local optimization algorithm and combined with NSGA-II algorithm and get a hybrid multi-objective optimization algorithm, two kinds of flexible skin support structure re calculated by the algorithm, obtained more satisfactory results, verify the validity of.4 algorithm, puts forward two kinds of deformation based on the ultrasonic motor wing: Wing flexible trailing edge and variable swept wing, and the design and manufacture. The boundary element method of the two wing aerodynamic characteristics were studied; the detailed design and research of flexible trailing edge wing flexible expansion and deformation of the skin Through the mechanism, the wind tunnel test of flexible trailing edge wing aerodynamic characteristics; design of variable sweep wing flexible shear skin and deformation mechanism and its mechanical properties are tested by the experiments.

【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
【分類號(hào)】：V224

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