Gust response analysis based on a nonlinear structural model and the unsteady aerodynamics of a flexible aircraft

Abstract

Purpose

This study aims to simulate gust effects on the aeroelastic behavior of a flexible aircraft. The dynamic response of the system for different discreet gust excitations is obtained using numerical simulations.

Design/methodology/approach

Coupled dynamics, including rigid and flexible body coordinates, are considered for modeling the dynamic behavior of the aircraft. Wing is considered flexible and other parts are considered rigid. Wing is modeled with nonlinear Euler Bernoulli beam. Moreover, unsteady aerodynamics based on the Wagner function are used for aerodynamic loading, and the results are compared with those of quasi-steady aerodynamics.

Findings

Von Kármán continuous gust is applied to this aircraft. In addition, the discrete “1- cosine” gust with different gust lengths is applied to the aircraft, and the maximum and minimum accelerations are computed. It is shown that the nonlinear modeling of the system represents the actual behavior and causes limit cycle oscillation phenomena.

Originality/value

This methodology can yield a relatively simple dynamic model for high aspect ratio aircrafts to provide insights into the vehicles’ dynamics, which can be available early in the design cycle.

Citation

Masrour, J., Sadati, S.H. and Shahravi, M. (2023), "Gust response analysis based on a nonlinear structural model and the unsteady aerodynamics of a flexible aircraft", Aircraft Engineering and Aerospace Technology, Vol. 95 No. 6, pp. 899-911. https://doi.org/10.1108/AEAT-07-2021-0216