Abstract
In this paper, design criteria are proposed for an aircraft morphing wing skin and conventional lattice structures are evaluated against the design criteria. Although the structural deformation and aerodynamic loadings during the morphing process directly affect the skin structure, the design of the morphing skin has been overlooked. Five design criteria for the morphing skin of a variable camber compliant wing were derived from structural analysis results and reference values. According to the evaluation of conventional lattice structures, it is concluded that there is an absolute need for a new structure that satisfies the required design criteria.
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