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The Desige and Optimization of Superelastic Flexible Honeycomb Structure

Author: PengHaiFeng
Tutor: YangJie；DongErBao
School: University of Science and Technology of China
Course: Mechanical and Electronic Engineering
Keywords: Intelligent deformation aircraft Hyperelastic skin structure Honeycomb core structure Equivalent elastic modulus Adaptive wing
CLC: V214.6
Type: Master's thesis
Year: 2011
Downloads: 88
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Abstract


The intelligent deformation aircraft able to change their shape to achieve higher levels of aerodynamic efficiency , has become an important development direction for the development of aerospace vehicles . Traditional skin function to maintain the aircraft shape, directly bear the aerodynamic loads and transmitted to the aircraft interior transverse longitudinal force component on the wing is deformed at the same time withstand the bending moment and shear force effect . Accompanied by deformation of aircraft development, and put forward some new requirements , both need to have a specific direction has a lower modulus in the plane to save the aircraft wing skins deformation energy at the same time in the other direction , to have a higher bearing the ability to avoid the surface occur due to the aerodynamic loads over a large deformation . The intelligent deformation aircraft development of the aircraft skin structure proposed new requirements. The deformation of the skin of the wing needs to have a high anisotropy , specific direction has a lower elastic modulus in the other direction has a higher aerodynamic bearing capacity , the paper design a better flexibility , a specific direction modulus low carrying capacity of the new super - elastic skin structure and mechanical properties of the honeycomb core unit theoretical calculation and finite element analysis and different geometrical parameters of a single unit cell of the honeycomb core and multiple cellular core unit body the axial stiffness measurement experiment ; through theoretical simulation and comparative analysis of the test . Experiment, simulation and theoretical analysis of the results showed that , the data of the three methods is relatively close to verify the theoretical analysis can be applied and the accuracy of the simulation method to obtain the super- elastic skin axial stiffness of the honeycomb core structure equivalent The modulus approximation formula . The article also briefly the two negative the mooring Song Mengpi unit , using the energy method to pull up the mechanics of cellular parameters derived optimal solution range and on optimal design toolbox , and processing of the experimental sample and its performance determination experiments to verify the negative Poisson characteristics of such a honeycomb unit .

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CLC: > Aviation, aerospace > Aviation > Basic theory and experiments > Aircraft Structural Mechanics > Honeycomb sandwich structure
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