Low-Fidelity Static Aeroelastic Analysis for Jig Shape Optimization of a Solar-Powered Hale Aircraft Wing

Abstract

This study investigates the static aeroelastic behavior of a lightweight, high-aspect-ratio wing designed for a solar-powered High Altitude Long Endurance (HALE) aircraft. The primary objective is to demonstrate that simplified, low-fidelity models can be effectively used to define the wing’s jig shape and stiffness distribution, ensuring optimal aerodynamic performance during cruise flight. High-aspect-ratio wings (HARWs) are susceptible to significant deformations under aerodynamic loading, which can alter the lift distribution and compromise performance. Therefore, accurate modeling of aeroelastic effects is essential, particularly in the early stages of the design process. The numerical analysis presented in this work uses a low-order, two-way fluid–structure interaction (FSI) method, combining the Vortex Lattice Method (VLM) and the Euler–Bernoulli beam model. This approach offers a balance between computational efficiency and physical accuracy. Validation was carried out by comparing simulation results with wind tunnel data, confirming the method's ability to predict lift coefficients and structural deformation with satisfactory accuracy. The study also introduces an innovative flat-upper-surface airfoil, optimized for solar panel integration and evaluated for static aeroelastic effects. Results show that, with a known distribution of stiffness and mass, the jig shape can be tailored to achieve the desired in-flight geometry. The proposed method provides a fast, reliable, and practical tool for early-stage wing design and is well-suited for engineering applications.