Abstract
Morphing aircraft has been a research hotspot in the aviation field in recent years, and the morphing wing is the most important part of morphing aircraft. In this paper, a variable camber wing (VCW) based on corrugated flexible composite skin (FCS) was proposed and its variable camber function was designed and validated in detail by experiments. Firstly, the conceptual design of the VCW was presented and the effectiveness and feasibility of the conceptual design were discussed. Moreover, using carbon/epoxy unidirectional reinforced prepreg as raw material, FCS specimens were prepared by the vacuum bag method, and the tensile experiment was carried out. The tensile behaviour of the FCS was analyzed and validated by numerical simulation. In addition, according to the design scheme of the VCW, a VCW prototype was manufactured, and the variable camber experiment was performed to validate the variable camber function. Finally, the finite element analysis (FEA) model for predicting the variable camber function of the VCW was established and the driving moment calculated by the FEA model was compared with experimental results. The FEA results were in good agreement with experimental results.
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