Al-Li alloy and aluminum honeycomb panel (AHP) are both excellent materials for aeronautical structures. In this paper, a plate-type aeronautical structure (PAS), which is a base mounting structure for 172 kg functional devices, is selected for comparative analysis with different materials. To compare system-level performance under multidisciplinary constraints, mathematical models for optimization are established and then structural optimization is carried out using Altair OptiStruct. For AHP, its honeycomb core is regarded as orthotropic material and its mechanical properties are calculated by Allen’s model in order to establish finite element model (FEM). The heights of facing sheet and honeycomb core are selected as design variables for size optimization. For Al-Li alloy plate, topology optimization is carried out to obtain its most efficient load path; and then a reconstruction process is executed for practical manufacturing consideration; to obtain its final configuration, accurate size optimization is also used for reconstructed model of Al-Li alloy plate. Finally, the optimized mass and performance of two PASs are compared. Results show that AHP is slightly superior to Al-Li alloy.

WS2/TiO2 composite layer was successfully in situ prepared by plasma electrolytic oxidation method adding Na2S and Na2WO4 into electrolyte. The structure, morphology and frictional properties of the composite layer were investigated by X-ray diffraction, scanning electron microscopy, and 3D confocal microscopy. It was found that the WS2/TiO2 composite layer is denser and has a lower friction coefficient when the adding concentration is 10–20 g/L. The WS2/TiO2 composite layer in situ prepared by plasma electrolytic oxidation is a new method to improve the trilogical hehavior of TC4 alloy.

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