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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2015, Vol. 36 ›› Issue (2): 680-690.doi: 10.7527/S1000-6893.2014.0090

• Material Engineering and Mechanical Manufacturing • Previous Articles     Next Articles

Design and analysis of a zero Poisson's ratio mixed cruciform honeycomb and its application in flexible skin

CHENG Wenjie1, ZHOU Li1, ZHANG Ping1, QIU Tao2   

  1. 1. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. Shenyang Aircraft Design and Research Institute, Shenyang 110035, China
  • Received:2014-03-25 Revised:2014-05-01 Online:2015-02-15 Published:2014-05-13
  • Supported by:

    National Natural Science Foundation of China (11172128, 51475228); Priority Academic Program Development of Jiangsu Higher Education Institutions

Abstract:

Variable camber/span/chord scheme for morphing flexible skin requires the skin to have the capacity of in-plane large deformation in one dimension and the ability to provide adequate out-of-plane bending and compressive rigidity. A zero Poisson's ratio mixed cruciform honeycomb is proposed and used as flexible skin design by covering silicone panel on its surface. The in-plane deformation mechanism of the honeycomb is theoretically analyzed, as well as the effect of the cell shape parameters on mechanical properties. Targeting the in-plane one-dimensional morphing capacity, the parameters of the honeycomb are optimized. The honeycomb structure is equivalent to an orthotropic material, and the resistance to bending out-of-plane and its influencing factors of the mixed cruciform honeycomb are studied. According to the design requirements of the variable camber trailing edge wing flexible skin, the applicability of the mixed cruciform honeycomb's structure parameter is studied. The results show that the designed honeycombs not only meet the operational requirement of the flexible skin but also have a light quality and small driving force.

Key words: flexible skin, honeycomb structures, zero Poisson's ratio, out-of-plane bending rigidity, equivalent elastic modulus

CLC Number: