Research on Flexible Honeycomb Structure Design for Morphing Aircraft
The wing skins of the morphing aircraft would be highly anisotropic with low in-plane extending stiffness to fit the wing transformation and high out-of-plane bending stiffness to undergo the aerodynamic loads. A material mechanics method is presented to evaluate the elastic modulus properties of the U-shape honeycomb structures. The U-shape honeycomb structures were proved to have low in-plane axial stiffness and good load resistance in other directions. Both finite element analysis and experimental tests were carried out to verify the accuracy of the proposed analytical formulation. And a theoretical analysis solution also was developed, which could well compare with both experimental results and FEA results. And the Possions ratio of the honeycomb structures was gained by FEA. It was also substantiated that U-shape honeycomb structures could be used for morphing aircraft wing skins.
Morphing aircraft Superelastic skin structures Honeycomb core Equivalent modulus
Peng Haifeng Dong Erbao Zhang Shiwu Yang Jie
Department of Precision Machinery and Precision Instrumentation USTC (University of Science and Technology of China) Hefei, Anhui Province, China
国际会议
哈尔滨
英文
2271-2274
2011-08-12（万方平台首次上网日期，不代表论文的发表时间）