Dynamic Gust Load Alleviation Study with Surrogate Models for Transonic Cruise Condition

Abstract

This study aims to predict dynamic responses of trailing-edge and droop-nose devices in 2D for a transonic cruise condition using surrogate models. The prepared surrogates, also known as reduced order models, were prepared using the Linear Frequency Domain solver, and are proven to provide quick results for a wide range of flight conditions while being computationally efficient. Three reduced order models were prepared, one for predicting gust load responses for given gust cases, a second purely to predict trailing-edge deflection dynamics responses, and a third to prognose droop-nose device deflection dynamic response. Each surrogate was modelled with 100 dynamic response results based on their respective parameter combinations, prepared as a Halton Sequence of points. The prepared surrogates were evaluated for quality of interpolation via the Leave-One-Out Test, and applied for prognosing three flight cases. The superposition principle was applied to combine the dynamic responses from each surrogate to evaluate the load mitigation capability of the trailing-edge and droop nose devices for the studied flight cases. The surrogate predictions were accurate within -2 orders of magnitude relative to conventional unsteady flow simulations and the results of this gust load alleviation study with the reduced order models are comparable to other studies. This study proves the applicability of surrogate models prepared with the Linear Frequency Domain method, as a knowledge-based engineering approach, to perform aerodynamic studies, relevant to conceptual research as well as industrial needs.