变形机翼关键技术的研究

发布时间：2018-03-18 01:10

本文选题：变形机翼　切入点：柔性蒙皮　出处：《南京航空航天大学》2014年博士论文　论文类型：学位论文

【摘要】：多任务变体飞机相比传统飞机具有更高的飞行效率和更优异的飞行性能,在军用和民用飞行器领域都有着广泛的应用前景。变形机翼作为变体飞机的重要组成部分,近年来日益受到重视,得到了快速的发展,已经从理论研究和实验室研究阶段逐步向实际应用阶段迈进。目前,美国科学家们提出并研究了多种不同的变形机翼构型,对其关键技术进行了广泛而深入的研究,并且在某些型号的飞机上进行了初步应用,得到了显著效果。我国的变形机翼研究工作刚刚起步,目前处于理论或样机测试阶段,技术尚未成熟,也未出现能够进行实际飞行应用的变形机翼。由于航空航天技术的敏感性,国外技术仅见于文献报道,其产品和关键技术也限制对我国出口。为此,加大变形机翼关键技术的研究和开发力度,加速柔性蒙皮、新型智能作动器以及变形机构等变形机翼关键技术的发展,将会有力地促进我国航空航天事业的发展。本文对国内外变体飞机与变形机翼的发展历史及研究现状进行了总结,对变体飞机构型进行了分类并对其研究内容进行了分析。在国内外对变形机翼几项关键技术研究的基础上,以研究和开发拥有自主知识产权的变形机翼为目标,开展了变形机翼柔性蒙皮的结构设计与优化、基于超声电机的变形机翼设计等方面的研究工作,并对两种变形机翼进行了实验测试,验证了变形机翼的性能。本论文的主要研究内容和成果如下:1、提出了一种具有优秀面内性能的褶皱型余弦蜂窝柔性伸缩蒙皮支撑结构。对其面内特性进行了理论与实验研究并通过比较研究对其面内伸缩特性进行了验证。研究了该结构面法向特性与结构参数的关系,并利用Optimus软件对其结构参数进行了优化。2、提出了折线形和U形蜂窝面内褶皱型伸缩蒙皮支撑结构。基于统一的结构参数,对余弦形、V形、折线形以及U形蜂窝四种结构的面内横向等效弹性模量进行了研究。建立了这四种结构的参数化有限元模型并对其面法向承载能力进行了研究。通过综合比较,对这四种面内褶皱型伸缩蒙皮支撑结构性能进行了探讨。3、提出了一种位矩阵基因表示的具有多重约束处理能力的NSGA-II算法,对柔性伸缩和剪切蒙皮支撑结构分别进行拓扑优化并得到了一系列优化结果;提出了一种局部优化算法并将之与NSGA-II算法结合,得到了一种混合多目标优化算法,利用该算法对两种柔性蒙皮支撑结构重新进行了优化计算,获得了更加理想的结果,验证了算法的有效性。4、提出了两种基于超声电机作动的变形机翼:柔性后缘机翼和变后掠机翼,并对其进行了设计与制造。通过面元法对这两种机翼的气动特性进行了研究;详细设计并研究了柔性后缘机翼的柔性伸缩蒙皮与变形机构,通过风洞试验验证了柔性后缘机翼的气动特性;设计了变后掠机翼的柔性剪切蒙皮与变形机构并对其机械性能进行了实验验证。
[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.

【学位授予单位】：南京航空航天大学
【学位级别】：博士
【学位授予年份】：2014
【分类号】：V224

【参考文献】