A Generic Morphing Wing Analysis and Design Framework

Abstract

A generic framework for morphing wing aeroelastic analysis and design is presented. The wing is discretised into an arbitrary number of wing segments. Two types of actuation mechanisms are identified: inter-rib mechanisms operating across a wing segment and intra-rib mechanisms acting between two adjacent wing segments. Virtually, any shape can be obtained by distributing four morphing modes over the entire morphing wing. Three are an intra-rib mechanism and one is an inter-rib mechanism. The intra-rib modes are wing shear, twist and extension, and the inter-rib mode is wing folding. The wing is modeled using a close coupling between a non-linear beam formulation and Weissinger aerodynamics. The framework is intended to aid quick preliminary design of morphing wings to trade-off contradictory requirements in a flight mission. The morphing wing can be optimized for discrete points in the flight mission, and for the entire flight mission. The framework can be used to predict aerodynamic performance, load distribution, aeroelastic deformations, and the required actuation forces and moments and corresponding actuation energy. Therefore, the performance gains of wing morphing can be weighed against the energy costs and weight penalties due to the presence of the actuators. The functionality of the framework is demonstrated by making use of a folding and sweeping wing test case.