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Design concepts of an aircraft wing: composite and morphing airfoil with auxetic structures

P R BUDARAPU,Sudhir Sastry Y B,R NATARAJAN

《结构与土木工程前沿（英文）》 2016年第10卷第4期页码 394-408 doi: 10.1007/s11709-016-0352-z

摘要： This paper is categorized into two parts. (1) A frame work to design the aircraft wing structure and (2) analysis of a morphing airfoil with auxetic structure. The developed design frame work in the first part is used to arrive at the sizes of the various components of an aircraft wing structure. The strength based design is adopted, where the design loads are extracted from the aerodynamic loads. The aerodynamic loads acting on a wing structure are converted to equivalent distributed loads, which are further converted point loads to arrive at the shear forces, bending and twisting moments along the wing span. Based on the estimated shear forces, bending and twisting moments, the strength based design is employed to estimate the sizes of various sections of a composite wing structure. A three dimensional numerical model of the composite wing structure has been developed and analyzed for the extreme load conditions. Glass fiber reinforced plastic material is used in the numerical analysis. The estimated natural frequencies are observed to be in the acceptable limits. Furthermore, the discussed design principles in the first part are extended to the design of a morphing airfoil with auxetic structure. The advantages of the morphing airfoil with auxetic structure are (i) larger displacement with limited straining of the components and (ii) unique deformation characteristics, which produce a theoretical in-plane Poisson’s ratio of −1. Aluminum Alloy AL6061-T651 is considered in the design of all the structural elements. The compliance characteristics of the airfoil are investigated through a numerical model. The numerical results are observed to be in close agreement with the experimental results in the literature.

关键词： wing design aerodynamic loads morphing airfoil auxetic structures negative Poisson’s ratio

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Design and applications of morphing aircraft and their structures

《机械工程前沿（英文）》 2023年第18卷第3期 doi: 10.1007/s11465-023-0750-6

摘要： Morphing aircraft can adaptively regulate their aerodynamic layout to meet the demands of varying flight conditions, improve their aerodynamic efficiency, and reduce their energy consumption. The design and fabrication of high-performance, lightweight, and intelligent morphing structures have become a hot topic in advanced aircraft design. This paper discusses morphing aircraft development history, structural characteristics, existing applications, and future prospects. First, some conventional mechanical morphing aircraft are examined with focus on their morphing modes, mechanisms, advantages, and disadvantages. Second, the novel applications of several technologies for morphing unmanned aerial vehicles, including additive manufacturing for fabricating complex morphing structures, lattice technology for reducing structural weight, and multi-mode morphing combined with flexible skins and foldable structures, are summarized and categorized. Moreover, in consideration of the further development of active morphing aircraft, the paper reviews morphing structures driven by smart material actuators, such as shape memory alloy and macro-fiber composites, and analyzes their advantages and limitations. Third, the paper discusses multiple challenges, including flexible structures, flexible skins, and control systems, in the design of future morphing aircraft. Lastly, the development and application of morphing structures in the aerospace field are discussed to provide a reference for future research and engineering applications.

关键词： morphing aircraft additive manufacturing lattice structure smart material flexible structure flexible skin

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Structural design of morphing trailing edge actuated by SMA

Qi WANG, Zhiwei XU, Qian ZHU

《机械工程前沿（英文）》 2013年第8卷第3期页码 268-275 doi: 10.1007/s11465-013-0261-y

摘要：

In this paper, the morphing trailing edge is designed to achieve the up and down deflection under the aerodynamic load. After a detailed and accurate computational analysis to determine the SMA specifications and layout programs, a solid model is created in CATIA and the structures of the morphing wing trailing edge are produced by CNC machining. A set of DSP measurement and control system is designed to accomplish the controlling experiment of the morphing wing trailing edge. At last, via the force analysis, the trailing edge is fabricated with four sections of aluminum alloy, and the arrangement scheme of SMA wires is determined. Experiment of precise control integral has been performed to survey the control effect. The experiment consists of deflection angle tests of the third joint and the integral structure. Primarily, the ultimate deflection angle is tested in these two experiments. Therefore, the controlling experiment of different angles could be performed within this range. The results show that the deflection error is less than 4% and response time is less than 6.7 s, the precise controlling of the morphing trailing edge is preliminary realized.

关键词： morphing wing trailing edge shape memory alloy digital signal processor PID algorithm

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Deformation analysis of shape memory polymer for morphing wing skin under airflow

Weilong YIN, Jingcang LIU, Jinsong LENG,

《机械工程前沿（英文）》 2009年第4卷第4期页码 447-449 doi: 10.1007/s11465-009-0062-5

摘要： The method for analyzing the out-of-plane deformation of a flexible skin under airflow is developed in this paper. The aerodynamic analysis is performed using the CFD software, and the structural analysis is performed using finite element method. The chief aim of the present study is to investigate the out-of-plane deformation of the shape memory polymer (SMP) skin at different temperatures. Numerical results show that the maximum out-of-plane displacement of the SMP skin increases with increasing temperature. When the SMP skin is heated to 53°C, the maximum out-of-plane displacement is about 7 mm. It decreases by 72%, when the SMP skin is applied with a uniform pre-strain of 0.1.

