Deformation characteristics of corrugated composites for morphing wings

被引：16
作者：
Ge R. [1 ]
Wang B. [1 ]
Mou C. [1 ]
Zhou Y. [1 ]
机构：
[1] Aeronautical Science Key Laboratory of Smart Materials and Structures, Nanjing University of Aeronautic and Astronautic
来源：
Frontiers of Mechanical Engineering in China | 2010年 / 5卷 / 1期
基金：
中国国家自然科学基金;
关键词：
Corrugated composites; Deformation characteristic; Experiment; Numerical analysis;
D O I：
10.1007/s11465-009-0063-4
中图分类号：
学科分类号：
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. © Higher Education Press and Springer-Verlag 2009.
引用
收藏
页码：73 / 78
页数：5
相关论文
共 11 条
  • [1] Ramrkahyani D.S., Lesieutre G.A., Frecker M., Bharti S., Aircraft Structural Morphing using Tendon Actuated Compliant Cellar Trusses, (2004)
  • [2] Yang S.B., Xu M., Research on Flight control of a smart skin aircraft, Flight Dynamics, 25, 1, pp. 39-42, (2007)
  • [3] Perkins D.A., Reed J.L., Havens E., Morphing Wing Structures for Loitering Air Vehicles, (2004)
  • [4] Tomohiro Y., Shin-Ichi T., Toshio O., Takashi I., Mechanical properties of corrugated composites for candidate materials of flexible wing structures, Composites, 37, pp. 1578-1586, (2006)
  • [5] Lin D.H., Pan D., Gao J., Chen S.K., Applications of Carbon Fiber Composite Materials in the Field of Aerospace, pp. 18-28, (1997)
  • [6] Tao B.Q., Shi L.H., Xiong K., Liang Da K., Yuan S.F., A smart composite structure system of self-diagnostic and self-adaptive strength, Journal of Applied Sciences, 17, 1, pp. 1-7, (1999)
  • [7] Rami H.A., Joonho C., Wei B.S., Roman P., Michael S., Refined Nonlinear Finite Element Models for Corrugated Fiberboards, (2008)
  • [8] Ellyin F., Kujawski D., Tensile and fatigue behaviour of glass fiber/epoxy laminates, Construction and Building Materials, 9, pp. 6425-6430, (1995)
  • [9] Aboura Z., Talbi N., Allaoui S., Benzeggagh M.L., Elastic behavior of corrugated cardboard: Experiments and modeling, Composite Structures, 63, pp. 53-62, (2004)
  • [10] Penga L.X., Liewb K.M., Kitipornchaib S., Analysis of stiffened corrugated plates based on the FSDT via the mesh-free method, International Journal of Mechanical Sciences, 49, pp. 364-378, (2007)
12