Optimization and Verification of Lightweight Low-Cost UAV Rudder Structure
Composite honeycomb sandwich structures are widely used in aircraft structures due to their high specific strength,specific modulus and designability.A lightweight and low-cost rudder structure scheme is proposed to increase the shear modulus by increase the density of the honeycomb core,thereby reducing the stress level of the composite panel and reducing the thickness of the panel.The rudder structure is designed and the optimization scheme is verified through finite element simulation calculation and experiment.Firstly,according to the shear modulus theory of honeycomb core,the honeycomb density that improves the shear modulus of honeycomb is selected.Secondly,finite element calculation and analysis are carried out on the structure,and it is found that the stress level of the skin decreases significantly with the increase of the shear modulus of the honeycomb core.Finally,honeycomb sandwich structures with different honeycomb core densities are designed for testing.The test results show that the denser the honeycomb core is,the higher its typical mechanical properties are,and the higher its residual strength after impact is.Both numerical simulation and experimental results verify the feasibility of this lightweight and low-cost UAV rudder structure optimization scheme.
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