关键词： aircraft morphing skin shape memory polymer (SMP) deformation pre-strain

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Kinematical synthesis of an inversion of the double linked fourbar for morphing wing applications

J. AGUIRREBEITIA, R. AVILéS, I. FERNáNDEZ, M. ABASOLO

《机械工程前沿（英文）》 2013年第8卷第1期页码 17-32 doi: 10.1007/s11465-013-0364-5

摘要：

This paper presents the kinematical features of an inversion of the double linked fourbar for morphing wing purposes. The structure of the mechanism is obtained using structural synthesis concepts, from an initial conceptual schematic. Then, kinematic characteristics as instant center of rotation, lock positions, dead point positions and uncertainty positions are derived for this mechanism in order to face the last step, the dimensional synthesis; in this sense, two kinds of dimensional synthesis are arranged to guide the wing along two positions, and to fulfill with the second one some aerodynamic and minimum actuation energy related issues.

关键词： morphing wing structural synthesis dimensional synthesis geometrical kinematics

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Deformation characteristics of corrugated composites for morphing wings

Ruijun GE, Bangfeng WANG, Changwei MOU, Yong ZHOU,

《机械工程前沿（英文）》 2010年第5卷第1期页码 73-78 doi: 10.1007/s11465-009-0063-4

摘要： To meet the needs of morphing and withstand aerodynamic loads of a morphing wing skin, a corrugated glass fabric-epoxy laminated composite is prepared and investigated in this paper. This composite is flexible in the corrugated direction and stiff in the transverse direction to the corrugation. FEM models are established and solved to predict the characteristics of the composites by the commercial FEM software ANSYS. The relationship between the configuration of elongation and tensile load along the corrugation direction is obtained through numerical simulation. To reflect the stretching superiority of the configuration, the elongation of corrugated and flat composites is calculated and compared under the same tensile load. The linear cumulative effect of corrugated composites deformation is proved by calculating the elongation of the composites with several different corrugation numbers. Several corrugated composite specimens were manufactured and tested to verify the results of numerical analysis and the equivalent elastic modulus of the composites were also evaluated through the specimen tests. Results of simulation and experiments show that the corrugated composite provided in this paper can afford obviously larger deformation than the flat one. The corrugated composite can provide a possible choice for morphing wing skin.

关键词： corrugated composites deformation characteristic numerical analysis experiment

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Module-based method for design and analysis of reconfigurable parallel robots

Fengfeng XI, Yuwen LI, Hongbo WANG

《机械工程前沿（英文）》 2011年第6卷第2期页码 151-159 doi: 10.1007/s11465-011-0121-6

摘要：

This paper presents a method for the design and analysis of reconfigurable parallel robots. The inherent modularity in a parallel robot lends itself as a natural candidate for reconfiguration. By taking the branches as building blocks, many modular parallel robots can be constructed, from which a reconfigurable parallel robot can be realized. Among three types of reconfigurations, namely, geometry morphing, topology morphing, and group morphing, the method presented here is for the last two reconfigurations, thereby advancing the current research that is mainly limited to geometry morphing. It is shown that the module-based method not only provides a systematic way of designing a reconfigurable parallel robot, but also offers a unified modeling for robot analysis. Two examples are provided, one showing the topology morphing and the other showing the group morphing.

关键词： reconfigurable parallel robot topology morphing group morphing

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复合式叶片型面测量系统的误差分析与补偿

李兵,陈磊,丁建军,蒋庄德

《中国工程科学》 2013年第15卷第1期页码 39-44

摘要：

针对具有复杂型面的叶片类零件检测中所面临的数字化测量问题，提出了一种复合式的测量原理与方法。分别采用接触式的电感原理和非接触式的激光三角原理测量叶片的叶根基准以及叶身型面，并基于此原理设计研制了叶片型面四坐标测量系统。研究中结合该系统的机械结构特征，对影响其测量精度的各项几何误差进行了系统的分析，并提出了基于激光干涉测量的误差提取与补偿方法。实验结果表明，应用提出的误差分析与补偿方法可有效获取叶片型面四坐标测量系统的几何误差并显著提高其测量精度。

关键词：叶片型面复合式测量原理误差分析误差补偿激光干涉测量

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高层建筑抗风智能幕墙 Article

丁菲, Ahsan Kareem

《工程（英文）》 2020年第6卷第12期页码 1443-1453 doi: 10.1016/j.eng.2020.07.020

摘要：

世界各地城市高层建筑的蓬勃发展使人们对其抗风性能提出了新要求。这涉及选择建筑外形使其风荷载最小化和有效传递荷载的结构拓扑形式。现行方法通常是在设计中寻找最优外形，但是会将其限定在静态或固定的建筑形式下。以台北101和哈利法塔的外形设计为例，气动外形修正通过修改建筑物的外观设计在减小风荷载和风致建筑物响应方面有很好的应用前景。在这些建筑物设计中，引入了横截面的倒角调整和锥度设计。除此之外，另一种引人注目的方案是设计一个能适应城市高楼林立复杂风环境变化的建筑，即设计动态立面。建筑形状的自主动态变形超越了传统静态形状优化设计，通过将传感、计算、传动装置和工程信息学融合在一起的信息物理系统而实现，并在本研究中进行了论证。新提出的方法将使建筑物能够智能地改变其轮廓，最大限度减弱动态风荷载激励，并有望通过利用计算设计的迅速发展，推动高层建筑设计从传统的静态立面转变为动态立面。

关键词：高层建筑气动外形修正自主变形信息物理系统计算设计代理模型机器学习