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杨智春 , 解江 . 柔性后缘自适应机翼的概念设计 [J ] . 航空学报 , 2009 , 30 ( 6 ): 1028 - 1034 . 对H.P.Monner提出的 “可转动翼肋”自适应机翼概念进行运动学研究，推导了驱动位移量和偏转变形量之间的对应关系。这种可变形翼肋可简化为由平面连杆机构组合而成的单自由度系统，能使机翼后缘柔性偏转的同时保持翼面光滑连续。提出了基于曲线逼近原理根据后缘中弧线偏转轨迹优化转轴点布局的翼肋机构设计方法。对悬臂梁型、圆弧型和反悬臂梁型3种偏转距离相等但偏转轨迹不同的柔性后缘进行了方案设计和分析，从翼肋机构的实现、承载能力以及气动特性3方面进行了建模计算和比较研究。结果表明，圆弧型是3种柔性后缘中最佳的设计方案；柔性后缘自适应机翼的设计分析方法是切实可行的，可根据实际需要设计出满足任意后缘偏转要求的自适应机翼。

YANG Z C , XIE J . Concept design of adaptive wing with flexible trailing edge [J ] . Acta Aeronautica et Astronautica Sinica , 2009 , 30 ( 6 ): 1028 - 1034 . (in Chinese) A concept design based on the rotating rib proposed by H.P.Monner is conducted to implement the variable camber adaptive wing concept by means of deforming the trailing edge flexibly with continued and smooth contour. A study is made of the kinematics of the rib structure, which can be simplified as a single degree- of freedom (DOF) leverage system constrained by pivot joints. The pivot location optimization by curve approximation is proposed to design the flexible trailing edge to meet the design requirements. To test the feasibility of the proposed concept design method, a 2D wing model characterized by NACA63015A airfoil with 1000 mm length in chordwise direction is utilized as a benchmark. The maximum deflection displacement of the tip point on the trailing edge as required by the design is 62 mm. Three types of cambered trailing edges with the same tip point deflection displacement but different deflection tracks, i.e., the beam type, the arc of circle type, and the inverse beam type, are introduced. A comparative study is performed in terms of structure realization, load carrying capability, and aerodynamic performance. The result shows that the model-configured with the arc of circle type trailing edge has the best performance and the design method is feasible and practical. It can be applied to any other design proposals of trailing edge deflection based on specific requirements.

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冷劲松 , 孙健 , 刘彦菊 . 智能材料和结构在变体飞行器的应用现状与前景展望 [J ] . 航空学报 , 2014 , 35 ( 1 ): 29 - 45 . DOI: 10.7527/S1000-6893.2013.0265 http://doi.org/10.7527/S1000-6893.2013.0265 变体飞行器可以根据不同的飞行条件改变自身形状以获得最优的气动性能，大大提高飞行器的综合性能，是未来飞行器发展的重要方向之一。新型智能材料和结构具有驱动、变形、承载、传感等特点，为变体飞行器的设计提供了新的技术途径。本文根据不同可变形机翼结构分类，详细阐述了智能材料和结构在自适应结构、智能驱动器和变形蒙皮等方面的研究现状。变体飞行器的实现亟需解决变形/承载一体化蒙皮技术、轻质大输出力驱动器技术和自适应结构技术等关键技术，本文还对智能材料和结构未来在变体飞行器上的应用前景进行了展望。

LENG J S , SUN J , LIU Y J . Application status and future prospect of smart materials and structures in morphing aircraft [J ] . Acta Aeronautica et Astronautica Sinica , 2014 , 35 ( 1 ): 29 - 45 . (in Chinese) DOI: 10.7527/S1000-6893.2013.0265 http://doi.org/10.7527/S1000-6893.2013.0265 Morphing aircraft can alter their shapes to achieve optimal aerodynamic performance under different flight conditions, which will greatly improve the comprehensive performance of the aircraft. Their emergence and development is one of the most important trends of future aircraft. Smart materials and structures have the properties of actuating, morphing, loading, sensing etc., which provide a new technological approach to morphing aircraft design. In this paper, research status is elaborated of smart materials and structures in adaptive structures, smart actuators, and morphing skins. Some key technologies are addressed in detail, such as deformation/loading integrative skins, lightweight high-output actuators, and adaptive structures. The future prospect of the application of smart materials and structures in morphing aircraft is also discussed.

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